WIND-TUNNEL INVESTIGATION OF FAVORABLE INTERFERENCE TO INCREASE LIFT-DRAG RATIOS OF SUPERSONIC AIRCRAFT: PART II: AN OPTIMIZED WING-BODY-INLET CONFIGURATION.
DAVID TAYLOR MODEL BASIN WASHINGTON D C
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The results of wind-tunnel tests conducted at a Mach number of 2.87 to investigate favorable interference effects on wing-body-inlet configurations are presented. The engine air inlet location and the body indentation angle for maximum lift increments were determined. These favorable lift increments correspond to about 20 percent of the cruise lift required for an attack aircraft. A fence, attached to the wing to reflect the shock wave emanating from the engine air inlet and to intensify the pressure field, increased the inboard lift but not sufficiently to overcome the resulting loss in lift ffrom the outboard section of the wing. Author