压力分布可控的高超声速进气道/前体一体化乘波设计

doi:10.7527/S1000-6893.2016.0017

Abstract

Abstract:

On the basis of two-dimensional curved shock hypersonic inlets, a new integration,waverider design, of hypersonic inlet and forebody with preassigned pressure distribution is presented. A proper streamwise pressure distribution is assigned as the first step according to the shape of a curved shock wave. Afterwards, the external compression part of the inlet and forebody with controllable wall pressure distribution could be designed using the inverse two-dimensional method of characteristics. An integrated configuration is then derived from this concept and numerically studied. The results show that, on the design point, the flow capture ratio of the integrated configuration is enhanced by 27% compared with the pure two-dimensional inlet without sidewalls. The pressure ratio coefficient of inlet outflow rises by 48.5%, and the total pressure recovery coefficient is 10% higher than the no-sidewall inlet. In addition, compared with the Caret integration case, although with the same geometry shape and waverider character,the performance of mass flow rate, pressure ratio and total pressure recovery coefficient are 5%, 6.4%, and 2.3% improved, respectively.

Key words: hypersonic, inlet and forebody integration, pressure distribution, waverider concept, two-dimensional hypersonic inlet

CLC Number:

V231.3

LI Yiqing, HAN Weiqiang, YOU Yancheng, PAN Chengjian. Integration waverider design of hypersonic inlet and forebody with preassigned pressure distribution[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(9): 2711-2720.

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Integration waverider design of hypersonic inlet and forebody with preassigned pressure distribution

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