大型客机低速构型高雷诺数风洞腹撑支架干扰数值模拟

doi:10.7527/S1000-6893.2019.23526

Abstract

Abstract: The wind tunnel to flight correlation correction is an important means to obtain the low-speed aerodynamic characteristics of modern civil aircraft. The method of increasing the wind tunnel test pressure is usually used to improve the Reynolds number, and the sting interference correction is a key part of the correction system. The numerical simulation is used to study the sting interference of the pressurized wind tunnel, and the variation of flow field and the main affected parts are analyzed. The comparison of the numerical simulation with the wind tunnel test shows that the lift coefficient differs by 0.006, the drag coefficient has a maximum difference of 0.001 2, and the pitching moment coefficient has a maximum difference of 0.01, verifying the reliability of the CFD numerical simulation method. The CFD simulation results show that the ventral sting increases the lift of the whole aircraft, reduces the drag, and increases the pitching moment. The ventral sting has a major influence on the lift of the wing. The ventral sting increases the dynamic pressure above the center of the wind tunnel and increases the flow velocity of the upper surface of the wing, thereby increasing the lift of the wing. Different from the traditional understanding, the ventral sting has a negative influence on the drag, and the main affected parts are slats because the deflection of the slats makes the normal vector part forward and reduces the drag. The main affected parts of the ventral sting on pitching moment are the fuselage and the horizontal tail. The results reveal the magnitude of the ventral sting on the aerodynamic characteristics, mainly affected parts, and the variation of flow fields. The results can provide reference for the correction of the sting interference and the optimization design of the support. The conclusion can be better used in the wind tunnel sting interference test and wind tunnel to flight data correction with certain engineering practicability.

Key words: civil aircraft, high Reynolds number, wind tunnel test, ventral sting, sting interference

CLC Number:

V211.753

WANG Jiming, GAO Yunhai, JIAO Renshan. Numerical simulation of ventral sting interference in high Reynolds number wind tunnel for civil aircraft low speed configuration[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(4): 123526-123526.

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Numerical simulation of ventral sting interference in high Reynolds number wind tunnel for civil aircraft low speed configuration

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