Abstract
The article presents a flow field visualization study on a typical payload shroud at transonic Mach numbers range. The numerical simulation over the heat shield is carried out by solving axisymmetric, turbulent, compressible, Reynolds-averaged Navier—Stokes equations. The closure of these equations is achieved using the Baldwin—Lomax turbulence model. The density contour plots are obtained at Mach number 0.80, 0.90, 0.95, and 1.0. The transonic flow field features over the heat shield are captured and compared with the schlieren pictures, and good matching between them is exhibited. The movement of the terminal shock is found to be a non-linear function of freestream Mach number. The location of the shock on the heat shield is also confirmed with the flight data. The numerical studies have shown that the reliable estimation of the transonic flow field can be made in conjunction with the flow visualization technique.
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Schedule a callMore From: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
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