Two-Dimensional Nonadiabatic Injection into a Supersonic Freestream

Turbulence and mean flow measurements were acquired downstream of a normal, supersonic (Mach 1.6), two-dimensional, slot injection into Mach 2.9 flow (Re/m = 16 106). An adiabatic (Tti/Tt = 1.0) and two nonadiabatic injection cases (Tti/Tt = 1.11 and Tti/Tt = 0.93) were studied. Multiple-overheat cross-film anemometry and conventional mean flow probes, as well as instantaneous schlieren photography, were utilized to study the turbulent mixing layer. The mean flow data included the pitot, cone-static, and Mach number profiles. The measured turbulence data included Reynolds shear stresses and turbulence intensities (mass flux and total temperature). The flow visualizations highlighted the physical phenomena of the flow as well as the associated turbulent structure that existed in the mixing layer. The injection and wall temperature were found to have a strong influence on the near wall (the bottom-half of the mixing layer relative to the wall) mean and statistical turbulent flow properties.

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