摘要
为了充分发挥乘波体布局作为吸气式高超声速飞行器前体的预压缩功能,基于吻切锥原理发展了一种多级压缩乘波体设计方法。通过该设计方法设计得到了三级压缩锥导乘波体。设计状态下的数值模拟结果显示,该乘波体产生的3道锥面激波按照设计预期相交于底部截面上。该三级压缩锥导乘波体的上表面采用膨胀式上表面布局设计并在底部与进气道相连,将进气道唇口取为设计条件下3道锥面激波相交的位置,由此获得了进行风洞实验的三级压缩锥导乘波体前体/进气道布局。对该型三级压缩锥导乘波体前体/进气道布局开展了数值模拟与高超声速风洞实验的对比校验,在流场波系结构方面得到了相吻合的结果,表明了设计方法的可靠性。
In order to give full play to the waverider forebody＇s pre-compression effect, a new design method for the multistage compression waverider is presented based on the osculating cone theory. A three-stage cone-derived waverider is designed by using this design method. Numerical simulation results show that three conical shock waves intersect at the bottom section as expected in design. The three-stage compression cone-derived waverider used in wind tunnel tests has an expanded upper surface. At the bottom section the waverider is connected with the inlet. The shape of the inlet lip is designed to match the contour of the three conical shock waves intersec- tion. Experimental research on the waverider forebody-inlet model is conducted. It is found that the shock wave shape is in good agreement with the numerical simulation result. Therefore, the correctness of the design method is validated.
出处
《实验流体力学》
CAS
CSCD
北大核心
2015年第5期38-44,共7页
Journal of Experiments in Fluid Mechanics
关键词
高超声速
气动布局
锥导乘波体
三级压缩
数值模拟
风洞实验
hypersonic
aerodynamic configuration
cone-derived waverider
three-stage compression
numerical simulation
wind tunnel experiment
