Cryogenic Tunnel Pressure Measurements on a Supercritical Airfoil for Several Shock Buffet Conditions

Steady and unsteady experimental data are presented for several xed geometry conditions from a test in the NASA Langley 0.3-Meter Transonic Cryogenic Tunnel. The purpose of this test was to obtain unsteady data for transonic conditions on a xed and pitching supercritical airfoil at high Reynolds numbers. Data and brief analyses for several of the xed geometry test conditions will be presented here. These are at Reynolds numbers from 6 2 10 6 to 35 2 10 6 based on chord length, and span a limited range of Mach numbers and angles of attack just below and at the onset of shock buet. Reynolds scaling eects appear in both the steady pressure data and in the onset of shock buffet at Reynolds numbers of 15 2 10 6 and 30 2 10 6 per chord length.