Summary of overall soil colour analysis by using Munsell Soil Colour Chart in response to stable and unstable slope conditions.
\r\n\t
",isbn:"978-1-83768-472-4",printIsbn:"978-1-83768-471-7",pdfIsbn:"978-1-83768-473-1",doi:null,price:0,priceEur:0,priceUsd:0,slug:null,numberOfPages:0,isOpenForSubmission:!0,isSalesforceBook:!1,isNomenclature:!1,hash:"be61949c97a884e4342d41ec7414e678",bookSignature:"Dr. Rahul Shukla",publishedDate:null,coverURL:"https://cdn.intechopen.com/books/images_new/12326.jpg",keywords:"Preformulation Studies, Kinetics, Drug Delivery, Analysis, Stability, Drug Content, Optimization, Toxicity, Nanotechnology, Biosensors, Biocompatible, Market Approval",numberOfDownloads:null,numberOfWosCitations:0,numberOfCrossrefCitations:null,numberOfDimensionsCitations:null,numberOfTotalCitations:null,isAvailableForWebshopOrdering:!0,dateEndFirstStepPublish:"June 24th 2022",dateEndSecondStepPublish:"July 22nd 2022",dateEndThirdStepPublish:"September 20th 2022",dateEndFourthStepPublish:"December 9th 2022",dateEndFifthStepPublish:"February 7th 2023",dateConfirmationOfParticipation:null,remainingDaysToSecondStep:"21 days",secondStepPassed:!1,areRegistrationsClosed:!1,currentStepOfPublishingProcess:2,editedByType:null,kuFlag:!1,biosketch:"Researcher in the fields of Nanomedicine, Particle engineering, nanomaterials, dendrimers for drug delivery, Polymeric nanoparticles, nanocrystals, nanogels, nanoemulsions, and Nano-nutraceuticals for therapeutic applications. Member of Indian Red Cross Society, Association of Pharmaceutical Teachers of India (APTI), Indian Pharmacy Graduate Association.",coeditorOneBiosketch:null,coeditorTwoBiosketch:null,coeditorThreeBiosketch:null,coeditorFourBiosketch:null,coeditorFiveBiosketch:null,editors:[{id:"319705",title:"Dr.",name:"Rahul",middleName:null,surname:"Shukla",slug:"rahul-shukla",fullName:"Rahul Shukla",profilePictureURL:"https://mts.intechopen.com/storage/users/319705/images/system/319705.jpg",biography:"Currently working as Assistant Professor at Department of Pharmaceutics, NIPER Raebareli, India, did Ph.D. in Pharmaceutical Sciences from CSIR CDRI and J.N.U New Delhi, India, M Pharm from IIT BHU,Varanasi, India and B. Pharm from Jamia Hamdard, New Delhi. He has the past experience of as Research Scientist at Dr Reddys Laboratories, India and D.S Kothari Post-Doctoral Fellow at Panjab University, India. He has more than ten years of research and academic experience. He has more than 100 publications including 40 book chapters to his credit. He has filed 7 Indian Patent and 1 Copyright. Recently he has also published a book in Elsevier,Intech as Editor. His current research interests include targeted drug delivery systems, particle engineering, controlled delivery for neurodegenerative diseases, dendrimer mediated drug delivery, solubilization and bioavailability enhancements.\nEmail id: rahulshuklapharm@gmail.com, rahul.shukla@niperraebareli.edu.in \nhttps://scholar.google.com/citations?hl=en&user=PegtvC0AAAAJ",institutionString:"National Institute of Pharmaceutical Education and Research",position:null,outsideEditionCount:0,totalCites:0,totalAuthoredChapters:"1",totalChapterViews:"0",totalEditedBooks:"0",institution:{name:"National Institute of Pharmaceutical Education and Research",institutionURL:null,country:{name:"India"}}}],coeditorOne:null,coeditorTwo:null,coeditorThree:null,coeditorFour:null,coeditorFive:null,topics:[{id:"19",title:"Pharmacology, Toxicology and Pharmaceutical Science",slug:"pharmacology-toxicology-and-pharmaceutical-science"}],chapters:null,productType:{id:"1",title:"Edited Volume",chapterContentType:"chapter",authoredCaption:"Edited by"},personalPublishingAssistant:{id:"478197",firstName:"Veronika",lastName:"Radosavac",middleName:null,title:"Dr.",imageUrl:"//cdnintech.com/web/frontend/www/assets/author.svg",email:"veronika@intechopen.com",biography:null}},relatedBooks:[{type:"book",id:"1591",title:"Infrared Spectroscopy",subtitle:"Materials Science, Engineering and Technology",isOpenForSubmission:!1,hash:"99b4b7b71a8caeb693ed762b40b017f4",slug:"infrared-spectroscopy-materials-science-engineering-and-technology",bookSignature:"Theophile Theophanides",coverURL:"https://cdn.intechopen.com/books/images_new/1591.jpg",editedByType:"Edited by",editors:[{id:"37194",title:"Dr.",name:"Theophile",surname:"Theophanides",slug:"theophile-theophanides",fullName:"Theophile Theophanides"}],productType:{id:"1",chapterContentType:"chapter",authoredCaption:"Edited by"}},{type:"book",id:"3161",title:"Frontiers in Guided Wave Optics and Optoelectronics",subtitle:null,isOpenForSubmission:!1,hash:"deb44e9c99f82bbce1083abea743146c",slug:"frontiers-in-guided-wave-optics-and-optoelectronics",bookSignature:"Bishnu Pal",coverURL:"https://cdn.intechopen.com/books/images_new/3161.jpg",editedByType:"Edited by",editors:[{id:"4782",title:"Prof.",name:"Bishnu",surname:"Pal",slug:"bishnu-pal",fullName:"Bishnu Pal"}],productType:{id:"1",chapterContentType:"chapter",authoredCaption:"Edited by"}},{type:"book",id:"371",title:"Abiotic Stress in Plants",subtitle:"Mechanisms and Adaptations",isOpenForSubmission:!1,hash:"588466f487e307619849d72389178a74",slug:"abiotic-stress-in-plants-mechanisms-and-adaptations",bookSignature:"Arun Shanker and B. Venkateswarlu",coverURL:"https://cdn.intechopen.com/books/images_new/371.jpg",editedByType:"Edited by",editors:[{id:"58592",title:"Dr.",name:"Arun",surname:"Shanker",slug:"arun-shanker",fullName:"Arun Shanker"}],productType:{id:"1",chapterContentType:"chapter",authoredCaption:"Edited by"}},{type:"book",id:"3092",title:"Anopheles mosquitoes",subtitle:"New insights into malaria vectors",isOpenForSubmission:!1,hash:"c9e622485316d5e296288bf24d2b0d64",slug:"anopheles-mosquitoes-new-insights-into-malaria-vectors",bookSignature:"Sylvie Manguin",coverURL:"https://cdn.intechopen.com/books/images_new/3092.jpg",editedByType:"Edited by",editors:[{id:"50017",title:"Prof.",name:"Sylvie",surname:"Manguin",slug:"sylvie-manguin",fullName:"Sylvie Manguin"}],productType:{id:"1",chapterContentType:"chapter",authoredCaption:"Edited by"}},{type:"book",id:"72",title:"Ionic Liquids",subtitle:"Theory, Properties, New Approaches",isOpenForSubmission:!1,hash:"d94ffa3cfa10505e3b1d676d46fcd3f5",slug:"ionic-liquids-theory-properties-new-approaches",bookSignature:"Alexander Kokorin",coverURL:"https://cdn.intechopen.com/books/images_new/72.jpg",editedByType:"Edited by",editors:[{id:"19816",title:"Prof.",name:"Alexander",surname:"Kokorin",slug:"alexander-kokorin",fullName:"Alexander Kokorin"}],productType:{id:"1",chapterContentType:"chapter",authoredCaption:"Edited by"}},{type:"book",id:"2270",title:"Fourier Transform",subtitle:"Materials Analysis",isOpenForSubmission:!1,hash:"5e094b066da527193e878e160b4772af",slug:"fourier-transform-materials-analysis",bookSignature:"Salih Mohammed Salih",coverURL:"https://cdn.intechopen.com/books/images_new/2270.jpg",editedByType:"Edited by",editors:[{id:"111691",title:"Dr.Ing.",name:"Salih",surname:"Salih",slug:"salih-salih",fullName:"Salih Salih"}],productType:{id:"1",chapterContentType:"chapter",authoredCaption:"Edited by"}},{type:"book",id:"117",title:"Artificial Neural Networks",subtitle:"Methodological Advances and Biomedical Applications",isOpenForSubmission:!1,hash:null,slug:"artificial-neural-networks-methodological-advances-and-biomedical-applications",bookSignature:"Kenji Suzuki",coverURL:"https://cdn.intechopen.com/books/images_new/117.jpg",editedByType:"Edited by",editors:[{id:"3095",title:"Prof.",name:"Kenji",surname:"Suzuki",slug:"kenji-suzuki",fullName:"Kenji Suzuki"}],productType:{id:"1",chapterContentType:"chapter",authoredCaption:"Edited by"}},{type:"book",id:"3828",title:"Application of Nanotechnology in Drug Delivery",subtitle:null,isOpenForSubmission:!1,hash:"51a27e7adbfafcfedb6e9683f209cba4",slug:"application-of-nanotechnology-in-drug-delivery",bookSignature:"Ali Demir Sezer",coverURL:"https://cdn.intechopen.com/books/images_new/3828.jpg",editedByType:"Edited by",editors:[{id:"62389",title:"PhD.",name:"Ali Demir",surname:"Sezer",slug:"ali-demir-sezer",fullName:"Ali Demir Sezer"}],productType:{id:"1",chapterContentType:"chapter",authoredCaption:"Edited by"}},{type:"book",id:"872",title:"Organic Pollutants Ten Years After the Stockholm Convention",subtitle:"Environmental and Analytical Update",isOpenForSubmission:!1,hash:"f01dc7077e1d23f3d8f5454985cafa0a",slug:"organic-pollutants-ten-years-after-the-stockholm-convention-environmental-and-analytical-update",bookSignature:"Tomasz Puzyn and Aleksandra Mostrag-Szlichtyng",coverURL:"https://cdn.intechopen.com/books/images_new/872.jpg",editedByType:"Edited by",editors:[{id:"84887",title:"Dr.",name:"Tomasz",surname:"Puzyn",slug:"tomasz-puzyn",fullName:"Tomasz Puzyn"}],productType:{id:"1",chapterContentType:"chapter",authoredCaption:"Edited by"}},{type:"book",id:"3569",title:"Biodegradation",subtitle:"Life of Science",isOpenForSubmission:!1,hash:"bb737eb528a53e5106c7e218d5f12ec6",slug:"biodegradation-life-of-science",bookSignature:"Rolando Chamy and Francisca Rosenkranz",coverURL:"https://cdn.intechopen.com/books/images_new/3569.jpg",editedByType:"Edited by",editors:[{id:"165784",title:"Dr.",name:"Rolando",surname:"Chamy",slug:"rolando-chamy",fullName:"Rolando Chamy"}],productType:{id:"1",chapterContentType:"chapter",authoredCaption:"Edited by"}}]},chapter:{item:{type:"chapter",id:"57634",title:"Slope Failure Analysis Using Chromaticity Variables",doi:"10.5772/intechopen.71248",slug:"slope-failure-analysis-using-chromaticity-variables",body:'\nThe slope failure trend has increased significantly owing to improper changes in land usage and ranked 10th among the most devastating natural disasters in the world occurring across almost all terrains with steep slopes singled out as the most susceptible to sliding [1]. Marques et al. [2] reported an annual rate of soil erosion of 30–40 ton/ha in developed countries of Asia, Africa and South America. On a global scale, the annual loss of 75 billion tons of soil costs the world about US$400 billion per year or approximately US$70 per person per year [3]. Soil erosion from catchments with natural forests is minimal, but levels of soil erosion tend to increase when natural forest is changed to tree crop plantations.
