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在M =1 .2～ 3.0 ,α =8°～ 30° , =0°、- 45°的范围内 ,进行了××导弹翼面超声速大迎角压力分布特性试验研究。结果表明 :在试验条件下 ,翼面压力分布具有锥型流的特征 ;M≥ 2 .0时 ,弹翼背风面压力值在较大迎角下十分接近理论极限值 ,且M数越高越接近 ;不同弹体滚转角对弹翼压力分布及剖面法向载荷有明显影响 ;由于弹体对弹翼的非线性压缩性影响 ,在相同α下 ,随M数增加 ,弹翼迎风面压力系数在 =- 45°时的某些区域逐渐增大。
In the range of M = 1.2 ~ 3.0, α = 8 ° ~ 30 °, = 0 °, and -45 °, the experimental study on the pressure distribution characteristics of the high-angle of attack of the XX missile was carried out. The results show that under the experimental conditions, the pressure distribution of the airfoil has the characteristics of a conical flow. When M≥2.0, the pressure value of the leeward surface of the missile is very close to the theoretical limit at a larger angle of attack, and the higher the M number The angle of roll angle of different projectile has a significant effect on the pressure distribution and the normal load of the projectile. Due to the nonlinear compressibility of projectile on the projectile, under the same α, with the increase of M, The coefficient increases gradually at = - 45 °.