Optimization Design and Flow Control of Bump Inlet
DOI:
https://doi.org/10.54691/djksgp76Keywords:
Concave-convex Inlet, Optimized Design, Flow Control.Abstract
For a bump inlet with a thick boundary layer in front of the inlet and a limited inlet height, the ability of bump to remove the boundary layer is limited. To obtain an inlet with a high total pressure recovery coefficient and low distortion, a serpentine diffuser is used to improve the flow field at the outlet. Then, a spoiler blade is used to eliminate the low pressure zone. In order to further improve the total pressure recovery coefficient of the inlet, a discharge slot is opened above the bump to relieve some of the low energy flow in front of the inlet. Through the combination of these two flow control methods, compared to the inlet without flow control, the total pressure recovery coefficient of the inlet is increased by 0.0262, and the steady-state distortion coefficient is reduced by 0.0076.
Downloads
References
[1] Gridley, Marvin C., and S. H. Walker. "Inlet and Nozzle Technology for 21st Century Fighter Aircraft." Aircraft Engine 1996.
[2] Gridley M C, CahillM J. ACIS Air Induction System Trade Study [M]. US: National Press Club, 2000.
[3] Mcfarlan J D Ⅲ. Lockheed Ma rtin’s joint strike fighter diverterless supersonic inlet [M]. National Press Club, 2000.
[4] Hehs E.JSF diverterless supersonic inlet [EB/OL]. http://www.codeonemaga zine.com /archives /2000 /articles /july- 00 /divertless-1. html,2000.
[5] Tillotson B, Loth E, Dutton J, et al. Experimental Study of a Mach 3 Bump-Compression Flowfield [J]. Journal of Propulsion and Power, 2006, 25(3): 545-554.
[6] Roe P L. Theory of waverider [C] / / AGARD-LS-42,1972: 1-17.
[7] Yang Ying kai. The research of bump inlet design[ C ] / / Russian-Chinese Scientific Co- nference, 2003:9-12.
[8] Vakili A D,Wu J M, Liver P, et al. Flow Control in a Diffusing S-Duct[C]//AIAA Shear Flow Control Conference. Boulder, Colorado.2013.
[9] Wendt B J, Reichert B A. The effects of vortex ingestion on the flow in a diffusing S-duct[J]. AIAA, 1994:2811.
[10] Reichert B A, Wendt B J. An Experimental Investigation of S-Duct Flow Control Using Arrays of Low-Profile Vortex Generators[C]//31st Aerospace Sciences Meeting and Exhibit. Reno, NV. AIAA-93-0018,1993.
[11] Paul A R, Kuppa K, Tripathi N, et al. Experimental and Computational Study of Flow Improvement Through Sigmoid Air Intake Ducts Using Flow Deflector[C]// 26th AIAA Applied Aerodynamics Conference. Honolulu, Hawaii. AIAA 2008-7513.
[12] Garnier E, Leplat M, Monnier J C, et al. Flow Control By Pulsed Jet In A Highly Bended S-Duct[C]// 6th AIAA Flow Control Conference. New Orleans, Louisiana. AIAA 2012-3250.
Downloads
Published
Issue
Section
License
Copyright (c) 2025 Scientific Journal of Intelligent Systems Research
This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.
How to Cite
