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THEORETICAL TILTROTOR ACOUSTIC MODEL
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aerodynamic AESOP airloads airplane configuration algebraic altitude altitude H angle angle of attack applied power assumed axis system constraints control time histories curve deceleration distance Doppler shift drag coefficient engine EPNdB feet flight path formance forward velocity Fourier series ft/sec fuel consumed fuel trajectories helicopter configuration helicopter rotor high-speed helicopter descent higher harmonic HORIZONTAL ACCELERATION LIMIT horizontal velocity hovering increase induced velocity initial kinematic performance lift coefficient loading law mathematical measuring location minimum momentum theory noise abatement profile nondimensional optimal trajectory optimization problem optimum parasite drag perceived noise level PNdB predicted profile drag coefficient R/D)max rate of climb rate of sink ratio reduce Regime resulting rotational noise rotor blade slipstream solution sound pressure level specified speed steady-state techniques terminal thrust tilt-rotor aircraft tilt-rotor performance tion TOUCHDOWN values VERTICAL ACCELERATION LIMIT vertical climb Vertol vortex noise VTOL VTOL aircraft wing zero