A wind-tunnel investigation of the NASA SC(2)-0012 airfoil has been conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel. This investigation supplements the two-dimensional airfoil studies of the Advanced Technology Airfoil Test Program. The Mach number was varied from 0.60 to 0.84. The stagnation temperature and pressure were varied to provide a Reynolds number range from 6 to 40 x 10 to the 6th power based on a 6.0-in. (15.24-cm) airfoil chord. No corrections for wind-tunnel wall interference have been made to the data. The aerodynamic results are presented as integrated force and moment coefficients and pressure distributions without any analysis.
High Reynolds Number Tests of the NASA (National Aeronautics and Space Administration) SC(2)-0012 Airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel
1987
58 pages
Report
Keine Angabe
Englisch
Aerodynamics , Airfoils , Transonic wind tunnels , Wind tunnel tests , Cryogenic wind tunnels , High reynolds number , Supercritical airfoils , Symmetrical bodies , Aerodynamic characteristics , Force distribution , Mach number , Moment distribution , Pressure distribution , Two dimensional flow , Wall flow