NASA STI Repository (National Aeronautics and Space Administration) · 1988 · 10 citations · 0 references
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EngineeringAerospace EngineeringMechanical EngineeringAerodynamicsAerospace StructuresFluid DynamicsAerodynamic DesignAerodynamic TestingAirfoil TheoryExperimental AerodynamicsExternal AerodynamicsTransonic AerodynamicsAerodynamic Performance TestingAirfoil AerodynamicsMach NumberReynolds NumberSurface PressureSurface Pressure DistributionTransonic Airfoil AerodynamicsTransonic Airfoils
This report presents in graphic and tabular forms the aerodynamic coefficient and surface pressure distribution data for a NASA SC(2)-0714 airfoil tested in the Langley 0.3-Meter Transonic Cryogenic Tunnel. The test was another in a series of tests involved in the joint NASA/U.S. Industry Advanced Technology Airfoil Tests program. This 14% thick supercritical airfoil was tested at Mach numbers from 0.6 to 0.76 and angles of attack from -2.0 to 6.0 degrees. The test Reynolds numbers were 4 million, 6 million, 10 million, 15 million, 30 million, 40 million, and 45 million.