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A potential-flow/boundary-layer method for calculating subsonic and transonic airfoil flow with trailing-edge separationThe development of a potential-flow/boundary-layer method for calculating subsonic and transonic turbulent flow past airfoils with trailing-edge separation is reported. A moment-of-momentum integral boundary-layer method is used which employs the law-of-the-wall/law-of-the-wake velocity profile and a two-layer eddy-viscosity model and ignores the laminar sublayer. All integrals across the boundary layer are obtained in closed form. Separation is assumed to occur when the shearing-stress velocity vanishes. A closed-form solution is derived for separated-flow regions where the shearing stress is negligible. In the potential-flow method, the exact form of the airfoil boundary condition is used, but it is applied at the chord line rather than the airfoil surface. This allows the accurate computation of flow about airfoils at large angles of attack but permits the use of body-oriented Cartesian computational grids. The governing equation for the perturbation velocity potential contains several terms in addition to the classical small-disturbance terms.
Document ID
19810018509
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Barnwell, R. W. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
June 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-81850
L-14255
Accession Number
81N27047
Funding Number(s)
PROJECT: RTOP 505-31-33-05
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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