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PRINCIPAL FORMULAE IN AERODYNAMICS
II THE AEROFOIL
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aero aerofoil section aeroplane aileron air forces air-stream airscrew efficiency aneroid angle of incidence aspect ratio biplane blade calculated called centre line camber centre of pressure climbing speed constant corresponding critical angle decreases drag coefficient engine equation experiments flat plate flight flow form drag full-scale fuselage given gives ground level H.Pr Hence increases indicated air speed induced drag induced velocity kL and kD layer lift and drag lift coefficient lift-incidence lifting force maximum miles per hour minimum monoplane motion nose obtained parasite drag pitch position profile drag rate of climb reduced right angles rotation rudder scale effect shape shown in Fig shows skin friction slipstream slot span stability stagger stalling speed standard density streamline body struts tail plane tail setting thickness thrust top speed torque tube turbulence undercarriage values of kL varies viscosity wind channel wing area wing drag wing loading yawing zero