Computational Investigation of Inlet Distortion at High Angles of Attack
Author:
Affiliation:
1. School of Mechanical and Aerospace Engineering, Queen’s University Belfast, Belfast, Northern Ireland BT9 5AH, United Kingdom
2. Powerplant & Systems, Powerplant & Systems, Bombardier Aerospace, Belfast, Northern Ireland BT3 9DZ, United Kingdom
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.C031789
Reference18 articles.
1. AlbersJ. A. “Effect of Inlet Lip Geometry on Predicted Surface and Flow Mach Number Distributions,” NASA TN-D-7446, 1973.
2. HodderB. K. “An Investigation of Engine Influence on Inlet Performance,” NASA CR-166136, 1981.
3. Comparison of model and full scale inlet distortions for subsonic commercial transport inlets
4. Reynolds number and fan/inlet coupling effects on subsonic transportinlet distortion
5. LarkinM. J.SchwiegerP. S. “Ultra High Bypass Nacelle Aerodynamics—Inlet Flow-Through High Angle of Attack Distortion Test,” NASA CR-189149, July 1992.
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