## Report, Volume 958U.S. Government Printing Office, 1950 - Aeronautics |

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958 LAMINAR MIXING absolute coefficient CD accurate ap Ames Aeronautical Laboratory Angle of attack approximating equation assumption axis BASIC EQUATIONS boundary conditions Calif coefficient of viscosity COMMITTEE FOR AERONAUTICS COMPRESSIBLE FLUID conservation of mass coordinates is independent corresponding Reynolds number Crocco refer curves dead-air region density Designation Sym Director equa equation 16 FLUID By Dean free-stream Mach number function u*(f held constant hence incompressible increasing Mach number independent variables integral equation iteration process Karman and Tsien laborious iteration laminar boundary layer Langley Field linear differential equation linear variation mixing layer mixing-layer thickness Moffett Field momentum equation ordinary differential equation Pitch point where mixing Pr=l Prandtl quadratures REPORT 958 LAMINAR shown in figure side of equation solution stream function SYMBOLS tion Tsien reference Unit Abbrevia United States Navy variation of viscosity velocity distribution calculations velocity profile Vice President viscosity with temperature zero Mach number