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基于当地流活塞理论的气动弹性计算方法研究

Simulation of Supersonic or Hypersonic Aeroelasticity Basing on Local Piston Theory

  • 摘要: 发展了一种高效、高精度的超音速、高超音速非定常气动力计算方法------基于定常CFD技术的当地流活塞理论. 运用当地流活塞理论计算非定常气动力,耦合结构运动方程,实现超音速、高超音速气动弹性的时域模拟. 运用这种方法计算了一系列非定常气动力算例和颤振算例,并和原始活塞理论、非定常Euler方程结果作了比较. 由于局部地使用活塞理论假设,这种方法大大地克服了原始活塞理论对飞行马赫数、翼型厚度和飞行迎角的限制. 与非定常Euler方程方法相比,当地流活塞理论的效率很高.

     

    Abstract: Existing piston theory for supersonic flow can only deal with thin supersonic wing with sharp leading edge at small angles of attack. The unsteady CFD technology basing on Euler/N-S equations can solve the unsteady aerodynamic loads precisely, but it often needs much computational time even just for a simple 3D shapes. Local piston theory basing on steady CFD technology has a good precision and high efficiency to compute the supersonic or hypersonic unsteady pressure by comparing the piston theory and unsteady Euler code. Coupling the structure equations, the supersonic or hypersonic aeroelasticity is simulated in time domain. The computed flutter precision of local piston theory is higher than original piston theory by comparing with the experimental data. The non-linear characteristics of the flutter speed with increasing Mach number and increasing anger of attack of a typical wing are studied. The computed flutter results by local piston theory agree with the theoretic analysis and are better than original piston theory at high Ma numbers.

     

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