Calculation of the Pressure Distribution on Axisymmetric Boattails Including Effects of Viscous Interactions and Exhaust Jets in Subsonic Flow |
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30 conical boattail angle at base base flows base pressure coefficient boattail at free boattail base boattail pressure distribution boattail pressure drag boattail trailing edge boundary layer calculation boundary layers separating calculation procedure Comparison of theoretical computer programs Conical Afterbodies convergence D)smooth Data from ref Dimensionless axial distance Dimensionless radius displacement thickness dividing streamline Effect of smoothing eight points smoothed equations experimental boattail pressure flow turning angle fourth iteration free stream Mach initial flow turning initial turning angle inviscid analysis iteration procedure iterative calculation jet off condition jet pressure ratios Lewis Research Center Mach number Mo NASA number Mo 0.8 number of 0.4 number of points points smoothed 0.767 pressure drag coefficients recompression reversed flow region separated flow separation point shown in figure smoothed for Mo static pressure stream Mach number SUBSONIC FLOW Supersonic theoretical and experimental trailing edge angle transonic turbulent boundary layers wake-body zero velocity line