\nThere were many incidents of slope failure occurring both at constructed and natural slopes that caused huge number of deaths especially in tropical countries which received high temperatures and yearly precipitation that brought a large amount of water and consequently triggered extreme effects on the slopes [4]. With these geological factors and climate condition, added with other contributing aspects, slope failure can be considered as one of the crucial threats of environmental catastrophe in Malaysia that requires a serious attention. For example, the slope failures in Hulu Kelang areas have been studied by a number of local researchers and practicing engineers. Ashaari et al. [5] had carried out a field survey work at Hulu Kelang area. A total of 152 slope failures scars of both soil and rock slopes were identified as the potential catastrophe sites. Gue and Cheah [6] investigated the slope failure motions at Kampung Pasir, Hulu Kelang using continuous monitoring approach. They found that the ground had moved from 2 to 17 mm during the monitoring period of 10 days. Hua-xi and Kun-long [7] had performed a detailed investigation on one of the major slope failures occurred in Hulu Kelang area, known as Bukit Antarabangsa 2008 landslide. They concluded that prolonged rainfall during the monsoon season was one of the main factors triggering the failure.
\nThe issue of slope failure in the highway construction industry is closely related to the soil factors [8]. The weakening of soil properties that causes slope failures is resulted from physiochemical activities. It is generated by natural phenomena and human activities through excessive developments which lead to disturbance and destruction of soil surface which are hazardous to slopes. There are many indicators of soil qualities such as organic matters and nutrient deficiency resulted from leachate showing a decline in soil chemical properties while erosion and water infiltration are examples of physical degradation processes [9]. Soil chemical indicators can be identified through specified considerations based on the existence of certain amount of soil colloids whereas physical indicators can be determined by exploring on certain physical appearances and water-holding capacity of the soils. Biological indicators are determined by identifying the amount and mass of microorganisms through concentrations of biogeochemical responses or determining the populations of microorganisms in slope soil.
\nThe soils of the humid tropic such as highly weathered soil (Oxisols) and sandy soil have been observed to be problematic, especially with regard to their fertility. Reviews of research work on current slope soil development in Malaysia, Thailand and Indonesia have significantly shown that such fertility constraints could be improved. Poor fertility of the saprolite is more complex and should be imposed with serious enhancement and management activities. Furthermore, like all acid soils of the humid tropics, Oxisols soils are low in pH value which causes many potential associating problems, including H, Al, and Mn toxicity, Ca deficiency, low CEC, P fixation and low microbial activities [9]. The shallow topsoil is highly vulnerable to erosion and if it is not managed properly especially after the process of clearing the vegetation on top of soil surface, it can slowly lose its original fertility and beneficial physical properties which finally will cause shallow slope failure. Several reviews on the characteristics and management of these soils did not take into account the effect of terracing in exposing saprolites or C horizon. With the surface soils and subsoils already being considered problematic, one could only imagine what kind of impact the saprolites pose to soil fertility.
\nTwo different localities that were chosen as sampling sites are North South Highway (PLUS) and East Coast Highway (LPT). The whole samples were taken from the slopes that have the gradient lower than 35°. As for unstable soil sample, only slope that collapsed abruptly were collected whereas for stable sample collected from the slope that fully covered by vegetation (Figure 1). At North South Highway, 30 soil samples of stable and 30 soil samples of unstable slopes were collected randomly from two sections which were at Section C2 (Tanjung Malim to Bidor) and Section C3 (Sungai Buloh to Tanjung Malim); whereas, in East West Highway (LPT), 30 soil samples of stable and 30 soil samples of unstable slopes were collected from Section 1 (Karak to Jengka) and Section 2 (Jengka to Kuantan). Therefore, a total of 120 soils samplings were collected from those two different localities in Peninsular Malaysia. Auger set was used to collect soil sample at the designated area and soil samples were collected in the depth of 30 cm from the surface. Then, the soil samples were stored in plastic bag and labelled for further analysis.
\nCondition and appearance of stable and unstable slopes soil.
The collected samples were air-dried, homogenised and sieved to pass a 2 mm mesh sieve for chromaticity variables analysis by CIELAB spectrophotometer. By using a CIELAB spectrophotometer analysis, 10 g of samples were accurately weighed by using analytical balance and was transferred into polystyrene cell and was placed horizontally under spectrophotometer. During the measurement, each sample was measured at three points randomly in order to obtain the mean colour and the variability between different points. When the measurement was completed, the variables L*a*b*, c* and h* values were displayed on the built by graphical display following each reading. Readings were entered by hand into an Excel spreadsheet.
\nFor analysis, all data gathered were inserted in Microsoft Excel. The mean and standard deviation for each concentration of every experiment was calculated. One-way ANOVA were conducted to measure the validity of the data and the significance of the variation in the results between the stable slope and unstable slope for each soil property.
\nSoil colours give valuable clues in regard to soil properties, soil classification and interpretation. Through this study, the results have been discussed in such a way that it is possible to relate between the Munsell and CIELAB system. It is because, Munsell and CIELAB system has a similar cylindrical structure, and the colour parameters L*, C * [over] ab (CIELAB) as hue, value, chroma (Munsell) represent the same colour perception attributes (hue, lightness, chroma) [10].
\nScoring with Munsell relies upon human perceived assessment of the three colour attributes: hue, value and chroma. These attributes give valuable clues in soil properties, soil classification and interpretation. Hue is identified as the basic spectral colour or wavelength (Red, Yellow, Blue, or in between, such as Yellow-Red). Value refers to measurement of soil organic matter (OM) in relation to the lightness or darkness of a colour and the range is from 0 (pure black) to 10 (pure white); while chroma is a measurement of colouring agents like Iron or Manganese and the range is from 0 (no colour) to 8 (most coloured).
\nFor this study, the analyses by using Munsell Soil Colour Chart showed a slight difference in stable and unstable slopes. The hues for overall samples were YR (Yellow-Red) and the hues indicating the stable slopes were between 2.5YR and 5YR while the range of hues that indicated the unstable slope was between 5YR and 10YR (Table 1). Within each letter range, hue became more Yellow and less Red as the numbers increased. Based on the result, 2.5YR is redder than 5YR and 7.5YR is less yellow than 10YR. This result is consistent with Fontes and Carvallho [11] that reported hue 2.5YR indicates hematite predominate (reddish black), hue 10YR indicates that the soil has goethite (yellowish brown) but does not have hematite whereas hues 7.5YR and 5YR indicate that the soil contains a mixture of goethite and hematite. It is generally believed that hematite, goethite and probably maghemite are the main pigmenting agents in the soil systems [12]. Thus, the different Oxisols variant studied for all sites could be categorised into two main groups which are hematitic or red soil comprising most of the samples from stable slope, and goethite or yellow soils made up most of samples from unstable slope. Therefore, the Munsell chroma combined with the hue value was also used to predict the relative amount of Iron oxides in highly weathered soils [11]. Iron oxides are reddish, yellow and orange in colour [13] and showed in a very small particle size in soils in comparison with other soil minerals which favour their capacity for pigmentation.
\nSummary of overall soil colour analysis by using Munsell Soil Colour Chart in response to stable and unstable slope conditions.
Ibáñez-Asensio et al. [14] stated that the dark colour of the soil organic matter is caused by the humid acid fraction and a huge amount of calcium carbonate that is also influencing organic matter on lightness. Carbonates of Calcium and Magnesium contribute to the white colour of the soils. Moreover, in terms of the differences in the regression equations, Schulze et al. [15] pointed out that the relationship between the organic matter content and the Munsell value of soils was strongly influenced by soil texture, parent material and vegetation. High contents of clay and sand affects the soil colour to become yellowish, reddish and whitish. Clay is the smallest particle in soils and exhibits colloidal properties. Some of the clays, like Iron oxide clay, play an important role in soil aggregation and in addition impart red to yellow colours to soils. Embrapa [16] stated that most minerals are not highly coloured and when they are coated with humus and Iron oxides, they take on the colours of humus (black or brown), Iron oxides and hydroxides (red and yellow). Table 1 showing summary of overall colour analysis by using Munsell Soil Colour Chart for 120 soil samples in response to stable and unstable slopes.
\nStatistical analysis showed that there was a significant difference for Oxisols colour variable L* between stable and unstable slopes. The value of colour variable L* was the lowest in stable slopes for each study area compared to unstable slopes. The value of variables L* in stable slopes ranged from 44 to 50 whereas in unstable slopes, from 61 to 63 (Figure 2).
