CK-1C靶机风洞模型实验数据的修正和使用

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％。

Correction and Use of the Test Date of Wind-Tunnel Model for the CK-lC Target

This paper gives an account of the methods of calculation together with an analyses, by which the wind-tunnel test data of the model with nose cone for the CK-1C target drone are corrected to the aerodynamic data for real flight. This work mainly includes five items, such as the correction of Reynolds number (including height effect), elasticity effect, intake effect, jet effect and sting-support interference. The correction of the zero-lift drag is carried on by taking into accunt jet together with the sting-support interference. An empirical formula is given thereby for correcting the effect of jet on the zero-lift drag for different Mach numbers at M<1.The wind-tunnel test data corrected by the methods suggested in this paper are provided for an orbit calculation and the results are in good agreement with those of flight tests. In generel, the errors of the two results mentioned above are from 5% to 10%, and the error of the level-light speed is as small as 2%.