密切曲内锥乘波前体进气道低马赫数性能试验研究

Experimental Studies of Osculating Inward Turning

关键词:  乘波体  进气道  一体化  密切内锥  风洞试验

Key words:  Waverider  Inlet  Integration  Osculating inward cone  Wind tunnel experiment

摘要:

基于密切曲内锥乘波前体进气道的一体化设计方法，生成了内外流匹配的一体化三维乘波前体进气道理论构型。在几何约束条件下，完成了实用化构型设计，其总收缩比4.6，内收缩比2.0。开展了来流马赫数3.0，3.5，4.0条件下的风洞试验研究。试验研究结果表明，一体化前体进气道可以在来流马赫数3.5及以上自起动；在马赫3.5和4.0，攻角0°时，其流量捕获系数分别为0.65和0.73，最大抗反压性能分别为26倍和38倍的来流压力。本文的试验研究结果，证实了设计的一体化密切内锥乘波前体进气道能够在吸气式高超声速飞行器的低马赫数端正常工作，并具备较高的流量捕获系数。

Abstract:

A three dimensional prototype hypersonic forbody/inlet model has been generated using Osculating Inward turning Cone Waverider forebody Inlet (OICWI) design method. An application OICWI model with geometrical constrained has been designed based on the prototype model and geometrical transition technology. Its total contraction ratio is 4.6 and the inner contraction ratio is 2.0. Wind-tunnel tests have been conducted at free stream flow Mach number of 4.0，3.5 and 3.0，respectively. The critical self-start Mach number is 3.5. The mass flow capture ratios at Mach number 3.5 and 4.0，angle of attack 0° are 0.65 and 0.73 respectively，the maximum withstand back pressure ratios at corresponding conditions are 26 and 38 times of free stream static pressure. The experiment results indicate OICWI test model can successfully work at the low fly Mach number range of air-breathing hypersonic vehicle and it also has high flow captured ratios at the low fly Mach number range.