Preliminary Take-Off Analysis and Simulation of PrandtlPlane Commercial Aircraft
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ORIGINAL ARTICLE
Preliminary Take‑Off Analysis and Simulation of PrandtlPlane Commercial Aircraft K. Abu Salem1 · G. Palaia1 · M. Bianchi1 · D. Zanetti2 · V. Cipolla1 · V. Binante2 Received: 17 February 2020 / Revised: 9 July 2020 / Accepted: 13 July 2020 © The Author(s) 2020
Abstract The present paper deals with the take-off performance analysis of PrandtlPlane aircraft. The PrandtlPlane is a Box-Wing configuration based on Prandtl’s “Best Wing System” concept, which minimizes the induced drag once wingspan and lift are given. The take-off dynamics is simulated implementing the non-linear equations of motion in a numerical tool, which adopts a Vortex Lattice Method solver to evaluate the aerodynamics characteristics taking also ground effects into account. The take-off analysis is performed for both a PrandtlPlane and a reference monoplane, with the aim of comparing the performance of the two different architectures. The preliminary results show the potential advantages of the PrandtlPlane, such as runway length reduction and improved passenger comfort. Keywords PrandtlPlane · Box-Wing · Take-off · PARSIFAL List of Symbols BFL Balanced field length (m) BPR Turbofan bypass ratio CL Lift coefficient CLα Derivative of lift coefficient respect to angle of attack (1/rad) CLδe Derivative of lift coefficient respect to elevator deflection (1/rad) CLδf Derivative of lift coefficient respect to flap deflection (1/rad) CLmax Maximum lift coefficient * K. Abu Salem [email protected] G. Palaia [email protected] M. Bianchi [email protected] D. Zanetti [email protected] V. Cipolla [email protected] V. Binante [email protected] 1
Department of Civil and Industrial Engineering, University of Pisa, Pisa, Italy
SkyBox Engineering S.r.l., Pisa, Italy
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Cm Pitching-moment coefficient Cm0 Pitching-moment coefficient at zero angle of attack Cmα Derivative of pitching moment coefficient respect to angle of attack (1/rad) Cmδe Derivative of pitching moment coefficient respect to elevator deflection (1/rad) Cmδf Derivative of pitching moment coefficient respect to flap deflection (1/rad) D Drag (N) d Centre of gravity-wheels horizontal distance (m) g Standard gravity (m/s2) h Centre of gravity-wheels vertical distance (m) IY Pitching moment of inertia (kgm2) L Lift (N) MA Aerodynamic pitching moment (N m) MTOW Maximum take-off weight (N) nZ Vertical load factor RN Vertical reaction of the ground (N) RT Horizontal reaction of the ground (N) T Thrust (N) TOD Take-off distance (m) V Speed (m/s) V1 Decision speed (m/s) V2 Take-off speed (m/s) VR Rotation speed (m/s) VZ Vertical speed (m/s)
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Vol.:(0123456789)
W Aircraft weight (N) (XF YF ZF) Final coordinates of main surfaces (m) (XI YI ZI) Initial coordinates of main surfaces (m) α Angle of attack (rad) γ Trajectory angle (rad) ΔZ Height (m) δe Deflection angle of elevators (rad) δf Deflection angle of flap (rad) θ Attitude angle (rad) μ Rolling friction coefficient Ψf Flap gain
K. Abu Sa
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