An airfoil which has particular application to the blade or blades of rotor aircraft such as helicopters and aircraft propellers is described. The airfoil thickness distribution and camber are shaped to maintain a near zero pitching moment coefficient over a wide range of lift coefficients and provide a zero pitching moment coefficient at section Mach numbers near 0.80 and to increase the drag divergence Mach number resulting in superior aircraft performance.
Family of airfoil shapes for rotating blades
01.11.1983
Sonstige
Keine Angabe
Englisch
Family of Airfoil Shapes for Rotating Blades
NTIS | 1982
|Family of Airfoil Shapes for Rotating Blades
NTIS | 1982
|