Surface Pressure Measurements on the Wing of a Wind Tunnel Model During Steady Rotation.

摘要

Wind tunnel measurements were conducted to determine the nature of the pressure distribution over the wing of a model of a basic training aircraft for a range of angles of attack and rotation rates representative of aircraft spinning conditions. The tests were carried out as part of a collaborative program organized through The Technical Cooperation Program and were conducted in the Spin Research Facility at the NASA Langley Research Center. Software for displaying the surface pressure distributions was developed at the Aeronautical Research Laboratory. This report presents pressure coefficient data obtained during the program, in both numerical and graphical form.