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Application of unsteady airfoil theory to rotary wingsA 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.
Document ID
Document Type
Reprint (Version printed in journal)
Kaza, K. R. V. (NASA Lewis Research Center Cleveland; Toledo, University, Toledo, OH, United States)
Kvaternik, R. G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 11, 2013
Publication Date
July 1, 1981
Publication Information
Publication: Journal of Aircraft
Volume: 18
Subject Category
Distribution Limits