\nThe average of variable L* in Oxisols for stable and unstable slopes.
Statistical analysis showed that there was a significant difference for Oxisols colour variable a* between stable and unstable slopes. The values of colour variable a* were higher in stable slopes from sites, Plus C2 and Site 2 LPT in comparison to unstable slopes. However, the results also revealed that the values of variable a* in stable slopes from sites, Plus C3 and Site 1 LPT were lower compared to unstable slope respectively. The level of variable a* in stable slopes ranged from 7.2 to 11.8 whereas in unstable slopes, from 5.4 to 10.5 (Figure 3).
\nThe average of variable a* in Oxisols for stable and unstable slopes.
Statistical analysis showed that there was a significant difference for Oxisols colour variable b* between stable and unstable slopes. The values of colour variables b* were higher in unstable slopes for each study area compared to stable slopes. The values of variable b* in unstable slopes ranged from 19 to 22.7 whereas in stable slopes, from 16.5 to 19.8 (Figure 4).
\nThe average of variable b* in Oxisols for stable and unstable slopes.
Statistical analysis showed that there was a significant difference Oxisols colour variable c* between stable and unstable slopes. The values of colour variable c* were higher in stable slopes for each study area compared to unstable slopes. The values of variable c* in stable slopes ranged from 21 to 25 whereas in unstable slopes, from 18 to 23 (Figure 5).
\nThe average of variable c* in Oxisols for stable and unstable slopes.
Statistical analysis showed that there was a significant difference for Oxisols colour variable h* between stable and unstable slopes. The values of colour variable h* were higher in stable slopes for each study area in comparison to unstable slopes. The values of variable h* in stable slopes ranged from 65 to 76 whereas in unstable slopes, from 60 to 69 (Figure 6).
\nThe average of variable h* in Oxisols for stable and unstable slopes.
Statistical analysis showed that there was a highly significant difference (P < 0.0001) in overall CIELAB soil colour variables analysis between stable and unstable slopes. The results of the quantitative measurements of soil colour performed in the laboratory are summarised in Table 2. The value of variables L* was higher in unstable slopes rather than stable slopes with the values of 62 and 48, whereas the value of variables a* was slightly lower in unstable slope with the value of 8.1 compared to the stable slope with 8.7 in value. The value of variables b* was slightly higher in unstable slope in comparison to stable slope with the value of 21 and 18. Finally, the value of variables c* and h* were lower in unstable slopes as compared to the stable slopes. In conclusion, the unstable slopes for overall sites consist of higher value of colour variables L*, b* and lower value of colour variables a*, c* and h*, respectively. Since there is a significant difference of colour variables in the comparison of different slope condition, it is possible to conclude the soil colour can be an indicator for early warning of shallow slope failure.
\nColour variables | \nSlope condition | \n|
---|---|---|
Stable slope | \nUnstable slope | \n|
L* (lightness) | \n48 ± 6 | \n62 ± 6 | \n
a* (red-green) | \n8.7 ± 2 | \n8.1 ± 1.5 | \n
b* (yellow - blue) | \n18 ± 4 | \n21 ± 4 | \n
C* (Chroma) | \n23 ± 4 | \n20 ± 4 | \n
h* (hue) | \n70 ± 6 | \n66 ± 6 | \n
Mean values for overall soil colour variables in stable and unstable slopes.
Munsell Soil Colour Charts are develop for colour identification of an object by direct comparison by using set of colour palettes with a sequence of colour samples on each page in it. CIELAB, is the methods that operated without relying on human eye. It works by scanning an object via spectrophotometer and the outcomes were recorded in graph in three dimensional colour space. This equipment is very effective as supporter to the Munsell colour system. Some complications that make the outcomes an alternative and attractive prospect are inherent to the Munsell colour system for example, a great degree of subjectivity and unpredictability between researchers. CIELAB spectrophotometer able to capture more colour data than Munsell colour charts because the level of precision by CIELAB spectrophotometer is available in colour description.
\nThrough the result and analysis using CIELAB spectrometer, variation of soil colours became apparent at different slope conditions. The soil samples collected from the unstable slopes were characterised by the high values of variables L*, b* and slightly lower values of variables a*, C* and h* (Table 2). The difference was also detectable by the soil colour reader using the Munsell colour system, where the findings indicated that the hues for overall samples were classified as YR (Yellow-Red), with the stable 2.5YR to 5YR whereas unstable slope 5YR to 10YR, respectively. The positive value CIELAB variables a* and b* are the indication that this soil sample of Oxisols are dominance by the Iron oxide which influencing the soil colour and also can detected directly through the Munsell Soil Colour Chart. This difference can be measured through the b* value where a strong positive value indicates a strong yellow colour and a strong negative value indicates a strong blue colour whereas a* value where a positive value indicates a red colour and negative value indicates green colour [17].
\nMoreover, the high value of variables L* in unstable slope in comparison to stable slope is the indication that the unstable slope consist low amount of organic matter content which have a great influencing as among the colouring agent for Oxisols soil. These observations also suggest that the colour of the slope soil samples, particularly the variable L* as soil colour that attributes lightness (similar to Munsell value) provides the most information about the relationship with soil properties which accounted to the ranges of 61–63. Since there was a significant difference for colour variables in the comparison of different slope conditions, it is possible to conclude the soil colour can be an indicator for early warning of shallow slope failure.
\nThe study on the relationship between chromaticity variables and other soil properties was initiated by investigating the response of soil colour, in stable and unstable slopes samples, in relation to some general properties of the slope soils. CIELAB analysis and Munsell Soil Colour Chart tests revealed important relationships between chromaticity variables and soil properties. These observations suggest that the variable L* provides marked indicator about the relationship with most of the soil properties. Colour variable L* is closely correlated with soil texture including clay and sand contents, soil organic carbon, Iron oxide and Aluminium concentrations. The relationships between L*, Iron oxide and Aluminium which contributed to the darkening of the soils, either individually or associated with other organic materials; also had been revealed by Ibáñez-Asensio et al. [14]. Furthermore, colour variable L* was found strongly affected by differences in climate and vegetation as well as soil moisture regime. The L* variable was the lowest (darker) in stable slope soils which covered by vegetation particularly with fern species in comparison with those unstable slope soils without vegetation. This attributed to the effect on the soil colour of the variations in the composition and quantity of soil humus [17].
\nTherefore, based on the results, it can be pointed out that unstable slope higher value of variable L* (lightness), which was the evidence that soil properties have strong influence on the weakly developed soils. Several researchers found the lightness value decreased when the number of clay sized particles increased and also indicated the presence of Iron oxides [15]. Most of Iron oxides are seen in small particle size so that very small quantities would be adequate in influencing soil colour since some of those particles had remained on the negatively charged surface of clay grains [15]. The correlation of L* with clay content, may be caused by the relationship of free oxides and humid compounds with phyllosilicates, favoured by their superficial activities. The phyllosilicates act as a support for the other pigments as the increase in phyllosilicates content (white or greyish pigments) would also cause an increase in L* [17].
\nIron oxide and soil total organic carbon have a combined influence on L*, and this effect is closely linked to the soil particle sizes. Schulze et al. [15] had found that soil organic carbon and Iron influence on the spectral reaction of soils interrelates with particle size. The results of the present research are consistent with their findings as it is confirmed that interactions between texture and Iron exist. It also showed a positive relationship between soil lightness and soil texture. Sawada et al. [17] also had found low values for soil colour variables particularly L* in stable slope soils with high clay content, high organic carbon and high concentration of Iron oxide. On the contrary, unstable slope contains high values of colour variables, high sand contents, low organic carbon and less concentration of iron oxide. Soil with coarse textures and low levels of organic carbon, consequently, generated greater lightness values than in soils with finer textures and higher contents of organic matter. The analysis used in this study confirms the multivariate relationships and the outcomes pointing to this direction. Finally, in relation to soil organic carbon content effects on lightness, this research had discovered the same relationship found by Konen et al. [18].
\nMoreover, in this study, it was found that variable h* (Hue) of the stable slope was slightly higher in comparison to unstable slope. This could be caused by the joint migration of the clay and Iron formed in the slope soils. The higher duration of the annual dry period at altitudes of less than 1000 m, higher temperatures with the consequent rising in dehydration of the Iron forms, could be the factors of this greater reddening [13]. This result is also consistent with the finding through the Munsell Soil Colour Chart that indicates the hues for overall samples were YR (Yellow-Red) which were influenced by high concentration of Iron oxides in studied area. Iron oxides can reflect the surrounding of the environments in which they are formed and are considered as colouring agents for most of slope soil samples. Curi [12] stated that in the soil systems, hematite, goethite and probably maghemite which are classified under Iron oxides are the main pigmenting agents in influencing soil colour. The hues that indicate stable slope are between 2.5YR and 5YR and unstable slope are between 5YR and 10YR. 10YR hue shows that the soil contains goethite predominance while 2.5YR hue is hematite predominate, whereas hues 7.5YR, and 5YR show a combination of goethite and hematite. From the findings it can be concluded that the yellowish colour for most of the unstable slope soil samples are caused by a yellow to brown iron oxide mineral called goethite. Generally, these soils have lower iron contents extracted by the sulphuric acid digestion than the other. That occurs either because the parent material had a low iron content or because iron was removed from the soil by percolating water.
\nDue to the yellower colour, it is relatively easy to distinguish the horizons for instance the red colour dominance for most of the stable slope soil samples are due to hematite and a dark red due to iron oxide. The content of iron oxides extracted by Non-ferric Red Oxisols are quite variable in texture, which ranges from medium to very clayey. The parent material for these soils is very variable and ranges from sandstones to pelitic rocks, with the major requirement being relatively high iron content. Similar to the variable a* value in stable slopes which is slightly higher and this means that the soils are slightly redder in comparison to unstable slopes which contain high sand fraction and slightly higher b* values, it means that the soil is dominantly yellowish in colour [18].
