Effects of boundary‐layers bleeding on performance parameters of hypersonic inlets

Abstract

Purpose

The purpose of this paper is to study the effects of boundary‐layers bleeding on performance parameters of hypersonic inlets.

Design/methodology/approach

The inner flowfield of a hypersonic inlet at different bleeding rates is simulated with a Reynolds‐averaged Navier‐Stokes solver using a renormalization group k‐ε turbulence model.

Findings

In contrast with no bleeding, the performance parameter of hypersonic inlets without backpressure is reduced slightly, but the flow uniformity is improved. The interaction between boundary layers and shocks is weakened at the action of the bleeding, which leads to that the boundary‐layers separations at the entrance of the isolator caused by the high‐backpressure occur later, and it can improve the maximum backpressure ratio of hypersonic inlets. With the bleeding rate increasing, the maximum backpressure ratio of hypersonic inlets is added, while the total‐pressure recovery coefficient and mass‐captured coefficient are reduced.

Originality/value

This paper is a useful reference to the design and performance improvement of hypersonic inlets and propulsion systems.

Citation

Chang, J. and Fan, Y. (2009), "Effects of boundary‐layers bleeding on performance parameters of hypersonic inlets", Aircraft Engineering and Aerospace Technology, Vol. 81 No. 3, pp. 204-211. https://doi.org/10.1108/00022660910954709