| 尖前缘任意翼型的超音速和高超音速俯仰安定性导数 |
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| 引用本文： | 张才文,陈劲松.尖前缘任意翼型的超音速和高超音速俯仰安定性导数[J].南京航空航天大学学报,1989(2). |
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| 作者姓名： | 张才文 陈劲松 |
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| 作者单位： | 南京航空学院空气动力学系
(张才文)，南京航空学院空气动力学系(陈劲松) |
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| 摘 要： | 本文推广了文1]的欧拉方程摄动法,讨论了尖前缘任意翼型俯仰安定性导数的计算方法,并应用该方法计算了双圆弧翼型的俯仰安定性导数,其数值结果与文2]的超音速线化位流方程有限差分法的数值结果比较,更接近于实验值。在激波附体的条件下,本文的方法可用于计算大迎角尖前缘任意翼型的超音速和高超音速俯仰安定性导数。
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| 关 键 词： | 翼型 超音速 高超音速 气动导数 俯仰 摄动法 |
Pitching Stability Derivatives of Arbitrary Airfoils with Sharp Edge in Supersonic and Hypersonic Flows |
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| Zhang Caiwen Chen Jingsong.Pitching Stability Derivatives of Arbitrary Airfoils with Sharp Edge in Supersonic and Hypersonic Flows[J].Journal of Nanjing University of Aeronautics & Astronautics,1989(2). |
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| Authors: | Zhang Caiwen Chen Jingsong |
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| Institution: | Department of Aerodynamics |
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| Abstract: | In this paper, the perturbation method of Euler equations1] is extented, and the technique for calculation pitching stability derivatives of arbitrary airfoils with sharp leading edge is discussed. Using this method, we obtain the solution of pitching stability derivatives of biconvex airfoils in a supersonic/hypersonic unsteady flow. The numerical results of this paper are more close to the experimental data than that of supersonic linearized potential equation solved by finite-difference method2]. This method may be used to calculate the arbitrary airfoils with sharp leading edge provided that the shock wave is attached. |
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| Keywords: | airfoils supersonic velocity hypersonic velocity aerodynamic derivatives pitch perturbation |
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