\nIn addition, with respect to the overall soil samples, the conditions of slope are essential in influencing the chroma values in such a way that the stable slopes has a slightly high chromatic value than the unstable slopes. As was stated before, this is interrelated to the larger amount of Iron formed in the stable slopes which might be caused by modification and illuviation of slope structure. Chroma C* is also correlated with total organic carbon content, which has also been described for other soils [19] and most strongly associated with soil texture content. This means that the colour of the texture becomes more uniform as the contents of these minerals increases, which may be attributable to the processes of reduction and enlargement.
\nThe overall soil colour analyses lead to the findings that the CIELAB variables L* (lightness), c* (chroma) and h* (hue) with significant values of colour variables measured at different slope conditions, provide the most information in relation to soil properties. Regarding to the relationship between soil properties, the study had identified that soil texture, total organic carbon (TOC), Iron oxide and Aluminium concentration were strongly interrelated with soil colour variables at the studied areas. It is also recommended that in order to explain and detect the colour of slope soils, the function and availability of lightness-darkness as an analytical factor should be highlighted, together with the amount of Iron oxides. To sum up, indicators that can be used to predict shallow slope failure based on chromaticity variables are high value of variable L*, low values of variables c* and h* and the Munsell Soil Colour Chart were between 2.5YR and 5YR (hematite predominance). The correlative relationships between chromaticity variables and soil erosion suggest that all these properties may potentially be used as an indicator of slope failure.
\nThese findings should be used to trigger further investigation of the reasons or sources for the failure of the slope soil and an assessment made of the potential risks to humans or the environment if the failure continues. Through this study it showed that the weakening of the slope soil properties occurred mostly due to erosion effect towards the existing soil properties. Consequently, serious attention should be emphasised on each slope along the highways particularly the unstable slopes in order to reduce harmful effects. Most of the landslides occurred during the rainy days when the soil is relatively wet. It would require special preventing strategies such as slope levelling, terracing and practicing in planting suitable vegetation in slope areas.
\nVegetation and slope stability are interrelated by the ability of the plant life growing on slopes to both promote and hinder the stability of the slope. The relationship is a complex combination of the type of soil, the rainfall regime, the plant species present, the slope aspect, and the steepness of the slope. Any study of soil properties should take serious attention towards any vegetation above the slope area as this factor is crucial in influencing the loss of several nutrients. Planting vegetation will increase the organic carbon in soil thus the ions of organic carbon will bind with ion in clay and hydrogen in soil. These reactions will strengthen the soil structure. Knowledge of the underlying slope stability as a function of the soil type, its age, horizon development, compaction, and other impacts are the major underlying aspect of understanding how vegetation can alter the stability of the slope. Our study did take note of vegetation, but for future studies, a more thorough study with regard to the vegetation of the areas in conjunction with certain soil properties would be interesting to be highlighted. The research findings showed that unstable slope was more likely to occur if there is no plant life growing on the top of soil. The less vegetation growing in the soil the more likely that erosion will happened. Vegetation can protect the soil from the impact of the rain and slows down the infiltration process. Plants with deeper roots are better at holding the soil together and protect it from erosion.
\nFinally, an efficient management on landslide risk, the coordination between regions, departments concerned, universities, research centres, non-governmental organisations and local peoples in landslide-prone would be helpful in order to obtain the better risk management. This coordination and communication would minimise the wasting budget, man power, time allocation and miscommunication of decisions taken in future. Additionally, the findings of this research can be integrated with the various components of landslide risk in risk information and management systems which should be developed as spatial decision support systems for local authorities dealing with risk management. The availability and quality of historic landslide database cannot be overemphasised since they constitute the basis for all components of landslide. Modern technologies, such as geographic information system (GIS) and remote communications, should have a wider application in landslide risk assessment and management.
\nThe authors would like to thanks Ministry of Education (MOE) and International Islamic University Malaysia (IIUM) for the Research Grant NRGS13-002-0002.
\nFlutter is defined as the dynamic instability of aeroelasticity. Flutter is one of the most dangerous aeroelasticity phenomena as it could lead to a destroyed structure. The reason is the unsteady aerodynamic forces generated from elastic deformations of the structure that are usually involved with complicated phenomena such as the shock wave/boundary layer interaction, flow separation, nonlinear limited cycle oscillation, and more. Flutter is determined as a critical issue determining the reliability of the airplane wings or aircraft engine turbo-machine blades. Therefore, in the early phase of the structural design of the air vehicle, aircraft engine turbo-machinery, flutter problems should be calculate and predicted. However, accurate prediction of the flutter is very challenging due to the perplexing physical phenomena and the required large amount of computation [1, 2, 3, 4].
Coupled aeroelastic solution procedures use strongly coupled algorithms which contained sufficient interaction between computational fluid dynamics (CFD) and computational structural dynamics (CSD). As computer technology progresses, higher-order methods of CFD based on the Euler and the Navier-Stokes equations become more attractive due to the ability of the model and its more accurately transonic, nonlinear, and viscous effects. CFD has also advanced from two-dimensional problems to fully three-dimensional problems with or without coupled solution of the structural equations (CSD). The flow solvers used in aeroelastic analysis include 3D Euler and Navier-Stokes solvers which assumed inviscid flow.
The dynamic response of flutter characteristics of the first AGARD 445.6 wing standard aeroelastic configuration was studied using an unsteady Navier-Stokes algorithm in order to investigate a previously noted discrepancy between Euler flutter characteristics and the experimental data [5]. The 3D implicit upwind Euler/Navier-Stokes code (CFL3D Version 2.1) was previously modified for the time-marching aeroelastic analysis of wings using the unsteady Euler equations. A linear stability analysis and a time-marching aeroelastic analysis were used to determine the flutter characteristics of the isolated 45° swept-back wing. The flutter characteristics of the wing were determined using traditional V-g analysis. This stability analysis was determined at free-stream Mach numbers of 0.96 and 1.141 using the generalized aerodynamic forces calculated by solving the Euler equations and the Navier-Stokes equations.
Computational flutter required a fluid-structure interface as a common boundary to exchange the aerodynamic loads and structural displacements at the wing surface. But, the aerodynamic and structural grids were not coincident due to different systems used (fluent solver for aerodynamic grids and mechanical ADPL solver for structural grids). Therefore, the system coupling tool in ANSYS Workbench was used to transfer the aerodynamic pressure loads from the CFD grid points to the CSD grid points and vice versa, which ensured a conservative transfer of energy between the two systems [6].
Time-accurate aeroelastic simulations were carried out using the modal coupled aeroelastic implementation for a standard experimental test case: the AGARD 445.6 aeroelastic wind tunnel model in the subsonic and transonic regions [7]. A numerical methodology coupling Navier-Stokes equations and structural modal equations for predicting 3D transonic wing flutter was described in [8]. A modal approach is used for the structural response. The results indicate that the first five modes are sufficient to accurately model the wing structure response. In Ref. [9], an unsteady Reynolds-averaged Navier-Stokes (RANS) model was coupled with normal modes of structure to predict the flutter boundary for the AGARD 445.6 wing. A new integrated CFD-CSD simulation for flutter calculations based on a parallel, multiblock, multigrid flow solver for the Euler/Navier-Stokes equations using the ANSYS software was found in [10]. Computations were performed for a three-dimensional test case of AGARD 445.6 wing to validate and establish the usefulness of the simulation. Immersed boundary method solved Navier-Stokes equations for flow in couple with the Newton equation for structure movement under the effect of friction force exerted on the structure surface to carry out fluid–structure interaction (FSI). However, computational grids needed to be re-meshed in each time step due to changes of the structure position in time. To overcome this obstacle, immersed boundary method and finite volume methods were both invoked in solving the interaction between fluid flow and moving structure [11]. This research estimated the numerical and experimental results on the wing structure at a low speed with four different wing models such as two rectangular and two trapezoid 3D-shape wings, each 3D-shape wing had symmetric and asymmetric airfoil, respectively.
The subsonic aeroelastic stability of a two-dimensional panel resting on a continuous elastic foundation was investigated in Ref. [12]. Tests were conducted experimentally on a 104 × 24 × 0.018 in. rectangular aluminum panel in a low-speed wind tunnel. Comparison of experiment and theory showed a good agreement in flutter speed and wavelength but poor agreement in wave speed and frequency at flutter. This discrepancy was attributed to the limitations in the test setup as well as to the general difficulty of predicting the wave speed and frequency as accurately as the flutter speed. Reference [13] tested the first AGARD standard aeroelastic configuration for dynamic response, 445.6 wing, in the 16 foot transonic dynamics tunnel at the National Aeronautics and Space Administration (NASA) Langley Research Center. Several models of the wing were tested in the transonic dynamic tunnel including full-span and semispan models over a range of Mach number from 0.338 to 1.141. The NASA conducted experiments in wind tunnel to estimate the aeroelastic characteristics of new and advanced flight vehicles, including fixed-wing, rotary-wing, and space-launch configurations. Reviews and assessments were made regarding available facilities, measurement techniques, and other means and devices useful in testing. The needs and requirements for advances and improvements in testing capabilities for future experimental research and development programs are described [14].
In [15], aeroelastic concepts for increased aircraft performance were mentioned. Active aeroelastic concepts as well as robust analysis concepts aiming at efficient analysis were carried out using numerical models with uncertain or varying model parameters. A high aspect ratio wing in wind tunnel testing conditions was considered for exploitation of fluid-structure interaction of active aeroelastic structures. The structural flexibility was exploited by using multiple control surfaces such that the deformed wing shape gives minimum drag for different flight conditions. Two different drag minimization methods were carried out: one was to reduce induced drag based on numerical optimization techniques, and another was to reduce measured total drag using real-time optimization in the wind tunnel experiment.
An approach for the prediction of dynamic modal transient response and flutter characteristics of structures with unknown system parameters, such as stiffness and mass, using experimental modal parameters was remarked in [16]. A finite element model was created by using the actual material properties of the structure to study the correlation of the results. The computed transient responses and flutter velocities by the proposed method using experimental modal parameters observed that material properties were not a prerequisite.
In Ref. [17], transonic flutter characteristics of AGARD 445.6 wing between the numerical method [5] and the experimental data of NASA’s experiment were compared [13]. The comparison provided the basis for developing the numerical setup and the experimental setup to check out subsonic flutter characteristics of some simple wing structures (e.g., a thin plate). Aeroelasticity on airplane wing, which had supercritical airfoil, was carried out in [18]. The model wings were made from different materials and dimensions. Hence, varied wing structures were created to accomplish a comprehensive analysis, and the flutter velocity was also restricted to appropriate values within the working range of experiment devices. At the same time, infinite element method with the help of the ANSYS software was also conducted to simulate the phenomena on the same model wings as a verification for the precision of the experimental models.
