Ibrahim, I.H. , Ng, E.Y.K. and Wong, L.W.K. (2010) Effect of the angle of attack on the YF-16 inlet. International Journal of Aerodynamics, 1(2), pp. 169-191. (doi: 10.1504/IJAD.2010.037926)
Full text not currently available from Enlighten.
Abstract
A k-ε numerical analysis of a fuselage-shielded inlet similar to that of the YF-16 was conducted. The simulations were conducted at Mach 0.6 at -10° to 40° angles of attack. Results were validated with experimental values obtained in the 90° bending pipe and circular S-duct. Pre-entry separation effects were simulated by a flat plate and offset by the diverter height. Results showed that the pressure recoveries resembled that of the YF-16 inlet, where negligible losses were up to 30° angle of attack (AOA). The increase in the angle of attack also resulted in the diminishing strength of the twin swirls.
| Item Type: | Articles |
|---|---|
| Status: | Published |
| Refereed: | Yes |
| Glasgow Author(s) Enlighten ID: | Ibrahim, Dr Imran |
| Authors: | Ibrahim, I.H., Ng, E.Y.K., and Wong, L.W.K. |
| College/School: | College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity |
| Journal Name: | International Journal of Aerodynamics |
| Publisher: | Inderscience |
| ISSN: | 1743-5447 |
| ISSN (Online): | 1743-5455 |
University Staff: Request a correction | Enlighten Editors: Update this record
Deposit and Record Details
Deposit and Record Details