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The aerodynamic characteristics and distinctive features of the flow past hypersonic integral-layout flight vehicles with air-breathing engines intended for cruise flight in the atmosphere are experimentally investigated. The experiments were conducted on a simplified model designed with regard for the general principles of integration of vehicles of the class considered. The tests were performed in a wind tunnel over the Mach and Reynolds number ranges 0.6 ≤ M ≤ 4 and 6.3 × 106 ≤ Re ≤ 16 × 106, respectively. Balance testing was carried out, the pressure distributions over the vehicle surface were measured, and the flowfields on the model surface were photographed. The effects of mounting a nacelle and contouring the internal duct are considered. The effect of the corrections on the duct flow in the absence of jet modeling is estimated. The results obtained can be used as a basis for developing the aerodynamic configurations of integral-layout flight vehicles, for forming their thrust and aerodynamic parameters under full-scale flight conditions, and for testing computation methods. 相似文献
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采用三维嵌合体网格埋入技术计算复杂外形的流场,这种技术简化了复杂几何外形计算网格的结构,将物理区域分成一系列子域,使每个子域都易于生成网格,并且其流场的计算可根据相应的边界条件独立地求解,在埋入边界上对流动参数进行插值传递子域网格的干扰信息,通过两个流场的耦合迭代计算整个流场的解。 相似文献
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