In an attempt to find an aerodynamic means of counteracting the transonic trim change of a fighter airplane, lower surface spoilers were tested on a 0.055-scale wind-tunnel model. The Mach number range of the tests was 0.8 to 1.2 at Reynolds numbers of approximately 4 million. Although the spoilers produced a moderate decrease in the trim change at low altitudes, they also produced a large increase in drag. Pressure-distribution tests with external fuel tanks showed large pressure changes on the lower surface of the wing due to the tanks.
Effect of Lower Surface Spoilers on the Transonic Trim Change of a Wind-Tunnel Model of a Fighter Airplane Having a Modified Delta Wing
1959
54 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Military Sciences , Wind tunnel tests , Fighter aircraft , Transonic speed , Scale models , Aerodynamic balance , Aerodynamic characteristics , Delta wings , Wind tunnel models , Reynolds number , Pressure distribution , Mach number , Aerodynamic stability , Spoilers , External tanks , Drag