牛顿流理论及其在谐振机翼上的应用

Newtonian Flow Theory and Its Application on Harmonic Oscillating Wings

根据牛顿流理论,文中讨论了高马赫数、任意迎角、一般剖面在均匀来流中作沉浮和俯仰谐振的翼型和机翼。导得翼型和机翼表面的牛顿撞击压强和安定性导数公式。给出楔、平板三角翼、双抛物线剖面三角翼俯仰刚性导数(-C_(mθ)和阻尼导数(-C_(m))的数值例子。数值结果与现有的牛顿-布兹曼流理论、薄激波层理论、欧拉方程摄动理论的结果作了比较,算例表明本文的结果令人满意。

On the Newtonian flow theory, discuss airfoils and wings of high Mach number, arbitrary angles of attack, and general section performing a harmonic pitching and pluging oscillation in a uniform incoming in persent paper. Derive formulas predicting the Newtonian impact pressure on airfoil and wing surface, and the stability derivatives. Give the numrical examples for the stiffness derivatives (- Cmθ) and the damping-in-pitch derivatives (-Cmθ) of wedge, flat plate delta wings, and double parabolic section delta wing.The numerical results are compared with existing theories including Newton-Busemann flow theory. thin shock-layer theory, and Eulerian equation perterbation theory.It is shown from above examples that results in persent paper are satisfactory.