现代自然层流翼型的设计方法

本文介绍一种设计跨声速自然层流翼型的计算流体力学(CFD)方法。本方法采用“正反迭代、余量修正”设计原理,通过将跨声速翼型设计软件NPU-TD2D中的反设计程序进行改进,并与含有层、湍流混合边界层修正的跨声速层流翼型计算程序DLRBGKWALZ耦合,实现了在跨声速粘性流动条件下直接设计层流翼型。亚、超临界的设计实例和风洞验证表明,本方法可以在几个设计迭代内设计出压力分布、转捩位置及气动参数均准确收敛于设计目标的新翼型,是一种设计现代自然层流翼型的有效而实用的CFD方法。

Numerical Design Method for Modern NLF Airfoils

Natural Laminar Flow (NLF) airfoils and wings are the modern techniques for the next generation of transport aircraft, but most of the numerical inverse methods for airfoil and wing designs are still confined to conventional full turbulent configurations. This paper represents a CFD method for the design of NLF airfoils directly under transonic viscous flow conditions.A modified inverse code of the transonic 2-D design software NPU-TD2D based on "iterative residual correction" principle has been coupled with an improved transonic airfoil analysis code DLR-BGKWALZ which includes the calculation of laminar boundary layer, transition prediction and turbulent boundary layer. The design examples, including the three presented in this paper show that the method is capable of providing satisfactory design results of modern NLF airfoils within a few design iterations. The windtunnel tests of the air-foils designed suggest that the present method may be considered to be an effective and practical design tool for NLF airfoils.