{"title":"Surface Pressure Measurements on a Forebody Using Pressure Sensitive Paint","authors":"K. M. Chung, Ying-Chi Huang, C. Y. Lin, Y. T. Wu","doi":"10.6125/JOAAA.202109_53(3).03","DOIUrl":null,"url":null,"abstract":"Pressure sensitive paint (PSP) gives the full-field pressure pattern on the model surface with a high spatial resolution and is an alternative to traditional pressure taps used in a wind tunnel model. This study determines surface pressure patterns on the forebody of an AGARD B model in a compressible flow and the data is in comparison with a numerical simulation using ANSYS Fluent software. The lift and drag coefficients are calculated and compared with data in literature. The experiments use a blowdown wind tunnel. The freestream Mach number is 0.83 and the angle of attack ranges from -4° to 8°. The difference between the results using PSP and the numerical simulation is less than 5%.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"54 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"2021-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"1","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"Journal of aeronautics, astronautics and aviation, Series A","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.6125/JOAAA.202109_53(3).03","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
引用次数: 1
Abstract
Pressure sensitive paint (PSP) gives the full-field pressure pattern on the model surface with a high spatial resolution and is an alternative to traditional pressure taps used in a wind tunnel model. This study determines surface pressure patterns on the forebody of an AGARD B model in a compressible flow and the data is in comparison with a numerical simulation using ANSYS Fluent software. The lift and drag coefficients are calculated and compared with data in literature. The experiments use a blowdown wind tunnel. The freestream Mach number is 0.83 and the angle of attack ranges from -4° to 8°. The difference between the results using PSP and the numerical simulation is less than 5%.
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