Experimental and numerical investigation of wind tunnel wall interference near Mach one

摘要

Surface pressure measurements on the CAST-10-2/DOA 2 aerofoil, conducted in the IAR 1.5m wind tunnel and supported by CFD simulations, are used to validate some new theoretical analyses of transonic wall intreference. Based on the transonic freeze principle, it is shown that the stream Math number correction is indeterminate near Mach one.