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Investigation to optimize the passive shock wave-boundary layer control for supercritical airfoil drag reductionThe optimization of passive shock wave/boundary layer control for supercritical airfoil drag reduction was investigated in a 3 in. x 15.4 in. Transonic Blowdown Wind Tunnel. A 14% thick supercritical airfoil was tested with 0%, 1.42% and 2.8% porosities at Mach numbers of .70 to .83. The 1.42% case incorporated a linear increase in porosity with the flow direction while the 2.8% case was uniform porosity. The static pressure distributions over the airfoil, the wake impact pressure data for determining the profile drag, and the Schlieren photographs for porous surface airfoils are presented and compared with the results for solid-surface airfoils. While the results show that linear 1.42% porosity actually led to a slight increase in drag it was found that the uniform 2.8% porosity can lead to a drag reduction of 46% at M = .81.
Document ID
19840008067
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Nagamatsu, H. T.
(Rensselaer Polytechnic Inst. Troy, NY, United States)
Ficarra, R.
(Rensselaer Polytechnic Inst. Troy, NY, United States)
Orozco, R.
(Rensselaer Polytechnic Inst. Troy, NY, United States)
Date Acquired
September 4, 2013
Publication Date
December 8, 1983
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:173276
NASA-CR-173276
Accession Number
84N16135
Funding Number(s)
CONTRACT_GRANT: NAG1-330
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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