乘波构型钝化方法分析及性能研究

Blunt methods for the leading edge of waverider

基于乘波构型设计高升阻比飞行器是新型高超声速飞行器布局设计的一种有效途径。受热防护系统设计和材料加工工艺等限制,实际应用中需要对乘波构型具有的尖前缘进行钝化。本文针对移除材料和增加材料两种边缘钝化方法进行了对比研究,分析了两种方法的共同点,并采用典型外形阐明了这一共性。在此基础上,基于移除材料方法对典型外形进行了一致钝化和非一致边缘钝化,利用CFD方法对两种钝化外形气动性能进行了仿真分析。流场计算表明:和一致边缘钝化相比,非一致边缘钝化有效降低了下表面高压气体向上表面的渗透,提高了外形所受的升力,降低了边缘所受的阻力,从而提高了钝化外形的升阻比;尖前缘乘波构型最大升阻比位于零度迎角,而钝化之后乘波构型最大升阻比在2°迎角附近取得;随着迎角的增大,钝化外形升阻比变化趋势和尖前缘外形变化趋势一致,非一致钝化乘波构型气动性能和尖前缘乘波构型气动性能较接近,非一致钝化方法得到外形的气动性能优于一致钝化外形。研究可为高超声速乘波飞行器的钝化修形设计提供参考依据。

Waverider is an effective reference configuration when designing high Lift-to-Drag ratio hypersonic aircraft.Restricted by aerodynamic thermal protection system and material processing technique,the sharp leading edge of a ideal waverider needs to be blunted.Two blunt methods,Tincher method and Takashima method,are discussed and analyzed in this work,and the feature that the two methods have in common is suggested and clarified by a typical waverider.Chosen a typical ideal waverider as reference model,uniform and non-uniform methods are applied,and the aerodynamic performances are studied.CFD method is used to analyze the performance of the three waverider models.The sharp leading edge waverider achieces its maximum Lift-to-Drag ratio at 0°angle of attack,which is the design point and shows the'wave rider'characteristic,the sharp leading edge prevents the high pressure leaking to the upper surface,thus shows good aerodynamic performance.Blunted waverider obtains the maximum lift-to-drag ratio at about 2°angle of attack.As the angle of attack increases,the aerodynamic performance of both the ideal and the blunted waveriders shows the same variationtrend,while the performance of the non-uniform blunted waverider is more close to the ideal one.The flow field pressure contours shows that the non-uniform blunted method effectively reduces the high pressure gas leaking from the lower surface to the upper surface,thus the non-uniform blunted waverider shows better aerodynamic performance than uniform blunted one,which can be referenced in the configuration design of hypersonic waverider analogue vehicle.