LOW SPEED WIND TUNNEL TESTS ON A ONE-SEVENTH SCALE MODEL OF THE H.126 JET FLAP AIRCRAFT

摘要

Low speed wind tunnel tests were performed on a one-seventh scale model of the British H.126 jet flap research aircraft over a range of jet momentum coefficients.nThe primary objective was to compare model aerodynamic characteristics with those of the aircraft, with the intent to provide preliminary data needed towards establishing small-to-full scale correlating techniques on jet flap V/STOL aircraft configurations. Lift and drag coefficients from the model and aircraft tests were found to be in reasonable agreement. The pitching moment coefficient and trim condition correlation was poor.nA secondary objective was to evaluate a modified thrust nozzle having thrust reversal capability. The results showed there was a considerable loss of lift in the reverse thrust operational mode because of increased nozzle-wing flow interference.nA comparison between the model simulated H.126 wing jet efflux and the model uniform pressure distribution wing jet efflux indicated, generally, no more than 5％ loss in weight flow rate.