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称作NSWCAP和Missile-DATCOM的两种快速的导弹空气动力学的预测程序巳经用于带制导、由火炮发射的铜头蛇导弹的外形气动计算上。通过与风洞试验和靶场自由飞试验所测得的数据进行比较对这二种程序进行了评估。计算中考虑二种状态的外形:马赫数0.5到1.8发射状态（弹体+尾翼）和马赫数0.3到0.9 5的作机动飞行状态（弹体+弹翼十尾翼）。比较结果表明:阻力系数符合得相当好,但CNα和CMα均显出较大的差异。造成这种差异的主要原因可能是计算中没有考虑弹体上的槽口和体与翼间的缝隙影响。NSWCAP对动导数Cep和（CNq+CMα）所作的预估不合适,而DATCOM程序则没有计算这一部分。然而,就实际计算的程序来说,用DATCOM程序算出的结果要比用NSWCAP程序算出的结果稍微精确一些。这二种程序都缺少有关控制而偏转对气动系数明确影响的预测值。如果这二种程序要能用于制导火箭的预测,则要增添这方面的测算内容。本文指出了这种程序中需要改善的部分。
Two fast missile aerodynamic predictive procedures, called NSWCAP and Missile-DATCOM, have been used for the aerodynamic calculations of guided copper snake missiles fired by artillery. Both procedures were evaluated by comparing the data measured with the wind tunnel test and the free-range test of the range. The calculation takes into account the appearance of two states: a maneuver state of Mach 0.5 to 1.8 (projectile + tail) and a Mach number of 0.3 to 0.9 5 (projectile + empennage). The comparison results show that the resistance coefficient is in good agreement, but both CNα and CMα show significant differences. The main reason for this difference may be calculated without considering the slot on the projectile body and the gap between the body and the wing. NSWCAP’s estimates of the moving derivatives Cep and (CNq + CMα) are not appropriate, and the DATCOM program does not calculate this part. However, for the actual calculation of the program, the results calculated using the DATCOM program are slightly more accurate than those calculated using the NSWCAP program. Both of these procedures lack the predictive value of deflections that have a clear effect on the aerodynamic coefficient with respect to control. If these two kinds of procedures should be used to guide the rocket’s forecast, we should add the contents of this measure. This article points out the parts of the program that need improvement.