![]() For each Mach number, multiple jet temperatures were investigated. Two additional nozzles were examined having design Mach numbers of 1.36 and 1.63. Operating points from the well-known supersonic jet data of Seiner et al.\cite for heated Mach 2 jets were used as a starting point for the matrix of cases examined in the current experiments using a geometrically similar Mach 2 nozzle. View Video Presentation: Experiments were conducted using modern measurement techniques to produce a comprehensive set of aerodynamic and thermodynamic data for turbulent supersonic jets. Calculations were obtained for blowing ratios of 0, 1, and 2, and are compared to experimental results. ![]() ![]() ![]() In addition to releasing the Set Point 42 data, this paper also contains a multiphysics analysis of the film cooling configuration, employing Reynolds-averaged Navier-Stokes calculations for the flow and a conjugate heat transfer method to model conduction to the test article structure. This paper contains the Set Point 42 data set where the square nozzle was operating at a jet Mach number of approximately 0.3, a jet static temperature ratio of 2.7, and cooling film blowing ratios from 0 to 3.0. The third data set, known as Set Point 42, was held back to provide blind data for the 2021 AIAA Propulsion Aerodynamics Workshop. Two of the three Set Points of data were published as AIAA 2020-1230 and NASA/TM-2019-220227. Data were collected at three distinct heated nozzle operating set points and over a range of film cooling blowing ratios. Thermocouples and an infrared camera were also used to make measurements of surface temperatures. Particle Image Velocimetry and spontaneous rotational Raman scattering spectroscopy were used to acquire high quality, spatially-resolved measurements of turbulent velocity statistics and temperature statistics of the film cooling flow, respectively. View Video Presentation: A multiphysics computational analysis of a film cooling flow is compared to data collected from an experiment consisting of a square heated nozzle flow blowing over a flat plate equipped with three patches of inclined cooling holes.
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