联合激波针-逆向喷流方法的新概念研究

Numerical investigation on drag and heat-transfer reduction using combined spike and forward facing jet method

提出一种可用于高超声速减阻和降热的联合激波针-逆向喷流方法,采用数值模拟对该方法在高超声速二维以及轴对称球柱外形上应用进行了概念验证。结果表明联合激波针-逆向喷流方法能有效降低外形的阻力以及头部热流,在同等来流及喷流条件下,其减阻和降热的效率均优于单独逆向喷流的结果。该方法应用于轴对称外形时,流动在钝体肩部再附点附近产生激波干扰而导致壁面出现热斑,通过增大喷管直径的方法来增大喷流量可降低激波在肩部再附区的干扰效应,达到消除热斑、降低局部高热流的目的。

The combined spike and forward facing jet method was put forward and was used on 2D planar cylinder and the axisymmetrical sphere cone.The Navier-Stokes equations were solved numerically to simulate the hypersonic flow around the blunt body with the spiked forward facing jet at the stagnation point.It is demonstrated that the combined spike and forward facing jet method has great efficiency in reducing drag and surface heat-transfer.Compared with the case only using forward facing jet,this paper＇s method can achieve equal,if no morn than,drag and heat-transfer reduction effects with less jet mass.It will produce hot-spot on the shoulder of axisymmetrical sphere cone,with the surface heat transfer much higher than that without injection.Large spike radius can increase jet mass,weaken the attached shock and eliminate the hot-spot on the shoulder.