摘要:
通过数值方法研究了高超声速级间分离测力试验中腹支撑对一级、二级弹体气动力的干扰规律,对试验中采用的“归零”干扰扣除方法得到的修正结果进行验证。主要研究不同迎角、级间距下腹支撑干扰对一级、二级流动结构和气动力特性的影响。研究结果表明,腹支撑干扰引起腹支撑一侧喷流出射高度增加。而腹支撑干扰引起的一级轴向力干扰量相对于轴向力原始量较小,一般小于2%,基本不需要进行修正。二级轴向力腹支撑干扰量百分比在0.1D(D 为模型参考直径)级间距、2°迎角状态最小,但也达到了10%,需要考虑进行修正。0.1D 级间距时二级法向力腹支撑干扰量采用“归零”修正方法的误差最小,约为0.005,基本可以接受。法向力的“归零”修正更适合于在0.1D 级间距下一级模型上进行,一、二级模型在0.5D 级间距下均不宜采用“归零”修正方法。
Abstract:
Characteristics of the interaction between the support and the test model are inves-tigated in stage separation tests which are carried out in Φ1m hypersonic wind tunnel.The reset zero method is validated in tests.The technical content includes the interaction effects of the sup-port on aerodynamics of two stages with different attack angles and separate distances.The re-sults indicate that the jet height on the underside increases due to the support interaction.The support-induced axis force increment of the first stage is so far smaller than the original value,u-sually less than 2%,and thus there is no need for interference correction.The support-induced axis force increment of the second stage is more than 10% of the original value at different attack angles and stage separation distances so that the correction should be considered.The error between reset zero method and CFD results in the case of separate distance 0.1D(D is the refer-ence diameter of model)is about 0.005 which is lower than other case and acceptable as a whole. Numerical and test results indicate that the interference correction of the normal force based on the zero reference is appropriate for the first stage in the case of 0.1D stage separation distance, but it is not suitable in the case of 0.5D stage distance for the other stages.
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