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Numerical study of porous airfoils in transonic flowA numerical study was made to examine the effect of a porous surface on the aerodynamic performance of a transonic airfoil. The pressure jump across the normal shock wave on the upper surface of the airfoil was reduced by making the surface below the shock porous. The weakened shock is preceded by an oblique shock at the upstream end of the porous surface where air is blown out of the cavity. The lambda shock structure shown in the numerical result qualitatively agrees with that observed in the wind tunnel. According to the present analysis, the porous airfoil has a smaller drag and a higher lift than the solid airfoil.
Document ID
19850019516
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Chen, C. L. (Colorado Univ. Boulder, United States)
Chow, C. Y. (Colorado Univ. Boulder, United States)
Holst, T. L. (NASA Ames Research Center Moffett Field, CA, United States)
Vandalsem, W. R. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 5, 2013
Publication Date
May 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
REPT-85209
NAS 1.15:86713
NASA-TM-86713
Accession Number
85N27828
Funding Number(s)
PROJECT: RTOP 505-31-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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