Subsonic Two-dimensional-flow Conditions Near an Airfoil Determined by Static Pressures Measured at the Tunnel Wall

Résumé du livre

This report contains experimental and calculated data concerning Mach number distributions in the flow field of an airfoil. Test data were obtained by means of orifices in the tunnel wall. Reasonably good agreement between theory and experiment (corrected to a stream Mach number of 0) was obtained in incompressible flow. Low-speed flow-field Mach numbers can be extended for use in subcritical Mach numbers by the application of the methods of Prandtl and Ackeret. The flow-field data measured at the tunnel wall appeared to be reasonably representative of conditions at the midspan location at any Mach number when steep pressure gradients on separation did not occur.