Historic Background on Flat Plate Turbulent Flow （历史背景对平板湍流）.pdfVIP

Historic Background on Flat Plate Turbulent Flow Skin Friction and Boundary Layer Growth HSR Airframe Technical Review Los Angeles, California February 9 - February 13, 1998 Robert M. Kulfan Boeing Commercial Airplane Group Page 1 Topics • Early Skin Friction Compressibility Prediction Attempts • Skin Friction Prediction Validation Studies • Prediction of Flat Plate Turbulent Layer Growth • Summary / Conclusions Recent CFD validation studies have shown significant variations in viscous drag predictions between the various methods used by the NASA and industry HSCT organizations. The methods include Navier Stokes CFD codes in which the viscous forces are part of the solutions, and predictions obtained from the different fully turbulent flow flat plate skin friction drag equations used by the various organizations. The initial objective of this study was to provide an experimental database of fully turbulent flow skin friction measurements on flat plate adiabatic surfaces at subsonic through supersonic Mach numbers and for a wide range of Reynolds numbers. The database could then be used as the initial Page 2 step in resolving the differences in the viscous predictions. This database,(Ref 1), was originally assembled in 1960 from selected experiments conducted prior to that time period. The criteria used to select the appropriate test data are described in the reference. Data were also found on turbulent boundary layer velocity profiles and it was therefore possible to analyze other boundary layer p