{"title":"基于边界元法的机翼几何形状对叶片涡相互作用响应的影响","authors":"T. Wood, S. Grace","doi":"10.1115/imece2001/nca-23536","DOIUrl":null,"url":null,"abstract":"\n The boundary element method provides a low-order computational model for investigating unsteady wing response. This method is applied here to investigate the effect of fixed wing geometry on the blade-vortex interaction (BVI) problem. The method has been validated using a harmonic Sears gust as well as three-dimensional BVI analytical results for thin, flat, rectangular wings. It is shown that wing taper and twist do not significantly affect the BVI response while sweep greatly reduces it.","PeriodicalId":387882,"journal":{"name":"Noise Control and Acoustics","volume":"3 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"2001-11-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"1","resultStr":"{\"title\":\"Wing Geometry Effect on Blade-Vortex Interaction Response Using BEM\",\"authors\":\"T. Wood, S. Grace\",\"doi\":\"10.1115/imece2001/nca-23536\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"\\n The boundary element method provides a low-order computational model for investigating unsteady wing response. This method is applied here to investigate the effect of fixed wing geometry on the blade-vortex interaction (BVI) problem. The method has been validated using a harmonic Sears gust as well as three-dimensional BVI analytical results for thin, flat, rectangular wings. It is shown that wing taper and twist do not significantly affect the BVI response while sweep greatly reduces it.\",\"PeriodicalId\":387882,\"journal\":{\"name\":\"Noise Control and Acoustics\",\"volume\":\"3 1\",\"pages\":\"0\"},\"PeriodicalIF\":0.0000,\"publicationDate\":\"2001-11-11\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"1\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Noise Control and Acoustics\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.1115/imece2001/nca-23536\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Noise Control and Acoustics","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1115/imece2001/nca-23536","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
Wing Geometry Effect on Blade-Vortex Interaction Response Using BEM
The boundary element method provides a low-order computational model for investigating unsteady wing response. This method is applied here to investigate the effect of fixed wing geometry on the blade-vortex interaction (BVI) problem. The method has been validated using a harmonic Sears gust as well as three-dimensional BVI analytical results for thin, flat, rectangular wings. It is shown that wing taper and twist do not significantly affect the BVI response while sweep greatly reduces it.
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