Aerodynamic Design of An Forebody-integrated Bump Inlet With A S-Shape Diffuser

DOI

10.2991/ifeesm-15.2015.156How to use a DOI?

Keywords

Bump Inlet, S-Shape Diffuser, Airframe-inlet Integrity Design

Abstract

In this paper the whole design method of an integrated bump inlet with an S-shape diffuser at its design Mach number 1.7 is presented. The model of the intake system with airframe is established based on the aircraft's flight task requirements. Then CFD analysis result indicates the low-momentum boundary layer fluid could be pushed away from the model centerline to the sides of the bump. The total pressure recovery reach 0.91 at the outlet of the intake. If the S-shape Diffuser is carefully designed by the function of centerline distribution, area distribution and area shape, it would prevent the airflow separation behind the normal shock wave in throat effectively and achieve better performance of the inlet.

Copyright

© 2015, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Wenlong Luo
AU  - Qiang Wang
PY  - 2015/09
DA  - 2015/09
TI  - Aerodynamic Design of An Forebody-integrated Bump Inlet With A S-Shape Diffuser
BT  - Proceedings of the 2015 International Forum on Energy, Environment Science and Materials
PB  - Atlantis Press
SP  - 840
EP  - 845
SN  - 2352-5401
UR  - https://doi.org/10.2991/ifeesm-15.2015.156
DO  - 10.2991/ifeesm-15.2015.156
ID  - Luo2015/09
ER  -