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 , surface pressure and wing bending and twist data are presented herein .