Effect of the angle of attack on the YF-16 inlet

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)

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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
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 > Aerospace Sciences
Journal Name:International Journal of Aerodynamics
ISSN (Online):1743-5455

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