Abstract

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 Laboratory’s Mach 6 windtunnel; The model simulated a movable cowl mounted on a sidewall compression plate. The skin friction gauge‘used’a 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.

Talk to us

Join us for a 30 min session where you can share your feedback and ask us any queries you have

Schedule a call

Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.