三角翼大迎角风洞试验支架干扰数值模拟研究

doi:10.7527/S1000-6893.2016.0095

Abstract

Abstract:

In current wars, the fighter is required to be capable of stalled flight at a high angle of attack (AOA). The investigation of the aerodynamic characteristics of the aircraft mainly relies on wind tunnel test and numerical simulation. In the wind tunnel test of high angle of attack, the commonly used method is to use sting support. The presence of the sting support can have an effect on the model testing results which will be numerically investigated in the present paper. The open source software package OpenFOAM 2.3 is used as computational fluid dynamics (CFD) computing platform, the PIMPLE algorithm is applied to solving Navier-Stokes (N-S) equations. The PIMPLE algorithm is a combination of both semi-implicit method for pressure-linked equations (SIMPLE) and pressure implicit with splitting of operator (PISO). A finite volume method is used for spatial discretization. Second order linear interpolation is also adopted. Backward differentiation method is to deal with time discretization. The employed turbulence model is Spalart-Allmaras-delayed detached eddy simulation (SA-DDES). In order to verify the reliability of the numerical method, the flow filed of the delta wing with sting support is computed at angles of attack of 0°, 10°, 30°, 50°, 70°, and 90° firstly. The obtained results are compared to the testing data and they are in close agreement. After that, the numerical simulation of the flow field of the delta wing without sting support is executed. The influence of the sting support on the flow filed, pressure coefficient distribution on the leeward side and aerodynamic coefficient is obtained through comparing the numerical results with and without sting support. In contrast to the situation without the sting support, at a high angle of attack, the presence of the sting support affects the flow field around the delta wing (but does not change the vortices and flow structure) and alters the pressure coefficient distribution on the wing leeward side. Therefore, normal force and pitching moment coefficients have significant changes.

Key words: high angle of attack, delta wing, unsteady flow field, OpenFOAM, SA-DDES, large eddy simulation

CLC Number:

V211.3

ZHANG Jun, AI Yu, HUANG Da, LIU Jing. Numerical simulation investigation of aerodynamic interference of sting support in wind tunnel test of a delta wing at big angles of attack[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(8): 2481-2489.

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Numerical simulation investigation of aerodynamic interference of sting support in wind tunnel test of a delta wing at big angles of attack

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