FLIGHT-TEST INVESTIGATION OF THE AERODYNAMIC CHARACTERIS¬TICS AND FLOW INTERFERENCE EFFECTS ABOUT THE AFT FUSELAGE OF THE F-111A AIRPLANE

摘要

Static pressure measurements were made on the aft fuselage of an F-111A airplane to determine local flow characteristics and engine/airframe inter¬action effects. Data were obtained over the Mach number range from 0.5 to 2.0. Aspiration effects associated with low ejector nozzle expansion ratios reduced the local pressure coefficients particularly on the interfairing but also extending to the trailing edge of the nacelle. The presence of after¬bodies also affected the behavior of the air flowing into and about the ejector nozzle.nPressures about the aft fuselage were improved by an increase in primary nozzle area at a supersonic speed.nA comparison of wind-tunnel and flight-test results showed generally good agreement, although there was a large disparity in pressure level about the ejector nozzle. However, the shape of the data curves and the local flow behavior were basically similar.