A clarification is presented on recent work concerning the application of unsteady airfoil theory to rotary wings. The application of this theory may be seen as consisting of four steps: (1) the selection of an appropriate unsteady airfoil theory; (2) the resolution of that velocity which is the resultant of aerodynamic and dynamic velocities at a point on the elastic axis into radial, tangential and perpendicular components, and the angular velocity of a blade section about the deformed axis; (3) the expression of lift and pitching moments in terms of the three components; and (4) the derivation of explicit expressions for the components in terms of flight velocity, induced flow, rotor rotational speed, blade motion variables, etc.
Application of unsteady airfoil theory to rotary wings
Journal of Aircraft ; 18
01.07.1981
Sonstige
Keine Angabe
Englisch
Application of unsteady airfoil theory to rotary wings
AIAA | 1980
|Application of Unsteady Airfoil Theory to Rotary Wings
AIAA | 1981
|