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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 best climbing speed biplane blade calculated called centre line camber centre of pressure constant corresponding critical angle decreases difference drag coefficient engine equation experiments flat plate flight flow form drag ft./min full-scale fuselage gives ground level H.Pa H.Pr Hence horse-power available horse-power required increases indicated air speed induced drag induced velocity lift and drag lift coefficient lifting force miles per hour minimum monoplane motion no-lift 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 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