The generalized equations of aeroelasticity motion:
where:
w: structural displacement at any time instant and position.
q: generalized displacement vector.
[M]: generalized mass matrice.
[C]: damping matrice.
[K]: stiffness matrices.
ϕ: normal modes of the structure.
N: total number of modes of the structure.
F: generalized force vector, which is responsible for linking the unsteady aerodynamics and inertial loads with the structural dynamics.
Eq. (1) shows that there are distinct terms representing the structure, aerodynamic, and dynamic disciplines. This equation was solved numerically by integrated CFD-CSD tool on the ANSYS software. This method was also called the two-way fluid-solid interaction (FSI). Aerodynamic loads were first calculated by CFD solver. Then, these loads were used to calculate the structural response of the wing structure through the fluid-solid interface. By using CSD solver, the structural deflection was estimated, and the mesh in each time step was deformed. The simulation of the two-way FSI is presented in Figure 1 [10].
Two-way FSI algorithm.
Following [8], the first four modes of vibration were sufficient to accurately model the wing structure response. So, in order to determine the time step of the unsteady problem, a modal method was applied to estimate first the natural frequency of the first four modes and then calculate the time step using the following formula:
where:
Δt: time step
f: natural frequency
The flutter velocity was estimated from the vibration of the wing tip position, the most dangerous position of the wing [5, 8, 9, 13]. From the variation of this position, the damping coefficient except the influence of structural damping was measured. It means that there was an effect of aerodynamic damping coefficient on the vibration of the wing structure. The aerodynamic damping coefficient was calculated as follows:
where:
Xi: ith peak of vibration.
n: number of periods.
ζ: aerodynamic damping coefficient.
The damping coefficient increased/decreased when the air velocity decreased/increased. The type of vibration was distinguished from the value of damping coefficient:
ζ > 0: The vibration was convergent. The wing structure was stable.
ζ < 0: The vibration was divergent. The wing structure was unstable.
ζ = 0: The vibration was harmonic oscillation. The wing was in critical state. The air velocity was in the flutter velocity.
AGARD 445.6 wing with aspect ratio of 1.65, taper ratio of 0.66, and 45o sweep angle at quarter chord line was studied as seen in Figure 2. The cross section of the wing was NACA65A004 airfoil in the stream-wise direction. This NACA65A004 airfoil was a symmetric airfoil with a maximum thickness of 4% of the local chord. The dimensions of the wing were root chord of 0.558 m, tip chord of 0.368 m, and semispan of 0.762 m. The wing model used in aeroelastic experiments [13] was constructed by laminated mahogany which was modeled as an orthotropic material with different material properties in different directions. The properties of the laminated mahogany are given in Table 1. The modal analysis was performed using mechanical APDLs solver to evaluate the accuracy of the constructed model.
Semispan AGARD 445.6 wing model.
Material property | E11 | E22 | E33 | G | υ | ρ |
---|---|---|---|---|---|---|
Value | 3.151 | 0.416 | 0.416 | 0.439 | 0.310 | 397.5 |
Unit | GPa | GPa | GPa | GPa | N/m2 | kg/m3 |
Mechanical properties for the weakened AGARD 445.6 wing.
The AGARD 445.6 wing was modeled at a zero attack angle and at altitudes of 9.65 and 14 km, the same conditions of experimental study in [13]. The wing was meshed in 9257 nodes and 1350 elements (Figure 3a). The fluid domain in CFD problem was meshed in 67,949 nodes and 279,535 elements (Figure 3b).
Computational grids. (a) AGARD 445.6 wing grids. (b) Fluid computational grids.
The free-stream air velocity was from 0.29 to 0.59 M at an altitude of 9.65 km and from 0.47 M to 0.73 M at an altitude of 14 km.
The mode shapes are obtained from the finite element analysis of the modeled wing. The deflection contours between the modal analysis and experiment [13] were compared as shown in Figure 4. The natural frequencies between the developed solution, experiment [13], and other researches were also compared as shown in Table 2. It could be concluded that the obtained results were in good agreement with the experimental results in [4, 6, 13] within an error relative of 8%. The frequency of the first mode was around 9.96 Hz. Following Eq. (3), the time step of the unsteady problem was estimated about 0.005 s.
Comparison of the mode shapes. (a) Mode 1. (b) Mode 2. (c) Mode 3. (d) Mode 4.
At altitude 9.65 km, the Mach number of air velocity was varied from 0.29 to 0.59 (M = 0.29; 0.35; 0.41; 0.47; 0.53; 0.59). From Eq. (4), the aerodynamic damping coefficient was calculated and presented in Figure 5a. The zero damping coefficients were interpolated at Mach number 0.46. While the experimental zero damping was 0.499 in [13], the difference between simulation results and results of [13] was about 8%.
Aerodynamic damping coefficients. (a) At altitude 9.65 km. (b) At altitude 14 km.
At altitude 14 km, the Mach numbers of air velocity were varied from 0.47 to 0.73 (M = 0.47; 0.53; 0.59; 0.65; 0.67; 0.73). From Eq. (4), the aerodynamic damping coefficient was calculated and presented in Figure 5b. The zero damping coefficients were interpolated at Mach number 0.58. While the experimental zero damping was 0.678 in [13], the difference within simulation results was about 14%.
In both the two considered altitudes (9.65 and 14 km), the numerical results agreed well with the experimental results of [13] with a relative error about 14%. This difference would be from the computation such as the quality of mesh and order of model in CFD and CSD.
For more details of the stability of the wing structure, the vibrated value of the wing tip position at three Mach numbers were plotted as shown in Figure 5.
At a Mach number smaller than the flutter value, the damping coefficient was positive, and the wing was stable (Figure 6a).
Vibration of wing at altitude H = 9.65 km. (a) M = 0.29 – ζ = 0.0071. (b) M = 0.47 – ζ = −0.000125. (c) M = 0.53 – ζ = −0.006.
At a Mach number near the flutter value, the damping coefficient was zero, and the vibration was harmonic oscillation (Figure 6b).
At a Mach number greater than the flutter value, the damping coefficient was negative, and the vibration was divergent (Figure 6c). This divergent vibration would create the damage of the wing such as loss of control for the flap, aileron, fracture of wing, etc.
Dynamic aeroelastic analysis was a problem related to fluid-structure interaction over a period of time. Therefore, the quality of aerodynamic grid and the time step strongly influenced the results of aeroelastic analysis. These parameters were also two of the most important problems in the dynamic aeroelastic analysis.
In order to evaluate the quality of aerodynamic grid, the coefficient of pressure of AGARD 445.6 wing was first estimated at 26% semispan and at 75.5% semispan and then was compared with Ref. [6] as shown in Figure 7. The presented results were in good agreement with the results in Ref. [6]. It could be concluded that these simulation settings were appropriate for solving the transonic flow.
Comparison of Cp distribution at M = 1.141, α = 0°. (a) 26 % semispan. (b) 75.5 % semispan.
To evaluate the time step size, three different time sizes were examined such as 0.001, 0.002, and 0.005 s. As it could be seen in Figure 8, the displacement of the wing tip was reduced with the reduction of time step size up to 0.002 s until the aeroelastic simulation did not change [6]. Therefore, the value 0.002 s of time step size in the numerical solution was chosen for both aerodynamic and structural analysis.
Wing-tip oscillation depends on the selected time step.
The limit of flutter was identified by using damping estimations for a large test point at each Mach number. At M = 0.499, the oscillation of the displacement of the wing tip was harmonic (Figure 9), and it was considered as a flutter point. At this limit of flutter, the air speed was calculated as 174.26 m/s, and the density of air was calculated as 0.432 kg/m3. These values were very close to the experimental values: 172.46 m/s for flutter speed and 0.428 kg/m3 for density of air (Table 3). This remark illustrated that the developed solution could be used to specify the transonic flutter characteristics with errors less than 10%.
Wing-tip oscillation of flutter point at M = 0.499.
The test model was set in AF6116 (M = 0.1) subsonic wind tunnel located at the Hanoi University of Science and Technology, which was of a blowdown type with a closed test section (0.4 × 0.5 × 1.0 m3). The wind speed could be arbitrarily varied up to 30 m/s, where the Reynolds number based on wing root chord was 106, which was driven by an 8 kW electric motor.
Flutter characteristics were determined with the help of the frequency meter and load cell, which allowed to specify the flutter frequency and root wing force, respectively. The oscillated frequency was measured by the DT-2234C+ frequency meter. The signal of measured frequency was averaged by five measurements. The force applied to the wing was measured by load cell system. In the experimental aeroelastic analysis, the flutter frequency and the flutter amplitude were measured at different velocities ranging from 10 to 30 m/s using an oscillator generator system.
Two wing models with the parameter and dimension are shown in Figure 10 and Table 4. The non-structure wing had only balsa wood, while the structure wing had balsa wood for skin and carbon rod and hard wood for the inner parts.
Experimental models. (a) Wing model. (b) Wing with support. (c). Broken wing.
Wing 1 (non-structure) | Wing 2 (with structure) | |
---|---|---|
Chord length | 300 mm | 300 mm |
Root chord length | 500 mm | 500 mm |
Tip chord length | 100 mm | 100 mm |
Profile | NACA65A004 | NACA65A004 |
Taper ratio | 0.5 | 0.5 |
Material | Balsa wood | Balsa wood, carbon rod, hard wood |
Mass | 5.1 g | 11.6 g |
Wing models.
Experimental results showed that a flutter phenomenon appeared with the non-structure wing (broken wing in Figure 10c), but this phenomenon did not happen with the structure wing model. It could be explained by the more durability of structure wing than that of the non-structure wing with the testing range of velocity. Experiments also demonstrated that the combination of multiple materials to more durability of structure of wing could be highly effective in preventing flutter phenomenon [18].
The measurement results of the non-structure wing were shown in Table 5. When the attack angle increased, the velocity of first oscillation, flutter velocity, and frequency decreased.
