An investigation was made to determine the lifting effectiveness and flow requirements of blowing over the trailing-edge flaps and ailerons on a large-scale model of a twin-engine, propeller-driven airplane having a high-aspect-ratio, thick, straight wing. With sufficient blowing jet momentum to prevent flow separation on the flap, the lift increment increased for flap deflections up to 80 deg (the maximum tested). This lift increment also increased with increasing propeller thrust coefficient. The blowing jet momentum coefficient required for attached flow on the flaps was not significantly affected by thrust coefficient, angle of attack, or blowing nozzle height.
Large-Scale Wind-Tunnel Tests of an Airplane Model with an Unswept, Aspect-Ratio-10 Wing, Two Propellers, and Blowing Flaps
1958
52 pages
Report
Keine Angabe
Englisch
Aerodynamics , Boundary layer separation , Trailing edge flaps , Wind tunnel tests , High aspect ratio , Externally blown flaps , Lift , Boundary layer control , Blowing , Flapping , Jet flow , Rectangular wings , Separated flow , Unswept wings , Aircraft models , Ailerons , Angle of attack , Thrust , Aerodynamic configurations , Aerodynamic coefficients
Engineering Index Backfile | 1959
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