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The theoretical wave drag of some bodies of revolution L E Fraenkel R M No 2842
Evaporation from the surface of a body in an airstream with particular reference to
Experiments on the flow into a swept leadingedge intake at zero forward speed with
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Aero aerodynamic centre aerofoil aircraft angle approximation aspect ratio Biconvex body boundary condition boundary layer calculated cent chord chordwise cone constant corresponding critical Mach curves delta wing derivatives distributed suction downwash drag coefficient duct effect equation experimental flat plate formulae free-stream function given incompressible flow increase intake integration laminar boundary layer laminar flow leading-edge lift coefficient lift distribution Lower surface Mach number maximum measured method mid-chord NACA obtained parabolic profile parameter pitching moment pitot plan form porous leading edge porous surface pressure distribution pressure gradient rate of suction Reynolds number root chord shown in Fig slot solution span spanwise speed static subsonic suction quantities supersonic supervelocity swept wing swept-back wings TABLE tests theory trailing edge transition position turbulent two-dimensional upper surface values variation velocity distribution velocity potential Wind Tunnel zero incidence