Computational study of wing deformation and sting interference effects with the CAE-AVM test case  

作　　者：Innokentiy KURSAKOV Egor KAZHAN Roy GEBBINK 

机构地区：[1]Central Aerohydrodynamic Institute Named After Professor N.E.Zhukovsky(TsAGI),Zhukovskiy 140180,Russia [2]German-Dutch Wind Tunnels(DNW),Marknesse 8316 PR,The Netherlands

出　　处：《Chinese Journal of Aeronautics》2018年第10期1954-1961,共8页中国航空学报（英文版）

基　　金：supported by the Grant Agreement(No.4.628.21.0004)with the Ministry of Education and Science of the Russian Federation(project unique identifier RFMEFI62815X0004)on the theme‘‘Development and implementation of the optimization of the aircraft power plant aerodynamics as a part of a 3rd generation multidisciplinary optimization and its application to optimization of promising new types of aircraft”

摘　　要：A modern transonic computational fluid dynamics test case is described in this paper,which is the Aerodynamic Validation Model（AVM） from the Chinese Aeronautical Establishment（CAE）. The CAE-AVM is a representation of a modern transonic business jet aircraft with a design Mach number of 0.85. Numerical simulations for the AVM are conducted for two geometries： one baseline geometry, and one geometry that includes the applied model support system of the wind tunnel as well as the deformed wing shape that occurred during wind tunnel testing. The combined influence of wing deformation and model support interference on local and integral aerodynamic features is presented. Comparisons between CFD and experimental results are made; reasons of discrepancy between results from considered cases are analyzed.A modern transonic computational fluid dynamics test case is described in this paper,which is the Aerodynamic Validation Model（AVM） from the Chinese Aeronautical Establishment（CAE）. The CAE-AVM is a representation of a modern transonic business jet aircraft with a design Mach number of 0.85. Numerical simulations for the AVM are conducted for two geometries： one baseline geometry, and one geometry that includes the applied model support system of the wind tunnel as well as the deformed wing shape that occurred during wind tunnel testing. The combined influence of wing deformation and model support interference on local and integral aerodynamic features is presented. Comparisons between CFD and experimental results are made; reasons of discrepancy between results from considered cases are analyzed.

关 键 词：Aerodynamic validation model CFD Sting interference Transonic test Wing deformation 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]