A Study of the Effects of Reynolds Number and Mach Number on Constant Pressure Coefficient Jump for Shock-induced Trailing-edge Separation, Volume 4090
What people are saying - Write a review
We haven't found any reviews in the usual places.
Other editions - View all
0.3-Meter Transonic Cryogenic 1/9-Scale Model airfoil and planform airfoil curvature airfoil parameters ALPHA=1 Angle of attack bi-convex airfoils boundary layer characteristics cn cn cn coco configurations CQ CQ CQ CQCQ Curve fits data base defined determined DFVLR R-4 Dimensional Flow Eh Eh Error Band Figure 15 Figure 17 finite wings flight test free stream Mach induced trailing edge Influence of Reynolds Langley 0.3-Meter Transonic Mach and Reynolds Mach number normal MBB Wing/Body NACA 0012 Airfoil NASA Number and Mach ONERA M-6 Wing Pearcey planform geometry prediction Pressure Coefficient Jump Pressure Distributions Reference shifted C plots shock induced trailing 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 flaps trailing edge separation Transonic Cryogenic Tunnel trend two-dimensional data two-dimensional flow upper surface crest wind tunnel Wing twist X/C(re f