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The stress distribution in a sweptback boxbeam with perpendicular ribs P B Hovell
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aerodynamic aerodynamic centre aerofoil aileron aircraft angle of attack applied approximately aspect ratio assumed assumptions attachment axes boundary layer calculated camber cent charts chord CM CM CM components considered constant corresponding curve damping deflection deformability derivatives design value displacement downwash dynamic pressure effect elastic axis elastic wash-out enthalpy estimated experimental flap formulae frequency fuselage gives indication inertia leading edge lift coefficient lift distribution liners load factor Mach number manoeuvre point maximum method mixture nozzle obtained oscillation pitching plane plotted position pressure ratio quarter-chord quasi-steady rear spar reflection plate Reynolds number root rotation Royal Aircraft Establishment shear shift of manoeuvre shown in Fig span speed stability stagnation pressure strain energy stress structure subsonic supersonic surface sweepback swept wings Table tailplane torque torsional rigidity trailing-edge angle transition traverse unsteady flow unswept velocity wind tunnel yawing zero