Effect of the angle of attack on the YF-16 inlet
by I.H. Ibrahim, E.Y.K. Ng, L.W.K. Wong
International Journal of Aerodynamics (IJAD), Vol. 1, No. 2, 2010

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.

Online publication date: Wed, 05-Jan-2011

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