Comparison of Two- and Three-Dimensional Transonic Tests Made in Various Large Wind Tunnels
FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH
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A critical study is reported of testing conditions at transonic speeds and of the validity of the data obtained in various Wind-Tunnels. In two dimensional flow, two models of NACA 0012 and supercritical profiles have been tested as well as three homothetical profiles of NACA 0012. In three dimensional flow, four homothetical models of a typical transport aircraft were successively tested in twelve transonic tunnels commonly used for development tests in various countries. The data are compared in a broad range of Reynolds number 0.3 to 7 millions between Mach number 0.7 and 0.96.
- Test Facilities, Equipment and Methods