Attack angle (0) | Velocity of first oscillation (m/s) | Flutter velocity (m/s) | Frequency (Hz) |
---|---|---|---|
0 | 20 | 22 | 37.38 |
5 | 17.8 | 20.5 | 32.22 |
10 | 15.2 | 19.5 | 30.31 |
Flutter characteristics at different attack angles—Non-structure wing.
Figure 11 resumed the measurement of the force at the wing root in varying velocities from zero to flutter velocity and more by using the load cell system. After increasing the air velocity from zero to the limit of non-structure wing, the limit velocity of non-structure wing was found at 19.5 m/s. The load at the wing root of this wing at flutter velocity is shown in Figure 12. The maximum force was 5.44 N, and the minimum force was 4.32 N.
Force at the wing root of the non-structure wing—Attack angle 10°.
Force at the wing root of the non-structure wing—Attack angle 10° and velocity 19.5 m/s.
With structure wing, different modes of vibration appeared depending on the characteristics of the structure as remarked in [8]. With the help of the oscillator generator system, the specific oscillation frequencies of the first four modes were estimated as shown in Table 6.
Mode | Frequency (Hz) | |
---|---|---|
Non-structure wing | Structure wing | |
1 | 24.3 | 23.5 |
2 | 67.0 | 63.0 |
3 | 103.6 | 115.3 |
4 | 132.0 | 139.0 |
Specific oscillation frequency of the non-structure and structure wings.
The frequencies of the first and second modes of the non-structure wing were higher than those of the structure wing, while the frequencies of third and fourth mode of structure wing were higher than those of non-structure wing (Table 6). Considering both wings in the first mode of oscillation, when the force was applied to the wing, the amplitude of the non-structure wing was higher than that of the structure wing (Figure 13). In conclusion, the non-structure wing was easier to resonate than the structure wing.
Amplitude of oscillation of the structure wing—Mode 1.
Fluid flow and deformation of structure were governed by the following equations with assumption of linear elastic structure [11]:
where:
u: fluid velocity vector
p: fluid pressure
f: force that affected on wing
Re: Reynolds number
Uc: displacement velocity
ωp: angular velocity
xc: center of gravity
θp: rotation of wing r
mp: mass of wing
Ip: inertial moment of wing
F: force created by fluid passing through the wing
T: moment created by fluid passing through the wing
To solve out these equations using IBM method, the most important was that the velocity of fluid at fluid-solid interface was equal to the velocity of the wing. It means that the interaction force (f) between the wing and fluid was calculated such that the boundary condition of fluid was satisfied on the surface of the wing.
IBM method used the Cartesian grid and immersed boundary that were illustrated in Figure 14, in which the moving surface of wing was described by Lagrangian points (rounded points) and fixed points in fluid were called Eulerian points. Parameters of Lagrangian points were noted as capitalization.
Cartesian grid and immersed boundary.
Discrete partial derivative of velocity over time in Eq. (5) with denote intermediate velocity at zero force of Lagrangian point, Ûk, force F of Lagrangian points were estimated as follows:
where:
k: time step.
Uk+1: identified from the moving surface of wing, so this velocity was known as U(b).
Force was created from displacement and affected on the fluid element. Force was calculated using the following interpolation formula:
where:
x: coordinate of Eulerian point.
N: set of Lagrangian points round Eulerian point
x
∆U
δh: 3D delta function identified as follows:
Three-step Runge–Kutta method was applied to solve Navier-Stokes equations and Newton equations as follows:
Step 1: Calculate the instantaneous velocity at Eulerian points with no immersed boundary surface, i.e., f = 0:
where:
k: step calculation of Runge-Kutta method (k = 1, 2, 3)
αk: coefficient of kth step calculation
γk: coefficient of kth step calculation
ζk: coefficient of kth step calculation
υ: kinematic viscosity
Apply this instantaneous velocity to calculate Lagrangian velocity on the surface of the wing:
This Lagrangian velocity was combined with wing velocity, U(b)x
Step 2: Solve out Navier-Stokes Eqs. (5) using calculated forces of Eulerian points to estimate the effect of flutter of the wing into the velocity field around the wing:
To satisfy the continuity equation, a temporary pressure was described:
Step 3: Solve Eq. (17), and calculate velocity and pressure at kth step of the Runge-Kutta method:
From the estimated forces at Lagrangian points, translational and angular movements of the wing were carried out by solving Eqs. (7) and (9):
After calculating the velocity of center of gravity (Uck) and angular velocity of wing (ωpk), coordinates of Lagrangian points were estimated by the same expressions.
Four different wing models were carried out in order to analyze the effect of the wing structure. There were two rectangular and two trapezoid 3D-shape wings, and each 3D-shape wing had symmetric (NACA65A004) and asymmetric (supercritical) airfoil, respectively. The wings had the same area of 450 cm2 and the same semispan-wise length of 30 cm. Therefore, the rectangular wing had a chord length of 7.5 cm, while the trapezoidal wing has no sweep angle, and the leading edge line had a tip chord length of 5 cm and root chord length of 10 cm. The wings were made of aluminum (Figure 15).
Wing models. (a) Rectangular wing. (b) Trapezoidal wing.
Experiments were performed using a low-speed blowdown wind tunnel, which belongs to the Department of Aerospace Engineering at the Hanoi University of Science and Technology, Vietnam. This wind tunnel had a maximum free-stream velocity in empty test section of 30 m/s that corresponded to Reynolds number 106. The wind tunnel was operated continuously by an 8 kW electric motor. The turbulence level in test section was slightly less than 1%. Free-stream velocity was kept constant in test section within ±2%. Total pressure of free-stream and dynamic pressures were measured by pitot tube within ±2%. Ambient temperature was measured within ±1%. Both experimental and numerical researches were performed at air velocity of 20 m/s and attack angle of 5°.
For the experimental study, 160 pressure taps were applied on the wing model (Figure 15). These pressure taps were connected to an external digital manometer via stainless and silicon tubes. Each pressure tap was measured one time with waiting time of 5 s (average of about 1000 instant values) using the Keyence pressure measurement. The standard deviation of the Keyence pressure measurement errors was within ±0.001 Pa. Moreover, flutter of wing was captured with help of high performance camera.
The results of IBM method were analyzed at three different instants (Figure 16):
Time T0: initial time when distortion did not occurred
Time T1: time between maximum deformation and non-deformation
Time T2: time of maximum distortion
Instant displacement of wings. (a) NACA65A004 – Rectangular wing. (b) NACA65A004 – Trapezoidal wing. (c) Supercritical – Rectangular wing. (d) Supercritical – Trapezoidal wing.
The wing deformation was maximum at the tip of the wing and decreased gradually into the root of the wing over time. However, the normal stress was found to have an opposite tendency in comparison with deformation. The maximum normal stress was observed at the root of the wing, while the minimum normal stress was found at the tip of the wing (Figures 17 and 18). It could be explained by the fixed support with fuselage at the root of the wing and free support at the tip of the wing [13]. These remarks were in well agreement with the experimental results within a relative error less than 10% (Table 7).
Instant normal stress—Rectangular wing.
Instant normal stress—Trapezoidal wing.
Wing | IBM method (mm) | Experiment method (mm) | Relative error (%) |
---|---|---|---|
NACA65A004-rectangular | 0.119 | 0.131 | 9.7 |
NACA65A004-trapezoidal | 0.030 | 0.033 | 8.6 |
Supercritical-rectangular | 0.035 | 0.039 | 9.9 |
Supercritical-trapezoidal | 0.034 | 0.037 | 9.2 |
Maximum deformation of the wing tip.
At T0 instant, the normal stress had important value near the wing tip. During flutter behaviors of wing, this important normal stress propagated from the tip of the wing to the root of the wing. The maximum value of the normal stress was found out at the root of the wing and at T2 instant.
With the same airfoil, the rectangular wing was found to be more distorted and have higher maximum deformation and higher maximum normal stress than the trapezoid wing. Thus, 3D-shape wing contributed significantly to the deformation of wing when aeroelasticity phenomenon occurred (Table 7).
With the same 3D-shape wing, the maximum deformation and maximum normal stress of NACA65A004 rectangular wing were higher than those of the rectangle supercritical wing. Meanwhile, the maximum deformation and maximum normal stress of NACA65A004 trapezoidal wing were less than those of the supercritical trapezoidal wing. It could be concluded that the 3D shape of wing played an important role in the durability of the structure (Table 7).
The flutter phenomenon of AGARD 445.6 wing was determined by (a) a modal approach for a structural response; (b) an aerodynamic damping coefficient to predict the appearance of flutter phenomenon; (c) a strongly coupled FSI method to predict the aeroelastic response for subsonic and transonic flutter characteristics; (d) an experiment method to predict the aeroelastic response for subsonic flutter characteristics with wing structure; (e) and an IBM method to improve the interface between the fluid and solid of aircraft wing.
In brief, the major results could be summarized as follows:
Experimental results were in good agreement with numerical results within a relative error less than 10%.
During aeroelasticity phenomenon, deformation of the wing tip was maximum while it was minimum at the wing root. The tendency of normal stress was in contrast with deformation. The minimum normal stress was observed at the wing tip, while the maximum normal stress was observed at the wing root;
Geometry of wing (3D shape, airfoil) had a significantly contribution to the deformation of wing when aeroelasticity phenomenon occurred.
For further research of aeroelasticity in the future, both experimental and numerical researches at low and high speed should be performed.
