新型人工转捩技术及风洞试验验证

doi:10.7527/S1000-6893.2014.0284

Abstract

Abstract:

An innovative artificial transition technique of distributed roughness elements is designed aimed at solving the problems encountered in fixed artificial transition tests with traditional methods in transonic wind tunnel. The shape, height and arrangement of the roughness elements and the design schemes for different configurations of models are determined by theoretical analysis. Meanwhile, the pressure coefficient on an airfoil surface (NACA0012) and the aerodynamic coefficients on an airplane model (GMB-01, or AGARD-B calibration model) are measured in the tests of artificial fixed transition. Sublimation flow visualization technique is used to judge or identify transition. The differences between natural free transition and artificial fixed transition are analyzed. The effectiveness of the innovative artificial transition technique is observed and analyzed. The results show that this kind of innovative artificial transition technique can trigger boundary layer transition from laminar to turbulent and is able to obtain aerodynamic results comparable to those at the high Reynolds number atmospheric flight conditions.

Key words: transonic aerodynamics, transonic wind tunnel, artificial transition, roughness elements, sublimation method, boundary layer

CLC Number:

V211.7

ZHAO Zijie, GAO Chao, ZHANG Zhengke. An innovative artificial transition technique and its validation through wind tunnel tests[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(6): 1830-1838.

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An innovative artificial transition technique and its validation through wind tunnel tests

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