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...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.展开更多
For the problem of ventral support interference in a transonic-speed wind tunnel with the blended-wing-body aircraft NPU-BWB-300 installed,the numerical simula-tion method based on Reynolds-averaged Navier–Stokes(RAN...For the problem of ventral support interference in a transonic-speed wind tunnel with the blended-wing-body aircraft NPU-BWB-300 installed,the numerical simula-tion method based on Reynolds-averaged Navier–Stokes(RANS)equations is used to study the influence law of aerodynamic characteristic interference with the variation of Mach numbers and angles of attack.Moreover,the characteristics of ventral support interference for blended-wing-body aircraft and conventional aircraft are compared.The relevant mechanism of the generation and change of ventral support interfer-ence is revealed by employing analysis of the body surface pressure,the shock wave of the strut,and the separation area between the strut and the aircraft.The aerody-namic characteristic interference obtained from the numerical simulation is linearized based on the principle of the least square method.Afterward,a numerical simulation correction method of ventral support interference in the transonic-speed wind tunnel for the blended-wing-body aircraft is developed.Finally,the test results after the cor-rections of ventral support interferences in the transonic-speed wind tunnel for NPU-BWB-300 are obtained,which is significant for the evaluation of current aerodynamic performances and subsequent optimization designs.展开更多
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”
文摘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.
基金This work has benefited greatly from the support of the National Key Project of China under grant GJXM92579the Shenyang Key Laboratory of Aircraft Icing and Ice Protection.
文摘For the problem of ventral support interference in a transonic-speed wind tunnel with the blended-wing-body aircraft NPU-BWB-300 installed,the numerical simula-tion method based on Reynolds-averaged Navier–Stokes(RANS)equations is used to study the influence law of aerodynamic characteristic interference with the variation of Mach numbers and angles of attack.Moreover,the characteristics of ventral support interference for blended-wing-body aircraft and conventional aircraft are compared.The relevant mechanism of the generation and change of ventral support interfer-ence is revealed by employing analysis of the body surface pressure,the shock wave of the strut,and the separation area between the strut and the aircraft.The aerody-namic characteristic interference obtained from the numerical simulation is linearized based on the principle of the least square method.Afterward,a numerical simulation correction method of ventral support interference in the transonic-speed wind tunnel for the blended-wing-body aircraft is developed.Finally,the test results after the cor-rections of ventral support interferences in the transonic-speed wind tunnel for NPU-BWB-300 are obtained,which is significant for the evaluation of current aerodynamic performances and subsequent optimization designs.
