{"title":"基于碰撞的冲击特性控制数值分析","authors":"Dawei Li, Kaibo Yu, X. Wang, Yuan-bo Gao","doi":"10.1088/1873-7005/acbb22","DOIUrl":null,"url":null,"abstract":"The effects of bump control on shock aerodynamic characteristics have been investigated by simulations. A bump control that based on the changes of local upper surface of two-dimensional (2D) airfoil or three-dimensional (3D) wing model has been applied to affect the shock intensity and position. The simulation results are close of other experiment when the calculate parameters are same with each other. The simulations show that the drag and lift characteristics can be improved with the bump control, and the results of improvement strongly depend on control parameters. For the 2D RAE2822 airfoil, the optimal control position of the bump control must keep close to the position of the shock wave. The 3D local bump that located on 80% wing span wise and closed to the tip can acquire a batter control results for the 3D RAE2822 wing model.","PeriodicalId":56311,"journal":{"name":"Fluid Dynamics Research","volume":" ","pages":""},"PeriodicalIF":1.3000,"publicationDate":"2023-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Numerical analysis of shock characteristics control based on bump\",\"authors\":\"Dawei Li, Kaibo Yu, X. Wang, Yuan-bo Gao\",\"doi\":\"10.1088/1873-7005/acbb22\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"The effects of bump control on shock aerodynamic characteristics have been investigated by simulations. A bump control that based on the changes of local upper surface of two-dimensional (2D) airfoil or three-dimensional (3D) wing model has been applied to affect the shock intensity and position. The simulation results are close of other experiment when the calculate parameters are same with each other. The simulations show that the drag and lift characteristics can be improved with the bump control, and the results of improvement strongly depend on control parameters. For the 2D RAE2822 airfoil, the optimal control position of the bump control must keep close to the position of the shock wave. The 3D local bump that located on 80% wing span wise and closed to the tip can acquire a batter control results for the 3D RAE2822 wing model.\",\"PeriodicalId\":56311,\"journal\":{\"name\":\"Fluid Dynamics Research\",\"volume\":\" \",\"pages\":\"\"},\"PeriodicalIF\":1.3000,\"publicationDate\":\"2023-02-10\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Fluid Dynamics Research\",\"FirstCategoryId\":\"5\",\"ListUrlMain\":\"https://doi.org/10.1088/1873-7005/acbb22\",\"RegionNum\":4,\"RegionCategory\":\"工程技术\",\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"Q3\",\"JCRName\":\"MECHANICS\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Fluid Dynamics Research","FirstCategoryId":"5","ListUrlMain":"https://doi.org/10.1088/1873-7005/acbb22","RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q3","JCRName":"MECHANICS","Score":null,"Total":0}
Numerical analysis of shock characteristics control based on bump
The effects of bump control on shock aerodynamic characteristics have been investigated by simulations. A bump control that based on the changes of local upper surface of two-dimensional (2D) airfoil or three-dimensional (3D) wing model has been applied to affect the shock intensity and position. The simulation results are close of other experiment when the calculate parameters are same with each other. The simulations show that the drag and lift characteristics can be improved with the bump control, and the results of improvement strongly depend on control parameters. For the 2D RAE2822 airfoil, the optimal control position of the bump control must keep close to the position of the shock wave. The 3D local bump that located on 80% wing span wise and closed to the tip can acquire a batter control results for the 3D RAE2822 wing model.
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Fluid Dynamics Research publishes original and creative works in all fields of fluid dynamics. The scope includes theoretical, numerical and experimental studies that contribute to the fundamental understanding and/or application of fluid phenomena.
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