NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
A simplified theory of oscillating aerofoils in transonic flow - Review and extensionA simplified theory of the dynamic motion of aerofoils of finite thickness in transonic flow is presented which excludes the effect of shock waves on the aerofoil itself and, thus, is restricted to free stream Mach numbers equal to unity or above. Numerical examples are analyzed for two-dimensional steady and unsteady (including transient) aerofoil motion and three-dimensional steady and unsteady flow over delta wings. The effects of flow separation and improvements in Bernoulli's equation and the surface boundary condition are briefly discussed.
Document ID
19810030541
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Dowell, E. H.
(Princeton University Princeton, N.J., United States)
Date Acquired
August 11, 2013
Publication Date
November 1, 1980
Publication Information
Publication: Aeronautical Quarterly
Volume: 31
Subject Category
Aerodynamics
Accession Number
81A14945
Funding Number(s)
CONTRACT_GRANT: NSG-2194
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available