M. Sohail, Yan Chao, M. Afzal, Zahid Maqbool, M. Younis, S. Naidu
{"title":"Application of higher order low dissipative scheme on hypersonic flow field using a minmod limiter","authors":"M. Sohail, Yan Chao, M. Afzal, Zahid Maqbool, M. Younis, S. Naidu","doi":"10.1109/ICMET.2010.5598407","DOIUrl":null,"url":null,"abstract":"The different shapes of reentry vehicle cone with different radii and cone half angle have been studied and verified with experimental data by using higher order low dissipative scheme of Harten and Yee. A code has been generated to simulate the flow at high Mach number and shock capturing technique has been used for the location of shock waves. The patterns of shock waves and aerodynamics performance have been studied as radius or angle of cone is changed and compared with available experimental data. The developed code by using a flux difference scheme is also validated for the same. Three different geometries with tip to base radius ratios have been simulated at Mach 5.9 at a wide range of angle of attack −4°,−2, 0, 2, 4, 6, 8, 10,12°.","PeriodicalId":415118,"journal":{"name":"2010 International Conference on Mechanical and Electrical Technology","volume":"69 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"2010-10-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"1","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"2010 International Conference on Mechanical and Electrical Technology","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1109/ICMET.2010.5598407","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
The different shapes of reentry vehicle cone with different radii and cone half angle have been studied and verified with experimental data by using higher order low dissipative scheme of Harten and Yee. A code has been generated to simulate the flow at high Mach number and shock capturing technique has been used for the location of shock waves. The patterns of shock waves and aerodynamics performance have been studied as radius or angle of cone is changed and compared with available experimental data. The developed code by using a flux difference scheme is also validated for the same. Three different geometries with tip to base radius ratios have been simulated at Mach 5.9 at a wide range of angle of attack −4°,−2, 0, 2, 4, 6, 8, 10,12°.
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