摘要
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。
An experimental investigation of pressure distribution characteristics of wings of ×× missile was conducted under the conditions of M =1.2～3.0, α =8°～30°, =0° and -45°.It is shown that:the pressure distribution on the wing surfaces is characterized by the cone flow under test conditions; the pressure on the leeward surfaces is almost approximate to theoretical limitation value, furthermore, the higher the Mach number, the smaller the difference between them; the rolling angles have considerable influence on the pressure distribution on the wings and the normal loads of the chord profiles; for a given angle of attack, the pressure coefficients in some area of the windward surfaces increase gradually with the increase of the Mach number at =-45° due to the non-linear compressibility influence of the body on the wings.
出处
《流体力学实验与测量》
CSCD
北大核心
2001年第3期43-47,共5页
Experiments and Measurements in Fluid Mechanics
