Spillage-Adaptive Fixed-Geometry Bump Inlet of Wide Speed Range

Zonghan Yu,Guoping Huang,Omer Musa,Ruilin Wang

doi:10.3390/aerospace8110340

Zonghan Yu, Guoping Huang + Show 2 more

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https://doi.org/10.3390/aerospace8110340

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Journal: Aerospace	Publication Date: Nov 11, 2021
Citations: 6	License type: CC BY 4.0

Affiliation: Nanjing University of Aeronautics and Astronautics

Abstract

In this work, a new spillage-adaptive bump inlet concept is proposed to widen the speed range for hypersonic air-breathing flight vehicles. Various approaches to improve the inlet start-ability are summarized and compared, among which the bump-inlet pattern holds the merits of high lift-to-drag ratio, boundary layer diversion, and flexible integration ability. The proposed spillage-adaptive concept ensures the inlet starting performance by spilling extra mass flow away at low speed number conditions. The inlet presetting position is determined by synthetically evaluating the flow uniformity and the low-kinetic-energy fluid proportion. The numerical results show that the flow spillage of the inlet increases with the inflow speed decrease, which makes the inlet easier to start at low speed conditions (M 2.5–6.0). The effects of the boundary layer on spillage are also studied in this work. The new integration pattern releases the flow spillage potentials of three-dimensional inward-turning inlets by reasonably arranging the inlet compression on the bump surface. Future work will focus on the spillage-controllable design method.

Highlights

Hypersonic inlet design is crucial to achieving the target of rapid global arrival [1,2,3,4].The contribution of inlets to the propulsion system is estimated [5] as follows: According to the maximum temperature limit which the material can bear at present, the converted energy by inlet compression occupies 12% of the added energy by combustion at M 1.8, while it increases to 66.7% at M 3.4
3.53.5 mm flatflat plate is set in front of the bump surface for boundary layerlayer de‐
Kouichiro [42] proposed another ηKE -RM relation, which is based on side-compression inlet experiments

Summary

Introduction

The contribution of inlets to the propulsion system is estimated [5] as follows: According to the maximum temperature limit which the material can bear at present (the temperature limit is approximately 2000 K), the converted energy by inlet compression occupies 12% of the added energy by combustion at M 1.8, while it increases to 66.7% at M 3.4. This energy reaches approximately 230% at M 4.5. The speed range is widened by approximately 3.5% in M

Methods

Results

Conclusion