一种新型乘波体设计方法研究

吻切锥乘波体是一种非常重要的高超声速飞行器设计构型,设计出既具有较高升阻比又能保持较高容积效率的乘波体,仍然是研究的难点。提出一种新型吻切乘波体设计方法,以圆锥流场为基准,在上表面出口型线(FCC)和下表面激波出口型线(ICC)基础上引入一条新的出口激波圆心曲线;通过调整出口激波曲率半径达到改变乘波体体积和容积率的目的;设计四种乘波体———传统吻切锥乘波体、激波半径减小乘波体、激波半径加长乘波体和直线ICC乘波体,并采用CFD数值模拟方法对四种乘波体进行对比分析。结果表明:所提乘波体设计方法合理可行;在无粘条件下,容积率小的乘波体拥有更大的升阻比;在粘性条件下,四种乘波体升阻比接近,本文设计的乘波体具有更大的容积率和更好的应用价值。

Investigation on a novel waverider design method

This paper proposes a new design method of osculating-cone waverider. Based on the conical flow field, with Flow Capture Curve (FCC) and Inlet Capture Curve (ICC) unchanged, a new curve is introduced to broaden the design space of conventional osculating-cone waverider. By adjusting the radius of curvature of the exit shock to achieve the purpose of changing the volume and volume efficiency of the waverider, in this study, four kinds of waveriders are designed, including the traditional osculating-cone waverider, the shock radius-reduced waverider, the shock radius-lengthened waverider, the waverider with straight line ICC. The CFD numerical simulation method was used to compare and analyze these waveriders designed in this paper. The results show that under the inviscid condition, the waverider with low volume efficiency has a larger lift-to-drag ratio; under viscous conditions, these four waveriders behave close lift-to-drag ratio property, but the waverider newly designed in this paper has a larger volumetric efficiency and better engineering application value.