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40 percent less Aero angle of 60 angles of yaw arbi arbitrary shape Beckwith Bernoulli's equation bow shock chordwise velocity profile Committee for Aeronautics COMPARISON WITH EXPERIMENTAL compressible flow compressible laminar boundary CYLINDERS IN SUPERSONIC cylinders of arbitrary data for small diagrs displacement thickness equation 15 equations 29 evaluated EXPERIMENTAL DATA heat conduction integral method INVESTIGATION OF LAMINAR Ivan L55F09 National Advisory laminar boundary layer LAMINAR HEAT TRANSFER Langley Field layer on yawed measured values mental data method is applied method is presented NACA RM L55F09 National Advisory Committee number of 6.9 obtained from equation Prandtl number predicted heat transfer present method recovery factor RM L55F09 National sions are derived stagnation line stream Mach number SUPERSONIC FLOW THEORETICAL INVESTIGATION theoretically predicted heat transfer and recovery TRANSFER ON YAWED transfer rates trary wall temperature wall temperature distribution yaw angle yawed circular cylinder yawed infinite cylinders zero heat transfer