| 航天飞机高超音速大攻角气动力工程估算方法 |
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| 引用本文： | 秦伊贤.航天飞机高超音速大攻角气动力工程估算方法[J].实验流体力学,1989(1). |
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| 作者姓名： | 秦伊贤 |
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| 作者单位： | 北京空气动力学研究所 |
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| 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。
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| 关 键 词： | 航天飞机 高超音速 大攻角工程估算 |
AN ENGINEERING ESTIMATION OF AERODYNAMIC FORCES ON A SPACE-SHUTTLE-LIKE CONFIGURATION AT HYPERSONIC SPEEDS AND HIGH ANGLES OF ATTACK |
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| Qin Yixian.AN ENGINEERING ESTIMATION OF AERODYNAMIC FORCES ON A SPACE-SHUTTLE-LIKE CONFIGURATION AT HYPERSONIC SPEEDS AND HIGH ANGLES OF ATTACK[J].Experiments and Measur in Fluid Mechanics,1989(1). |
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| Authors: | Qin Yixian |
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| Institution: | Beijing Institute of Aerodynamics |
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| Abstract: | 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. |
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| Keywords: | space shuttle hypersonic speed high angle of attack |
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