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airfoils altitude analysis angle of attack appendix as-overtemperatured atomic oxygen axial blade exit angle boundary layer buckets bypass calculated chemical chemical equilibrium Coanda effect Coanda nozzle COMMITTEE FOR AERONAUTICS cone configuration constant curve cycle decrease deflection angle deflection plate deflection-plate angle density drag coefficient droplet effect energy engine enthalpy equation equilibrium equivalence ratio exit whirl feet flame flap flat-plate friction heat transfer heat-transfer impingement efficiency inches increase inlet velocity ratio jet deflectors laminar leading-edge cracking m-curve Mach number maximum measured molecular NACA TN nacelle station NATIONAL ADVISORY COMMITTEE nozzle exit nozzle height nozzle pressure ratio obtained overtemperatured parameter percent performance plate length plug nozzle Primary-nozzle pressure ratio radiation ramjet recombination reference Reynolds number shear stress shown in figure side force STANFORD STANFORD UNIVERSITY stator stress-rupture supersonic tailpipe theoretical tion tube turbojet turbulent undeflected values variation zero