Experimental Investigation of the Impact Probe Method for Determining Local Skin Friction in the Presence of an Adverse Pressure Gradient for a Range of Mach Numbers from 1.70 to 2.75

摘要

The results are presented of an experimental program to determine the feasibility of using a surface impact probe to measure values of local skin friction in a turbulent boundary layer over a range of Mach Numbers and pressure gradients. The work is an extension of previous work on adverse pressure gradients which was done at a nominal Mach Number of 2.0. The present investigation was conducted on an adiabatic flat surface which formed the test-section floor of a variable Mach Number supersonic wind tunnel. The Mach Numbers ranged from 1.70 to 2.75 with adverse pressure gradients of zero to 1.57 psi/in. (Author)