DID YOU KNOW? DTIC has over 3.5 million final reports on DoD funded research, development, test, and evaluation activities available to our registered users. Click HERE
to register or log in.
Augmentation of Fighter-Aircraft Performance by Spanwise Blowing over the Wing Leading Edge,
NATIONAL AERONUATICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER
Spanwise blowing over the wing canard of a 135 model of a close-coupled-canard fighter-airplane configuration similar to the Kfir-C2 was investigated experimentally in low-speed flow. Tests were conducted at airspeeds of 30 msec Reynolds number of 180000 based on mean aerodynamic chord with angle-of-attack sweeps form -8 deg to 60 deg, and yaw-angle sweeps from -8 deg to 36 deg at fixed angles of attack 0 deg, 10 deg, 20 deg, 25 deg, 30 deg, and 35 deg. Significant improvement in lift-curve slope, maximum lift, drag polar and laterallimit. In spite of the highly swept 60 deg leading edge, the efficiency of the lift augmentation by blowing was relatively high and was found to increase with increasing blowing momentum on the close-coupled-canard configuration. Interesting possibilities of obtaining much higher efficiencies with swirling jets were indicated. Author
This article is from 'Aerodynamics of Vortical Type Flows in Three Dimensions: Conference Proceedings Held at Rotterdam, Netherlands on 25-28 April 1983,' AD-A135 157, p33-1-33-26.