摘要
本文给出了航天飞机轨道器在无粘、无侧滑和不偏舵情况下再入飞行高超音速大攻角气动力计算方法。对复杂的航天飞机外形,本文提出用三角形有限表面面元法来逼近,克服了已有方法中采用平面梯形面元逼近后近似外形有裂缝,有台阶等不连续的缺陷,其结果与实验结果吻合较好,从而证明用三角形表面面元法更为合理。
This paper presents a method to calculate aerodynamicforces of a re-entry space shuttle orbiter in hypersonic inviscid flowswith zero side-slip angle,zero flap deflection and high angles of att-ack.A triangular finite surface panel method is used to approximatethe complex shuttle configuration,hence discontinuity defects shch asgaps and steps in the planar trapezoid panel approximation are elimi-nated.The results are in good agreement with experimental results,which proves that using triangular surface panel is more appropriate.
关键词
航天飞机
高超音速
大攻角工程
space shuttle
hypersonic speed
high angle of attack
