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aerodynamic Aeronautical Sciences Aircraft Corporation airfoil airplane alloys altitude angle of attack applied approximation assumed axial axis beam bending blade boundary layer calculated cent characteristics Company compression compressor computed constant corresponding critical Mach cross section curve deflection delta wing determined distribution Division drag coefficient dynamic effect efficiency elastic energy engine equation experimental factor flight force frequency fuel function fuselage given increase isentropic lift coefficient linear load Mach Number maximum method modes modulus motion normal oblique shock obtained oscillations parameter Paul Kollsman plane plastic bending plate plotted pressure ratio problem propeller propulsive rivets rocket rotation rotor shear shock wave shown in Fig skin friction solution speed sq.in stability stress structure subsonic supersonic supersonic flow surface temperature tests theory thickness thrust tion tunnel turbine turbulence vector velocity vibration wave drag wing zero