摘要
对非定常超音速飞行条件下尾翼片气动加热温度分布给出了一般的数值计算方法．对某翼型尾翼片在典型弹道飞行时进行了具体计算，所得结果合理．
A numerical calculation methed of the fin temperature distribution under the condition of unsteady state supersonic flight has been given in the present paper.A typical example of this calculation for a profile in a typical trajectory is established.The results of numerical calculation have shown reasonably satisfied.
出处
《弹道学报》
CSCD
1994年第4期51-56,共6页
Journal of Ballistics
关键词
温度分布
气动加热
数值计算
尾翼片
temperature distribation,aerodynamic heating,numerical calculation
