Abstract
The pressure difference across the wing and leading-edge extension (LEX) of a rigid 6% scale model of an F/A-18 was measured, and the integrated static and rms loads were computed. The total loads on the aircraft were obtained using a sting-mounted balance from which the body loads can be deduced by subtracting the LEX and wing loads. The effects of Mach number and angle of attack were analyzed and results for M = 0.25, 0.6, and 0.8 at a = 20‐35 deg are presented. The effectiveness of the LEX as a highlift device is demonstrated by comparing the individual lift contributions from the wing and LEX at different angles of attack and Mach numbers. It is shown that the LEX vortex can generate large nonlinear static lift while inducing high unsteady lift on the aircraft.
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