Computational Investigation of Inlet Distortion at High Angles of Attack-Reference-Cited by-同舟云学术

Computational Investigation of Inlet Distortion at High Angles of Attack

Published:2014-03 Issue:2 Volume:51 Page:361-376
ISSN:0021-8669
Container-title:Journal of Aircraft
language:en
Short-container-title:Journal of Aircraft

Author:

Kennedy Stefan¹,Robinson Theresa¹,Spence Stephen¹,Richardson John²

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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