Flat Plate Boundary Layer Transition in the LUT Gun Tunnel; a Transition-Radiated Aerodynamic Noise Correlation for Gun Tunnel and Conventional Wind Tunnel Data at Supersonic and Hypersonic Mach Numbers

摘要

Flat plate boundary layer transition data from the LUT gun tunnel and zero pressure gradient data from three further gun tunnels are analysed on the basis of the Pate and Schueler aerodynamic noise correlation of conventional wind tunnel data, and are shown to be consistent with it. Thus aerodynamic noise from the test facility is again the main influencing factor on transition. A wall to adiabatic wall temperature ratio effect is identified which is not explicit in the original correlation of data for adiabatic surfaces. This is attributed to the well known wall cooling effect on boundary layer transition.