电弧风洞内三维翼冷壁热流测量的归一化研究  

Normalization Study on Cold-wall Heat Flux Measurement of Three Dimension Wings in Arc Wind Tunnel

作　　者：许考[1] 陈连忠[1] 董永晖[1] 张友华[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《导弹与航天运载技术》2014年第1期17-20,共4页Missiles and Space Vehicles

摘　　要：通过实验并结合工程算法研究电弧风洞内翼前缘、翼面及翼轴上的冷壁热流密度在不同来流总焓或相同来流总焓条件下的变化规律。结果表明:对于相同测试件和相同喷管来说,无论来流总焓变化与否,前缘及翼面上某固定点的冷壁热流密度基本上呈同步变化;当来流总焓不变时,翼面上同一测点热流密度与前缘上与其在同一平面内测点热流密度比值基本不变,该平面垂直于前缘中心线;当来流总焓变化时,两比值轻微变化,但幅度较小,而翼的底部缝隙内的轴上热流密度与前缘热流密度比值变化幅度较大。利用上述结果,由翼前缘上热流密度可推算出翼面的热流密度,反之亦然。The variation rules of the cold-wall heat flux on the leading edge, the surface and the axis of some wing when the total flow enthalpy was uniform or different were respectively studied by experiments combined with engineering calculation. The results showed that, for the same test article and the same nozzle, the cold-wall heat flux on the leading edges and the surface of some wing varied synchronously regardless of the varying condition of the flow enthalpy; the ratio of the cold-wall heat flux on the wing surface to that on the leading edge kept invariable when the flow enthalpy was constant; and when the total flow enthalpy changed, that ratio varied slightly, but the ratio of the cold-wall heat flux on the axial of the wing to that on the leading edge varied largely. The testing positions of heat flux on the surface and the leading edge of the wing were in the same plane which was perpendicular to the central line of the leading edge. According to the conclusion above, the cold-wall heat flux on the wing surface could be reckoned from the cold-wall heat flux on the leading edge and vice versa.

关 键 词：冷壁热流 归一化 翼 电弧风洞 

分 类 号：V211.1[航空宇航科学与技术—航空宇航推进理论与工程]