A part of this work was supported by the Ministry of Science and Technology in Vietnam through the bilateral and multilateral research project HNQT/SPĐP/12.19.
structural displacement at any time instant and position
generalized displacement vector
generalized mass matrice
damping matrice
stiffness matrices
normal modes of the structure
total number of modes of the structure
generalized force vector
ith peak of vibration
number of period
aerodynamic damping coefficient
Mach number
fluid velocity vector
fluid pressure
force that affected on wing
Reynolds number
displacement velocity
angular velocity
center of gravity
rotation of wing
mass of wing
inertial moment of wing
force that created by fluid go pass through the wing
moment that created by fluid go pass through the wing
coordinate of Eulerian point
set of Lagrangian points round Eulerian point
coordinate of Lagrangian point
volume of effect corresponded to Lagrangian point
3D delta function
coefficient of step Runge-Kutta calculation
kinematic viscosity
normal stress following x-coordinates
normal stress following y-coordinates
normal stress following z-coordinates
shear stress
density
coefficient of pressure
attack angle
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\n\n\r\n\tThis series will provide a comprehensive overview of recent research trends in business and management, economics, and marketing. Topics will include asset liability management, financial consequences of the financial crisis and covid-19, financial accounting, mergers and acquisitions, management accounting, SMEs, financial markets, corporate finance and governance, managerial technology and innovation, resource management and sustainable development, social entrepreneurship, corporate responsibility, ethics and accountability, microeconomics, labour economics, macroeconomics, public economics, financial economics, econometrics, direct marketing, creative marketing, internet marketing, market planning and forecasting, brand management, market segmentation and targeting and other topics under business and management. This book series will focus on various aspects of business and management whose in-depth understanding is critical for business and company management to function effectively during this uncertain time of financial crisis, Covid-19 pandemic, and military activity in Europe.
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Saxena",profilePictureURL:"https://s3.us-east-1.amazonaws.com/intech-files/0030O00002bRET3QAO/Profile_Picture_2022-05-10T10:10:26.jpeg",institutionString:"King George's Medical University",institution:{name:"King George's Medical University",institutionURL:null,country:{name:"India"}}}],equalEditorOne:null,equalEditorTwo:null,equalEditorThree:null}]},subseriesFiltersForPublishedBooks:[{group:"subseries",caption:"Bacterial Infectious Diseases",value:3,count:2},{group:"subseries",caption:"Parasitic Infectious Diseases",value:5,count:4},{group:"subseries",caption:"Viral Infectious Diseases",value:6,count:7}],publicationYearFilters:[{group:"publicationYear",caption:"2022",value:2022,count:2},{group:"publicationYear",caption:"2021",value:2021,count:4},{group:"publicationYear",caption:"2020",value:2020,count:3},{group:"publicationYear",caption:"2019",value:2019,count:3},{group:"publicationYear",caption:"2018",value:2018,count:1}],authors:{paginationCount:229,paginationItems:[{id:"318170",title:"Dr.",name:"Aneesa",middleName:null,surname:"Moolla",slug:"aneesa-moolla",fullName:"Aneesa Moolla",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/318170/images/system/318170.png",biography:"Dr. Aneesa Moolla has extensive experience in the diverse fields of health care having previously worked in dental private practice, at the Red Cross Flying Doctors association, and in healthcare corporate settings. She is now a lecturer at the University of Witwatersrand, South Africa, and a principal researcher at the Health Economics and Epidemiology Research Office (HE2RO), South Africa. Dr. Moolla holds a Ph.D. in Psychology with her research being focused on mental health and resilience. In her professional work capacity, her research has further expanded into the fields of early childhood development, mental health, the HIV and TB care cascades, as well as COVID. She is also a UNESCO-trained International Bioethics Facilitator.",institutionString:"University of the Witwatersrand",institution:{name:"University of the Witwatersrand",country:{name:"South Africa"}}},{id:"419588",title:"Ph.D.",name:"Sergio",middleName:"Alexandre",surname:"Gehrke",slug:"sergio-gehrke",fullName:"Sergio Gehrke",position:null,profilePictureURL:"https://s3.us-east-1.amazonaws.com/intech-files/0033Y000038WgMKQA0/Profile_Picture_2022-06-02T11:44:20.jpg",biography:"Dr. Sergio Alexandre Gehrke is a doctorate holder in two fields. The first is a Ph.D. in Cellular and Molecular Biology from the Pontificia Catholic University, Porto Alegre, Brazil, in 2010 and the other is an International Ph.D. in Bioengineering from the Universidad Miguel Hernandez, Elche/Alicante, Spain, obtained in 2020. In 2018, he completed a postdoctoral fellowship in Materials Engineering in the NUCLEMAT of the Pontificia Catholic University, Porto Alegre, Brazil. He is currently the Director of the Postgraduate Program in Implantology of the Bioface/UCAM/PgO (Montevideo, Uruguay), Director of the Cathedra of Biotechnology of the Catholic University of Murcia (Murcia, Spain), an Extraordinary Full Professor of the Catholic University of Murcia (Murcia, Spain) as well as the Director of the private center of research Biotecnos – Technology and Science (Montevideo, Uruguay). Applied biomaterials, cellular and molecular biology, and dental implants are among his research interests. He has published several original papers in renowned journals. In addition, he is also a Collaborating Professor in several Postgraduate programs at different universities all over the world.",institutionString:null,institution:{name:"Universidad Católica San Antonio de Murcia",country:{name:"Spain"}}},{id:"342152",title:"Dr.",name:"Santo",middleName:null,surname:"Grace Umesh",slug:"santo-grace-umesh",fullName:"Santo Grace Umesh",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/342152/images/16311_n.jpg",biography:null,institutionString:null,institution:{name:"SRM Dental College",country:{name:"India"}}},{id:"333647",title:"Dr.",name:"Shreya",middleName:null,surname:"Kishore",slug:"shreya-kishore",fullName:"Shreya Kishore",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/333647/images/14701_n.jpg",biography:"Dr. Shreya Kishore completed her Bachelor in Dental Surgery in Chettinad Dental College and Research Institute, Chennai, and her Master of Dental Surgery (Orthodontics) in Saveetha Dental College, Chennai. She is also Invisalign certified. She’s working as a Senior Lecturer in the Department of Orthodontics, SRM Dental College since November 2019. She is actively involved in teaching orthodontics to the undergraduates and the postgraduates. Her clinical research topics include new orthodontic brackets, fixed appliances and TADs. She’s published 4 articles in well renowned indexed journals and has a published patency of her own. Her private practice is currently limited to orthodontics and works as a consultant in various clinics.",institutionString:null,institution:{name:"SRM Dental College",country:{name:"India"}}},{id:"323731",title:"Prof.",name:"Deepak M.",middleName:"Macchindra",surname:"Vikhe",slug:"deepak-m.-vikhe",fullName:"Deepak M. Vikhe",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/323731/images/13613_n.jpg",biography:"Dr Deepak M.Vikhe .\n\n\t\n\tDr Deepak M.Vikhe , completed his Masters & PhD in Prosthodontics from Rural Dental College, Loni securing third rank in the Pravara Institute of Medical Sciences Deemed University. He was awarded Dr.G.C.DAS Memorial Award for Research on Implants at 39th IPS conference Dubai (U A E).He has two patents under his name. He has received Dr.Saraswati medal award for best research for implant study in 2017.He has received Fully funded scholarship to Spain ,university of Santiago de Compostela. He has completed fellowship in Implantlogy from Noble Biocare. \nHe has attended various conferences and CDE programmes and has national publications to his credit. His field of interest is in Implant supported prosthesis. Presently he is working as a associate professor in the Dept of Prosthodontics, Rural Dental College, Loni and maintains a successful private practice specialising in Implantology at Rahata.\n\nEmail: drdeepak_mvikhe@yahoo.com..................",institutionString:null,institution:{name:"Pravara Institute of Medical Sciences",country:{name:"India"}}},{id:"204110",title:"Dr.",name:"Ahmed A.",middleName:null,surname:"Madfa",slug:"ahmed-a.-madfa",fullName:"Ahmed A. Madfa",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/204110/images/system/204110.jpg",biography:"Dr. Madfa is currently Associate Professor of Endodontics at Thamar University and a visiting lecturer at Sana'a University and University of Sciences and Technology. He has more than 6 years of experience in teaching. His research interests include root canal morphology, functionally graded concept, dental biomaterials, epidemiology and dental education, biomimetic restoration, finite element analysis and endodontic regeneration. Dr. Madfa has numerous international publications, full articles, two patents, a book and a book chapter. Furthermore, he won 14 international scientific awards. Furthermore, he is involved in many academic activities ranging from editorial board member, reviewer for many international journals and postgraduate students' supervisor. Besides, I deliver many courses and training workshops at various scientific events. Dr. Madfa also regularly attends international conferences and holds administrative positions (Deputy Dean of the Faculty for Students’ & Academic Affairs and Deputy Head of Research Unit).",institutionString:"Thamar University",institution:null},{id:"210472",title:"Dr.",name:"Nermin",middleName:"Mohammed Ahmed",surname:"Yussif",slug:"nermin-yussif",fullName:"Nermin Yussif",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/210472/images/system/210472.jpg",biography:"Dr. Nermin Mohammed Ahmed Yussif is working at the Faculty of dentistry, University for October university for modern sciences and arts (MSA). Her areas of expertise include: periodontology, dental laserology, oral implantology, periodontal plastic surgeries, oral mesotherapy, nutrition, dental pharmacology. She is an editor and reviewer in numerous international journals.",institutionString:"MSA University",institution:null},{id:"204606",title:"Dr.",name:"Serdar",middleName:null,surname:"Gözler",slug:"serdar-gozler",fullName:"Serdar Gözler",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/204606/images/system/204606.jpeg",biography:"Dr. Serdar Gözler has completed his undergraduate studies at the Marmara University Faculty of Dentistry in 1978, followed by an assistantship in the Prosthesis Department of Dicle University Faculty of Dentistry. Starting his PhD work on non-resilient overdentures with Assoc. Prof. Hüsnü Yavuzyılmaz, he continued his studies with Prof. Dr. Gürbüz Öztürk of Istanbul University Faculty of Dentistry Department of Prosthodontics, this time on Gnatology. He attended training programs on occlusion, neurology, neurophysiology, EMG, radiology and biostatistics. In 1982, he presented his PhD thesis \\Gerber and Lauritzen Occlusion Analysis Techniques: Diagnosis Values,\\ at Istanbul University School of Dentistry, Department of Prosthodontics. As he was also working with Prof. Senih Çalıkkocaoğlu on The Physiology of Chewing at the same time, Gözler has written a chapter in Çalıkkocaoğlu\\'s book \\Complete Prostheses\\ entitled \\The Place of Neuromuscular Mechanism in Prosthetic Dentistry.