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

Authors: I.H. Ibrahim, E.Y.K. Ng, L.W.K. Wong

Addresses: School of Mechanical and Aerospace Engineering, Nanyang Technological University, 50 Nanyang Avenue, Singapore 639798 Singapore. ' School of Mechanical and Aerospace Engineering, Nanyang Technological University, 50 Nanyang Avenue, Singapore 639798 Singapore. ' Air Logistic Department, 2 Air Logistic Department, 506 Airport Road, Singapore 534395 Singapore

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.

Keywords: angle of attack; curved diffusers; subsonic diffusers; pressure recovery; distortion; YF-16 aircraft; fuselage-shielded inlet; normal shock inlet; intake aerodynamics; flow separation; flow patterns; manoeuvrability.

DOI: 10.1504/IJAD.2010.037926

International Journal of Aerodynamics, 2010 Vol.1 No.2, pp.169 - 191

Published online: 05 Jan 2011 *

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