EXPLORATORY WIND-TUNNEL INVESTIGATION TO DETERMINE THE LIFT EFFECTS OF BLOWING OVER FLAPS FROM NACELLES MOUNTED ABOVE THE WING

摘要

An exploratory wind-tunnel Investigation has been made to determine the lift effects of blowing from nacelles over the upper surface of flaps on a model having a delta wing of aspect ratio 3 several flap conditions were examined. High-pressure air was blown from an external-pipe arrange¬ment supported above the wing to simulate jet-engine exhaust. The jet-momentum-coefficient range was from 0 to 3.0and the model angle of attack was 0°.nThe results of this limited investigation show that values of jet-circulation lift coefficient larger than the jet reaction were produced with blowing over flaps from nacelles mounted above the wing. The use of double slotted flaps with the gap unsealed between the flaps and wing had a large detrimental effect on the lift capabilities. With these gaps sealed, larger lift coefficients were obtained when fantails were added to the nacelles. The longitudinal trim problems created by large diving moments were similar to those encountered with other jet-augmented-flap systems.