A Study of the Effects of Reynolds Number and Mach Number on Constant Pressure Coefficient Jump for Shock-induced Trailing-edge Separation
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0.3-Meter Transonic Cryogenic airfoil and planform airfoil curvature ALPHA ALPHA=2 Angle of attack bi-convex airfoils boundary layer camber CAST 10-2/DOA Airfoil characteristics CM CM CM CM cn cn CM cn cn 53 cn cn cn cn S3 configurations Curve fits data base Data in Two-Dimensional data sets defined DFVLR R-4 Error Band Figure 17 flight test induced trailing edge Influence of Reynolds isis isis Langley 0.3-Meter Transonic Mach and Reynolds MBB Wing/Body MBB-A3 D ONERA-D NACA 0012 Airfoil NASA ONERA D Airfoil ONERA M-6 Wing phenomenon planform geometry Reference Reynolds number Shifted C Plots Shifted Cp shock induced trailing Shock Jump shock-induced separation shock-induced trailing-edge separation shown in Figure span station stream Mach number Supercritical Airfoil three-dimensional data three-dimensional flow trailing edge separation Transonic Cryogenic Tunnel trend two-dimensional flow upper surface crest wind tunnel X/C Figure X/C(re f