| 流体式高超声速可调进气道流动机理及工作特性分析 |
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| 引用本文： | 李程鸿,谭慧俊,孙姝,张启帆,田方超.流体式高超声速可调进气道流动机理及工作特性分析[J].宇航学报,2011,32(12):2613-2621. |
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| 作者姓名： | 李程鸿 谭慧俊 孙姝 张启帆 田方超 |
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| 作者单位： | 1.南京航空航天大学能源与动力学院，南京 210016；2.南京航空航天大学民航/飞行学院，南京 210016 |
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| 摘 要： | 针对基于二次流控制的定几何高超声速可调进气道设计概念，给出了其具体的流道实现方案，而后通过全流道仿真分析，检验了该可调进气道在马赫数4~6范围内的可实现性，获得了其工作特性，并对弯曲激波后的总压损失特性、二次流的能量获取及消耗机制等流动机理进行了专门分析。结果表明：该流体式可调进气道能够依靠自身高压驱动二次流来实现对口部波系的调节，使进气道在低马赫数下的流量系数相对于常规定几何高超声速进气道提高24%以上，总压恢复提高7%左右，且最大二次流消耗量只占了进气道捕获流量的1.6%左右。另外，虽然弯曲激波的波后总压和马赫数分布表现出了一定的不均匀性，但是其平均总压恢复系数与相同倾角平面激波相比下降不大。二次流循环流动所消耗的机械能由外部外流剪切力做功补充，而二次流注入会使当地边界层的速度型变得瘦弱，形状因子增大。
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| 关 键 词： | 高超声速 进气道 可调进气道 二次流 流动控制 |
Flow Mechanism and Operating Characteristics of a Fluidic Variable Hypersonic Inlet |
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| LI Cheng-hong,TAN Hui-jun,SUN Shu,ZHANG Qi-fan,TIAN Fang-chao.Flow Mechanism and Operating Characteristics of a Fluidic Variable Hypersonic Inlet[J].Journal of Astronautics,2011,32(12):2613-2621. |
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| Authors: | LI Cheng-hong TAN Hui-jun SUN Shu ZHANG Qi-fan TIAN Fang-chao |
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| Affiliation: | 1.College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China； 2.College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | To study the concept of variable hypersonic inlet with fixed-geometry controlled by secondary flow, a realizable secondary flow induced duct scheme is proposed in this paper. Then, by using a computational method, the realization of this variable fluidic hypersonic inlet with the operating Mach number from 4 to 6 is validated and the operating characteristics are obtained. Finally the flow mechanism of the secondary flow is investigated by analyzing parameters after the curved shock waves and energy consuming /supplying in the circulatory flowing of secondary flow. The results show that adjusting valves in ducts can alter the secondary flow rate induced from fluidic variable hypersonic inlet driven by high pressure in the isolator to realize the adjusting the shock waves at cowl lip. For a fluidic variable hypersonic inlet with an operating Mach number of 4-6, the shock-on lip condition can be maintained from Mach 5 to 6 with the maximum cost of 1.6% secondary flow ratio. The captured mass flow and total pressure recovery are enhanced by 20% and 7% respectively at low Mach numbers compared with conventional hypersonic inlet. Although the distributions of the total pressure recovery and the Mach number become non-uniform, the mass-averaged total pressure recovery decreases a little compared with the planar shock wave with the same turn angle. The energy consumed by secondary flow in the circular flowing is supplied by working of external flow shear stress. With the injecting of secondary flow, the local boundary layer becomes thinner and the shape factor rises.
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| Keywords: | Hypersonic Inlet Variable inlet Secondary flow Fluidic control |
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