Experimental aerodynamic investigations of the NASA Common Research Model have been conducted in the NASA Langley National Transonic Facility, the NASA Ames 11-ft wind tunnel, and the European Transonic Wind Tunnel. In the NASA Ames 11-ft wind tunnel, data have been obtained at only a chord Reynolds number of 5 million for a wing/body/tail = 0 degree incidence configuration. Data have been obtained at chord Reynolds numbers of 5, 19.8 and 30 million for the same configuration in the National Transonic Facility and in the European Transonic Facility. Force and moment, surface pressure, wing bending and twist, and surface flow visualization data were obtained in all three facilities but only the force and moment and surface pressure data are presented herein.
Comparison of the NASA Common Research Model European Transonic Wind Tunnel Test Data to NASA Test Data
2015
15 pages
Report
Keine Angabe
Englisch
Fluid Mechanics , Test Facilities & Equipment , Air Transportation , Aerodynamics , Comparison , International cooperation , Wind tunnel tests , Transonic wind tunnels , Aircraft models , Supercritical wings , Transonic flow , Data correlation , Commercial aircraft , Data mining , Twisting , Bending , Data processing , Reynolds number , Body-wing and tail configurations , Angle of attack , Mach number , Computational fluid dynamics , Pressure measurement , Aerodynamic drag