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首页> 外文期刊>Journal of Aerospace Sciences and Technologies >FLOW FIELD OVER BOAT-TAIL REGION OF HEAT SHIELD OF A TYPICAL LAUNCH VEHICLE AT MACH 2
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FLOW FIELD OVER BOAT-TAIL REGION OF HEAT SHIELD OF A TYPICAL LAUNCH VEHICLE AT MACH 2

机译：一台典型的发射车在马赫2时热风船的船尾区域上的流场

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摘要

Boat-tailed heat shields offer a higher payload volume but lead to flow separation and associated effects. In the present paper an attempt is made to find out the effect of boat-tail angle on the over all flow field with special emphasis on acoustic load near the boat-tail region. Experiments and CFD routes are used to investigate the flow field. Experiments consist of steady and unsteady pressure measurements and flow visualisation through schlieren and oil flow. CFD simulations are also carried out for the wind tunnel conditions. Results indicate that fluctuating pressure co-efficient increases with flow separation, peaks at reattachment point and reduces further downstream. An Increase in boat-tail angle from 20° to 30° leads to about 12% increase in acoustic loads. All these studies were carried out at a Mach number of 2 and a Reynolds number of 4 X 10~6 based on model length.
机译：船尾隔热罩可提供更高的有效负载量，但会导致流动分离和相关影响。在本文中，试图找出船尾角对整个流场的影响，特别着重于船尾区域附近的声负荷。实验和CFD路线用于研究流场。实验包括稳态和非稳态压力测量以及通过schlieren和油流的流动可视化。还针对风洞条件进行了CFD模拟。结果表明，脉动压力系数随流量分离而增加，在重新连接点达到峰值，并在下游进一步降低。船尾角从20°增大到30°会导致声学负载增加约12％。所有这些研究都是基于模型长度以2的马赫数和4 X 10〜6的雷诺数进行的。

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