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- W2598298809 abstract "This report presents the results of the experimentalinvestigation on a NAL-114-36-00 symmetric supercritical airfoil developed at NAL and tested in O.3m wind tunnel over a free stream Mach number range of 0.53 to 0.85 and angle of incidence range of 0° to 4°. Model surface pressures were measured and compared with the theoretical pressure distribution of the same airfoil and also of baseline airfoil NACAO012. Comparison showed that the symmetric supercritical aerofoil was shock free atdesign Mach number and angle of incidence, matching withtheoretical predictions whereas NACA0012 airfoil had strongshock for the same design conditions ." @default.
- W2598298809 created "2017-04-07" @default.
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- W2598298809 date "1989-04-01" @default.
- W2598298809 modified "2023-09-23" @default.
- W2598298809 title "Tests on NAL-114-26-00 symmetric supercritical airfoil in 0.3MWind tunnel" @default.
- W2598298809 hasPublicationYear "1989" @default.
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