Experimental and Numerical Investigation of a Fluidically Variable Hypersonic Inlet
Author:
Affiliation:
1. Nanjing University of Aeronautics and Astronautics, 210016 Nanjing, People’s Republic of China
2. AECC Commercial Aircraft Engine Co., Ltd., 200241 Shanghai, People’s Republic of China
Funder
China Postdoctoral Science Foundation
National Natural Science Foundation of China
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.J055767
Reference24 articles.
1. Progress in Astronautics and Aeronautics;Van Wie D. M.,2000
2. JohnsonH. J.MontoyaE. J. “Local Flow Measurements at the Inlet Spike Tip of a Mach 3 Supersonic Cruise Airplane,” NASA TN D-6987, May 1973.
3. Flow Oscillation Characteristics in Conical Cavity with Multiple Disks
4. Numerical and experimental analysis of a hypersonic variable geometry inlet
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