高速火箭增强冲压发动机内转进气道气动设计与风洞试验

doi:10.7527/S1000-6893.2025.32202

Abstract

Abstract: Integrating inward-turning inlet with high compression efficiency, good internal flow quality, high flow coefficient, and low overflow resistance with a rocket-augmented ramjet engine can effectively improve the performance of rocket-combined ramjet inlet within the typical flight range and greatly enhance the application potential of rocket-augmented ramjet engine. Based on the typical central strut configuration of a rocket-augmented ramjet engine, if only a simple structural integration method is adopted, the physical intervention of the central strut would seriously damage the compression performance of the inward-turning inlet while its wedge-shaped leading edge would divide the high-speed airflow downstream of the inlet isolator and cause oblique shock and expansion wave interference, resulting in additional compression and an increase in internal contraction ratio, causing a significant decrease in the total pressure recovery coefficient. To address these issues, this paper proposes a structural integration design method between an inward-turning inlet and central strut based on streamline tracing technique. By integrating the central strut with the inlet compression surfaces, not only can additional compression effects be eliminated, but the inflow compression capability of its special precursor can also be fully utilized. The numerical simulation and wind tunnel test verification results indicate that this design method can enable the integrated inward-turning inlet to fully exert the compres-sion performance of the basic flow field while introducing the central strut. Compared with the traditional wedge-shaped central strut, its length can be reduced by 60% at most, and the internal contraction ratio can be reduced by 25%, thus ensuring better start capability. Under the conditions of high contraction ratio and strong compression with the incoming flow of Mach 6 and the throat pressure rise ratio of 34.8, the total pressure recovery coefficient is improved by 17%.

Key words: rocket-augmented ramjet, inward-turning inlet, streamline tracing technique, central strut, wind tunnel test

CLC Number:

V438.2

References

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Aerodynamic design and wind tunnel test on the inward-turning inlet of high-speed rocket-augmented ramjet engine

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