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PRELIMINARY NOTES ON THE EFFICIENCY OF PROPULSION SYSTEMS
Explosive Rocket with Thrust Augmentation
27 other sections not shown
according adiabatic airplane angle of attack approximate assumed augmenter tube axis buckling lengths buckling load calculation chemical reaction coefficient combustion compression compressor computed constant corresponding curve cycle decrease defined derivative determined detonation wave differential equation diffuser disturbance motion engine equal exhaust expansion explosive rocket figure flow fluid formula friction fuel function fuselage gives heat hence increase indifference curve kinetic energy km/h laminar laminar flow m/sec magnitude maximum mixer mixture moduli of elasticity neutral vibrations nodal lines nondimensional nozzle obtained orthotropic plate over-all efficiency parameter plane plywood plywood plate pressure propagation propeller propulsive efficiency quantity ratio reference Reynolds number rocket with thrust rotating system shear shock wave solution speed stability stress temperature theoretical theory thermal efficiency thermodynamic cycle thrust augmenter tion true rocket turbine turborocket unity velocity of detonation viscosity wing wmax zero