曲外锥乘波前体进气道低马赫数段实验研究

Experimental studies of Curved Cone Waverider forebody Inlet(CCWI)at low Mach number range

为了研究新型一体化曲外锥乘波前体进气道在低马赫数端的自起动、抗反压特性及侧滑对性能的影响,基于几何约束及钝度修型的实用化风洞实验模型,采用进气道节流系统,在来流马赫数3.0、3.5和4.0,迎角-4°~6°范围内,不同堵锥位置状态下获得了一体化曲外锥乘波前体进气道的表面压力分布及流场高清纹影。实验结果表明,实验模型在来流马赫数3.5和4.0时具备自起动能力;在0°迎角,来流马赫数3.5和4.0,最大抗反压能力分别约为24和33倍来流压力;侧滑角对一体化曲外锥乘波前体进气道的流量捕获和流动压缩性能影响相对较弱。曲外锥乘波前体进气道具有同超燃冲压燃烧室、高超声速飞行器进行一体化设计的特性。

The self-start ability,anti-backpressure performance and side slip influences to the performance of the Curved Cone Waverider forebody Inlet(CCWI)were experimentally studied in the present paper.Based on the geometrically constrained and bluntly modified practical CCWI wind tunnel experimental model,using the inlet throttling systems,the static pressure distributions and high resolution sherilen maps of the CCWI's flow field were obtained at free steam Mach numbers(Ma∞)3.0,3.5 and 4.0 at different throttling cone positions.The experimental results show that the integrated CCWI model can self-start at Ma∞ 3.5 and 4.0.At the angle of attack 0°,its maximum anti-back pressure abilities is about 24 and 33 times of the free stream static pressure(p∞)at Ma∞3.5 and 4.0,respectively.Side slip has little influence on mass flow capture and flow compression abilities for CCWI.The study on CCWI can be used for practical integration studies with scramjet engine and air-breathing vehicles.