高超侧压式进气道高焓脉冲风洞实验

Test of a generic sidewall compression scramjet inlet in the high-enthalpy impulse wind tunnel

关键词:  超燃冲压发动机  高超声速进气道  侧压式进气道+  进气道试验

Key words:  Scramjet  Hypersonic inlet  Sidewall compression inlet~+  Inlet test

摘要:

为验证一种双楔顶压、侧板中置的侧压式进气道基本性能,设计了一套进口面积为110mm×91mm的双流道试验模型,并在300mm马赫数6的高焓脉冲风洞中进行了吹风实验。实验测量了进气道和隔离段内的沿程静压分布和隔离段进出口截面的皮托压力分布,分析了进气道内的典型流场特征,获得了进气道的基本性能参数,并以马赫数的测量为例阐述了流场不均匀性对测量结果可能造成的影响。实验结果表明,马赫数6来流条件下,该侧压式进气道流量系数为0.83,隔离段出口平均马赫数为2.57,总压恢复系数为0.296,增压比为23.7,表明这种侧压式进气道的气动布局方式能够获得较好的总体性能。

Abstract:

A generic three-dimensional scramjet inlet with two ramps and mid-located sidewalls was tested in the CARDC (chinese aerodynamic research and development center) high-enthalpy impulse wind tunnel at Mach 6. Distributions of the static pressure along the centerlines of the top wall, sidewall and cowl bottom wall, and Pitot-pressure distributions at the inlet and isolator exit plane were experimentally obtained. Among them, static pressure distributions were compared with the numerical results simulated by FLUENT software and show good agreement except for some pressure peaks throughout the inlet and isolator. Based on the experimental data, typical characteristics of the flowfiled were identified. Pitot-pressure distributions show at the inlet exit plane, the flowfield is significantly nonuniform, but at the isolator exit plane, the core flow tends to be nominally uniform. Experimental results indicate the scramjet inlet has a better performance with a mass capture ratio 0.83, averaged Mach number 2.57, total pressure recovery 0.296, and compression pressure ratio 23.7 at the isolator exit plane.