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angle at base base flows base pressure coefficient boattail at free boattail at Mq boattail base boattail flows boattail pressure distribution boattail pressure drag boattail trailing edge boattails at subsonic boundary layer calculation boundary layers separating calculation procedure combining an inviscid Comparison of theoretical computer programs Conical Afterbodies conical boattail convergence displacement thickness distributions on boattails dividing streamline Dlsmooth Effect of smoothing Eight points smoothed equations experimental boattail pressure fourth iteration free stream Mach initial flow turning initial turning angle inviscid analysis inviscid flow program iteration procedure iterative calculation jet off condition jet pressure ratios Lewis Research Center NASA number of 0.4 number of points numbers with turbulent pressure drag coefficients recompression region for base reversed flow region separated flow separation point shown in figure static pressure stream Mach number SUBSONIC FLOW Supersonic theoretical and experimental trailing edge angle turbulent boundary layers viscous effects including wake wake-body zero velocity line