Heat transfer and skin friction in a Mach 6: Inlet flow
Conference Paper
Overview
Overview
abstract
1999, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. An experimental investigation was carried out to measure skin friction and heat flux in a Mach 6 freejet test of a scramjet inlet component. The investigation was performed in the Air Force Research Laboratorys Mach 6 wind- tunnel; The model simulated a movable cowl mounted on a sidewall compression plate. The skin friction gaugeuseda floating element supported by a miniature cantilever beam which is instrumented with strain gauges to measure the beam deflection. Coaxial thermocouples were used to measure the wall temperature from which the heat flux was.deduced. Several measurements.were taken on the sidewall compression plate without the cowl lip, effectively a flat plate. This information was then used to determine the boundary layer transition point and the influence on the boundary layer profile. The data is useful both for drag assessment of scramjet inlets and for CFD turbulence model development. Comparison between the measured skin friction and two turbulent boundary layer skin friction correlations, the Van Driest II and Spalding and Chi, showed that the Spalding and Chi more accurately matched the measured conditions. A Reynolds analogy factor of 1.29 is required to match skin friction data to heat flux measurements.
