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<p>A method for experimentally determining the adiabatic wall temperature and recovery factor in high-speed flows through the use of IR thermography is presented. This involves characterizing the heat flux–wall temperature relationship across multiple wind tunnel tests at varying wall temperatures. The method yields values on a per-pixel basis, making it applicable to complex flows. Consequently, this allows for the calculation of an accurate Stanton number based on the local adiabatic wall temperature. The technique is demonstrated in a Mach 2.3 indraft facility, initially focusing on a turbulent boundary layer and subsequently on a more complex swept shock–boundary layer interaction. To demonstrate the relevance of this method, the local adiabatic wall temperature approach is compared to the commonly used simplifying assumption of a constant adiabatic wall temperature based on the turbulent flat-plate boundary layer recovery factor. For the demonstration cases, a significant variation in adiabatic wall temperature was measured across the domain. It is then shown that neglecting this variation leads to substantial errors in both trend and magnitude of the Stanton number. These errors are particularly pronounced when the wall-to-recovery temperature ratio <InlineEquation ID="IEq1"> <EquationSource Format="TEX">\(T_w\)</EquationSource> <EquationSource Format="MATHML"><math> <msub> <mi>T</mi> <mi>w</mi> </msub> </math></EquationSource> </InlineEquation>/<InlineEquation ID="IEq2"> <EquationSource Format="TEX">\(T_r\)</EquationSource> <EquationSource Format="MATHML"><math> <msub> <mi>T</mi> <mi>r</mi> </msub> </math></EquationSource> </InlineEquation> is close to unity.</p>

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A method for determining adiabatic wall temperature in high-speed flows

  • 期刊论文

  • 发表日期：

    2026年7月11日

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  • Max Z. Vitols,
  • James A. S. Threadgill,
  • Jesse C. Little

摘要

A method for experimentally determining the adiabatic wall temperature and recovery factor in high-speed flows through the use of IR thermography is presented. This involves characterizing the heat flux–wall temperature relationship across multiple wind tunnel tests at varying wall temperatures. The method yields values on a per-pixel basis, making it applicable to complex flows. Consequently, this allows for the calculation of an accurate Stanton number based on the local adiabatic wall temperature. The technique is demonstrated in a Mach 2.3 indraft facility, initially focusing on a turbulent boundary layer and subsequently on a more complex swept shock–boundary layer interaction. To demonstrate the relevance of this method, the local adiabatic wall temperature approach is compared to the commonly used simplifying assumption of a constant adiabatic wall temperature based on the turbulent flat-plate boundary layer recovery factor. For the demonstration cases, a significant variation in adiabatic wall temperature was measured across the domain. It is then shown that neglecting this variation leads to substantial errors in both trend and magnitude of the Stanton number. These errors are particularly pronounced when the wall-to-recovery temperature ratio \(T_w\) T w / \(T_r\) T r is close to unity.