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Tests of a Centaurus Nacelle Installation with N A C A Cowl and Rear Swept Exhaust System
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aerofoil aircraft amplitude angle antisymmetrical Appendix approximately axis B.Sc beam calculated cent Centaurus coefficient combustion chamber components compression compressor constant cooling cowl curves cycle cylinder deadrise deflexion diffuser distribution drag dural edge members effect efficiency engine entry equation EQUIVALENT AIRSPEED exhaust factor ﬁrst ﬂight Flight Mach Number ﬂow force formulae frequency ft./sec fuel functions fuselage gas turbine gill exit give given heat exchanger impact increase inlet intercooling isentropic load longerons loss maximum measured method modes normal obtained oscillograph output panel parameters pickup piston plane plotted pressure ratio propeller propulsive ramjet range rivets roots Royal Aircraft Establishment rudder shear stress shown in Fig speciﬁc speed stability static stringers symmetrical Table tailplane take-off thrust torsional total head trim tunnel turbine values variation velocity vibration Wind Tunnel wing Young's modulus zero