高超声速双楔激波干扰定常射流控制试验研究

Double wedge shock interaction control using steady jet in hypersonic flow:Experimental study

激波干扰问题是超声速/高超声速飞行器中广泛存在的现象,且会带来压力载荷、热载荷剧增等严重问题。为了降低激波干扰区热载荷,开展了高超声速双楔流场第Ⅴ类、第Ⅳ类激波干扰气源/自持定常射流控制试验研究。双楔激波干扰气源定常射流控制降热机理体现在两方面:射流的隔绝作用以及激波干扰结构改变作用。在射流控制下,激波干扰区与壁面的干扰强度减弱,流场结构变化显著,不再是典型的第Ⅴ类、第Ⅳ类激波干扰结构,壁面热流也相应降低。射流压比越大,隔绝作用及结构改变作用越强,热流极值降低比例也越大,第Ⅴ类、第Ⅳ类激波干扰的热流极值最高分别降低约81.2%和79.6%。自持定常射流通过收集高速来流能量产生,在自持射流控制下,双楔第Ⅴ类、第Ⅳ类激波干扰区热流极值分别降低约20%和4.5%,提高自持射流压比是提升其激波干扰控制降热效果的关键。

Shock interaction is a widespread phenomenon in supersonic/hypersonic vehicles,bringing serious prob⁃lems such as pressure load and thermal load increase.To reduce the thermal load in the shock interaction zone,we conduct an experimental study on the control of Type-V and Type-Ⅳdouble wedge shock interaction using air source/self-sustaining steady jet in hypersonic flow.The control and heat reduction mechanism of double wedge shock inter⁃action by air source steady jet is embodied in two aspects:isolation effect of jet flow and structural change effect of shock interaction.Under the jet control,the interaction intensity between the shock interaction zone and the wall is weakened,and the structure of the flow field changes significantly,which is no longer the typical Type-V and Type-Ⅳshock interaction,and the heat flux on the wall also decreases correspondingly.Larger jet pressure ratios lead to stronger isolation effect and structural change effect,as well as larger reduction ratios of heat flux extremum.The maximum reduction ratio of heat flux extremum of Type-V and Type-Ⅳshock interaction is about 81.2%and 79.6%,respectively.Self-sustaining steady jet is generated by collecting high speed flow energy.Under the control of selfsustaining jet,the heat flux extremum of the double-wedge Type-V and Type-Ⅳshock interaction zones decreases by about 20%and 4.5%respectively.Improving the pressure ratio of the self-sustaining jet is the key to improving the control and heat reduction effect of shock wave interaction.