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The passage of an infinite swept airfoil through an oblique gustAn approximate solution is reported for the unsteady aerodynamic response of an infinite swept wing encountering a vertical oblique gust in a compressible stream. The approximate expressions are of closed form and do not require excessive computer storage or computation time, and further, they are in good agreement with the results of exact theory. This analysis is used to predict the unsteady aerodynamic response of a helicopter rotor blade encountering the trailing vortex from a previous blade. Significant effects of three dimensionality and compressibility are evident in the results obtained. In addition, an approximate solution for the unsteady aerodynamic forces associated with the pitching or plunging motion of a two dimensional airfoil in a subsonic stream is presented. The mathematical form of this solution approaches the incompressible solution as the Mach number vanishes, the linear transonic solution as the Mach number approaches one, and the solution predicted by piston theory as the reduced frequency becomes large.
Document ID
19740018312
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Adamczyk, J. L. (United Aircraft Corp. East Hartford, CT, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1974
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-2395
Accession Number
74N26425
Funding Number(s)
CONTRACT_GRANT: NAS1-11557
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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