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在低落压比4~10下,对高速二维单边膨胀喷管模型试验件的壁面静压分布进行了试验研究,模拟气体为高压空气;用三维数值计算得到了喷管性能参数,丰富了流场信息。试验和数值模拟结果表明,处于深度过膨胀状态下的单边膨胀喷管内部出现了自由激波、分离激波、两种激波相交及相互影响、自由激波分离和激波诱导分离等复杂现象;上膨胀面大面积的气流分离而形成的低压区使喷管轴向推力系数Cfa仅为0.78~0.87;此外,推力矢量角pδ为18°~25°,这对飞行器的配平和控制面操作带来一定的困难。
The static pressure distribution on the wall of high-speed two-dimensional uniaxial expansion nozzle was experimentally studied under the condition of low pressure ratio of 4 ~ 10, and the simulated gas was high pressure air. The nozzle performance parameters were obtained by three-dimensional numerical calculation, Flow field information. The experimental results and numerical simulations show that free shock waves, separation shock waves, the intersection and interaction between the two shock waves, the free shock separation and the shock-induced separation appear in the single-side expansion nozzle under deep over-inflated condition Phenomenon; the expansion of the large area of ?? the flow of air separation and the formation of low-pressure nozzle axial thrust coefficient Cfa only 0.78 ~ 0.87; In addition, the thrust vector angle pδ 18 ° ~ 25 °, which aircraft trim and control surface Operation brings some difficulties.