论文标题
跨性苏联流程的新相似法
A new similarity law for transonic-supersonic flow
论文作者
论文摘要
如何在高速流中准确有效地确定飞机的空气动力是现代空气动力学的巨大挑战之一。在这封信中，我们提出了一项新的相似性定律，以使较薄的身体稳定的跨性别 - 苏普斯式流动。新的相似性法是基于当地的马赫数冻结原则。这取决于特定的热比和自由流马赫数。新的相似性法律使人们能够从更容易接触到的参考状态下确定飞机的升力和拖动系数。新的相似性定律的有效性通过了与二维机翼流和三维机翼流的数值模拟的良好一致性证实。
How to determine accurately and efficiently the aerodynamic forces of the aircraft in high-speed flow is one of great challenges in modern aerodynamics. In this Letter we propose a new similarity law for steady transonic-supersonic flow over thin bodies. The new similarity law is based on the local Mach number frozen principle. It depends on both the specific heat ratio and the free-stream Mach number. The new similarity law enables one to determine the lift and drag coefficients of the aircraft from that of a reference state which is more reachable. The validity of the new similarity law has been confirmed by the excellent agreement with numerical simulations of both two-dimensional airfoil flows and three-dimensional wing flows.
