Evaluation of the surface reflective visualization (SRV) system is conducted using both experimental and numerical simulation techniques. Experimental measurements are made with a spherical five-hole probe utilizing a local look-up calibration algorithm. These data are used to determine the location of the primary vortex core as well as the spanwise integrated density gradient. The numerical simulation technique employs a fast ray tracing algorithm and schlieren system simulation to determine the integrated density gradient distribution over the surface of the wing. The initial numerical flow solution used in the simulation is generated via a computational code based on a finite volume discretization of the three-dimensional conservation law form of the Euler equations. Both the experimental and numerical validation procedures support initial interpretations of SRV images of the compressible vortical flowfield above the lee side of the delta wing. The experimental results of the probe explorations supported the geometric interpretation of the images. The numerical simulation demonstrated that the SRV technique can, indeed, be expected to visualize the embedded crossflow shock existing at transonic flow conditions. Nomenclature c r = root chord, 120 mm / = focal length / = illumination n = refractive index y le = local spanwise distance from root chord to leading edge Z h = length of integration path K = Gladstone-Dale constant
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