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本文叙述了CK-1C靶机带堵锥风洞模型的实验数据到真实飞行情况下使用的气动力数据的计算和分析方法。主要包括Re数(含高度)修正、弹性影响、进气效应、喷流效应和模型尾支架干扰五个方面内容。在零升阻力修正中,本文把喷流效应与尾支架干扰结合起来考虑。从而,提出一个在M<1时,喷流效应对零升阻力系数受M数影响的经验修正公式. 风洞实验数据经用本文方法修正后,供给轨道计算,得出的结果与试飞结果吻合较好。一般误差在5～10％范围内,其平飞速度误差可以达到2％。
This paper describes the calculation and analysis methods of the aerodynamic data used in the real flight condition of the experimental data of the CK-1C target model with a frustoconical wind tunnel. Mainly includes the Re number (including height) correction, elastic effect, intake effect, jet effect and model tail bracket interference five aspects. In the zero-lift resistance correction, this paper considers jet effect and tailrace interference. Thus, an empirical correction formula for the effect of jet flow on the zero lift coefficient by M is proposed when M <1. The experimental data of the wind tunnel, after being corrected by this method, are supplied to the orbit calculation and the results are in good agreement with the test results better. General error in the range of 5 ~ 10%, the error rate of flat fly can reach 2%.