\\ The book was published five times since by the Istanbul University Publications. Having presented in various conferences about occlusion analysis until 1998, Dr. Gözler has also decided to use the T-Scan II occlusion analysis method. Having been personally trained by Dr. Robert Kerstein on this method, Dr. Gözler has been lecturing on the T-Scan Occlusion Analysis Method in conferences both in Turkey and abroad. Dr. Gözler has various articles and presentations on Digital Occlusion Analysis methods. He is now Head of the TMD Clinic at Prosthodontic Department of Faculty of Dentistry , Istanbul Aydın University , Turkey.",institutionString:"Istanbul Aydin University",institution:{name:"Istanbul Aydın University",country:{name:"Turkey"}}},{id:"240870",title:"Ph.D.",name:"Alaa Eddin Omar",middleName:null,surname:"Al Ostwani",slug:"alaa-eddin-omar-al-ostwani",fullName:"Alaa Eddin Omar Al Ostwani",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/240870/images/system/240870.jpeg",biography:"Dr. Al Ostwani Alaa Eddin Omar received his Master in dentistry from Damascus University in 2010, and his Ph.D. in Pediatric Dentistry from Damascus University in 2014. Dr. Al Ostwani is an assistant professor and faculty member at IUST University since 2014. \nDuring his academic experience, he has received several awards including the scientific research award from the Union of Arab Universities, the Syrian gold medal and the international gold medal for invention and creativity. Dr. Al Ostwani is a Member of the International Association of Dental Traumatology and the Syrian Society for Research and Preventive Dentistry since 2017. He is also a Member of the Reviewer Board of International Journal of Dental Medicine (IJDM), and the Indian Journal of Conservative and Endodontics since 2016.",institutionString:"International University for Science and Technology.",institution:{name:"Islamic University of Science and Technology",country:{name:"India"}}},{id:"42847",title:"Dr.",name:"Belma",middleName:null,surname:"Işik Aslan",slug:"belma-isik-aslan",fullName:"Belma Işik Aslan",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/42847/images/system/42847.jpg",biography:"Dr. Belma IşIk Aslan was born in 1976 in Ankara-TURKEY. After graduating from TED Ankara College in 1994, she attended to Gazi University, Faculty of Dentistry in Ankara. She completed her PhD in orthodontic education at Gazi University between 1999-2005. Dr. Işık Aslan stayed at the Providence Hospital Craniofacial Institude and Reconstructive Surgery in Michigan, USA for three months as an observer. She worked as a specialist doctor at Gazi University, Dentistry Faculty, Department of Orthodontics between 2005-2014. She was appointed as associate professor in January, 2014 and as professor in 2021. Dr. Işık Aslan still works as an instructor at the same faculty. She has published a total of 35 articles, 10 book chapters, 39 conference proceedings both internationally and nationally. Also she was the academic editor of the international book 'Current Advances in Orthodontics'. She is a member of the Turkish Orthodontic Society and Turkish Cleft Lip and Palate Society. She is married and has 2 children. Her knowledge of English is at an advanced level.",institutionString:"Gazi University Dentistry Faculty Department of Orthodontics",institution:null},{id:"178412",title:"Associate Prof.",name:"Guhan",middleName:null,surname:"Dergin",slug:"guhan-dergin",fullName:"Guhan Dergin",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/178412/images/6954_n.jpg",biography:"Assoc. Prof. Dr. Gühan Dergin was born in 1973 in Izmit. He graduated from Marmara University Faculty of Dentistry in 1999. He completed his specialty of OMFS surgery in Marmara University Faculty of Dentistry and obtained his PhD degree in 2006. In 2005, he was invited as a visiting doctor in the Oral and Maxillofacial Surgery Department of the University of North Carolina, USA, where he went on a scholarship. Dr. Dergin still continues his academic career as an associate professor in Marmara University Faculty of Dentistry. He has many articles in international and national scientific journals and chapters in books.",institutionString:null,institution:{name:"Marmara University",country:{name:"Turkey"}}},{id:"178414",title:"Prof.",name:"Yusuf",middleName:null,surname:"Emes",slug:"yusuf-emes",fullName:"Yusuf Emes",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/178414/images/6953_n.jpg",biography:"Born in Istanbul in 1974, Dr. Emes graduated from Istanbul University Faculty of Dentistry in 1997 and completed his PhD degree in Istanbul University faculty of Dentistry Department of Oral and Maxillofacial Surgery in 2005. He has papers published in international and national scientific journals, including research articles on implantology, oroantral fistulas, odontogenic cysts, and temporomandibular disorders. Dr. Emes is currently working as a full-time academic staff in Istanbul University faculty of Dentistry Department of Oral and Maxillofacial Surgery.",institutionString:null,institution:{name:"Istanbul University",country:{name:"Turkey"}}},{id:"192229",title:"Ph.D.",name:"Ana Luiza",middleName:null,surname:"De Carvalho Felippini",slug:"ana-luiza-de-carvalho-felippini",fullName:"Ana Luiza De Carvalho Felippini",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/192229/images/system/192229.jpg",biography:null,institutionString:"University of São Paulo",institution:{name:"University of Sao Paulo",country:{name:"Brazil"}}},{id:"256851",title:"Prof.",name:"Ayşe",middleName:null,surname:"Gülşen",slug:"ayse-gulsen",fullName:"Ayşe Gülşen",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/256851/images/9696_n.jpg",biography:"Dr. Ayşe Gülşen graduated in 1990 from Faculty of Dentistry, University of Ankara and did a postgraduate program at University of Gazi. \nShe worked as an observer and research assistant in Craniofacial Surgery Departments in New York, Providence Hospital in Michigan and Chang Gung Memorial Hospital in Taiwan. \nShe works as Craniofacial Orthodontist in Department of Aesthetic, Plastic and Reconstructive Surgery, Faculty of Medicine, University of Gazi, Ankara Turkey since 2004.",institutionString:"Univeristy of Gazi",institution:null},{id:"255366",title:"Prof.",name:"Tosun",middleName:null,surname:"Tosun",slug:"tosun-tosun",fullName:"Tosun Tosun",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/255366/images/7347_n.jpg",biography:"Graduated at the Faculty of Dentistry, University of Istanbul, Turkey in 1989;\nVisitor Assistant at the University of Padua, Italy and Branemark Osseointegration Center of Treviso, Italy between 1993-94;\nPhD thesis on oral implantology in University of Istanbul and was awarded the academic title “Dr.med.dent.”, 1997;\nHe was awarded the academic title “Doç.Dr.” (Associated Professor) in 2003;\nProficiency in Botulinum Toxin Applications, Reading-UK in 2009;\nMastership, RWTH Certificate in Laser Therapy in Dentistry, AALZ-Aachen University, Germany 2009-11;\nMaster of Science (MSc) in Laser Dentistry, University of Genoa, Italy 2013-14.\n\nDr.Tosun worked as Research Assistant in the Department of Oral Implantology, Faculty of Dentistry, University of Istanbul between 1990-2002. \nHe worked part-time as Consultant surgeon in Harvard Medical International Hospitals and John Hopkins Medicine, Istanbul between years 2007-09.\u2028He was contract Professor in the Department of Surgical and Diagnostic Sciences (DI.S.C.), Medical School, University of Genova, Italy between years 2011-16. \nSince 2015 he is visiting Professor at Medical School, University of Plovdiv, Bulgaria. \nCurrently he is Associated Prof.Dr. at the Dental School, Oral Surgery Dept., Istanbul Aydin University and since 2003 he works in his own private clinic in Istanbul, Turkey.\u2028\nDr.Tosun is reviewer in journal ‘Laser in Medical Sciences’, reviewer in journal ‘Folia Medica\\', a Fellow of the International Team for Implantology, Clinical Lecturer of DGZI German Association of Oral Implantology, Expert Lecturer of Laser&Health Academy, Country Representative of World Federation for Laser Dentistry, member of European Federation of Periodontology, member of Academy of Laser Dentistry. Dr.Tosun presents papers in international and national congresses and has scientific publications in international and national journals. He speaks english, spanish, italian and french.",institutionString:null,institution:{name:"Istanbul Aydın University",country:{name:"Turkey"}}},{id:"171887",title:"Prof.",name:"Zühre",middleName:null,surname:"Akarslan",slug:"zuhre-akarslan",fullName:"Zühre Akarslan",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/171887/images/system/171887.jpg",biography:"Zühre Akarslan was born in 1977 in Cyprus. She graduated from Gazi University Faculty of Dentistry, Ankara, Turkey in 2000. \r\nLater she received her Ph.D. degree from the Oral Diagnosis and Radiology Department; which was recently renamed as Oral and Dentomaxillofacial Radiology, from the same university. \r\nShe is working as a full-time Associate Professor and is a lecturer and an academic researcher. \r\nHer expertise areas are dental caries, cancer, dental fear and anxiety, gag reflex in dentistry, oral medicine, and dentomaxillofacial radiology.",institutionString:"Gazi University",institution:{name:"Gazi University",country:{name:"Turkey"}}},{id:"256417",title:"Associate Prof.",name:"Sanaz",middleName:null,surname:"Sadry",slug:"sanaz-sadry",fullName:"Sanaz Sadry",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/256417/images/8106_n.jpg",biography:null,institutionString:null,institution:null},{id:"272237",title:"Dr.",name:"Pinar",middleName:"Kiymet",surname:"Karataban",slug:"pinar-karataban",fullName:"Pinar Karataban",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/272237/images/8911_n.png",biography:"Assist.Prof.Dr.Pınar Kıymet Karataban, DDS PhD \n\nDr.Pınar Kıymet Karataban was born in Istanbul in 1975. 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Her main interests are paleodontology, ancient and contemporary dentistry, oral microbiology, cerebral palsy and special care dentistry. She has national and international publications, scientific reports and is a member of IAPO (International Association for Paleodontology), IADH (International Association of Disability and Oral Health) and EAPD (European Association of Pediatric Dentistry).",institutionString:null,institution:null},{id:"202198",title:"Dr.",name:"Buket",middleName:null,surname:"Aybar",slug:"buket-aybar",fullName:"Buket Aybar",position:null,profilePictureURL:"https://mts.intechopen.com/storage/users/202198/images/6955_n.jpg",biography:"Buket Aybar, DDS, PhD, was born in 1971. 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