进口型线水平投影可控的变截面内收缩进气道设计

doi:10.7527/S1000-6893.2016.0270

Abstract

Abstract:

A design method is developed for three-dimensional variable section inward turning inlet with controlled horizontal projection of intake curve. Based on the basic flowfield with arc tangent Mach number distribution, the inward turning inlet with smooth shape transition from an elliptical horizontal projection of intake curve to a circular exit is designed utilizing streamline tracing and shape transition techniques. Numerical simulation is conducted at the design point (Ma_i=5.4) and the relay point (Ma_i=4.0). The results indicate that the inlet is of the major features of the basic flowfield, and 98% free incoming flow at the design point can be captured under the inviscid condition. The performance of the throat plane is close to the basic flowfield. In comparison with the inlet of elliptical intake, the variable section inlet with elliptical-to-circular transition has similar flowfield structure and slightly lower performance. Under the viscous condition, the total pressure recovery coefficient of the throat plane reduces 2.9% and 1.2% at the design point and the relay point, respectively. In addition, the inlet has high overall performance, and the flow coefficient reaches 0.82 at the relay point.

Key words: hypersonic, inward turning inlet, horizontal projection, shape transition, streamline tracing

CLC Number:

V231.3

LI Yongzhou, SUN Di, ZHANG Kunyuan, GUO Shiliang. Design on variable section inward turning inlet with controlled horizontal projection of intake curve[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(5): 120640-120640.

References

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Design on variable section inward turning inlet with controlled horizontal projection of intake curve

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