Technical Memorandum - National Advisory Committee for Aeronautics, Volumes 1131-1140
National Advisory Committee for Aeronautics, 1947 - Aeronautics
Chiefly translations from foreign aeronautical journals.
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airfoil angle of attack approximation assumed assumption axial beam bending bolt calculated column of fresh combustion chamber comparison compression shock computed condensation wave condition constant corresponding critical cross section curve deformation determined diameter effect elastic energy equilibrium experimental figure 12 finite flight speed flow form drag formula fresh charge friction function given gives gravity drag increase induced drag infinitely investigation jet tube lead length limit of proportionality load distribution Mach number maximum measured method missile NACA nondimensional normal shock obtained percent pipe pitot pressure pitot tube planing surface plate pressure distribution problem radial rarefaction wave ratio reference reflected Reynolds number rivets shown in figure spray drag stability stagnation point static pressure stresses subsonic diffuser supersonic symmetry tests theoretical theory tion turbulent values valves variation velocity distribution velocity of sound virtual displacements vortex sound wave drag width zero