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MAE142_Lecture13

MAE142_Lecture13 - F-16 Aircraft Model NASA Image MAE 142...

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F-16 Aircraft Model MAE 142 NASA Image
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2 MAE 142 F-16 Falcon The F-16, manufactered by General Dynamics/Lockheed/Lockheed Martin, went into production in 1976. References: Stevens, BL and Lewis, FL, Aircraft Control and Simulation, Wiley, 1992. Morelli, EA, Global Nonlinear Parametric Modeling with Application to F-16 Aerodynamics, 1998 American Control Conference. Wingspan: 32 ft 8 in (9.96 m) Wing area: 300 ft² (27.87 m²) Airfoil: NACA 64A204 root and tip Empty weight: 18,900 lb (8,570 kg) Loaded weight: 26,500 lb (12,000 kg) Max takeoff weight: 42,300 lb (19,200 kg) Powerplant: F110-GE-100 afterburning turbofan Dry thrust: 17,155 lbf (76.3 kN) Thrust with afterburner: 28,600 lbf (127 kN) NASA Image
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3 MAE 142 Angle-of-Attack and Sideslip z B Velocity Vector y B x B x W y W z W Angle-of-Attack Sideslip
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4 MAE 142 Wind-to-Body Axis Transformation Two rotations are needed to transform the wind axis into the body-fixed axis. Rotate about negative z-axis by the sideslip angle. Rotate about positive y-axis by the angle-of-attack. T W2B = [ cos 0 sin 0 1 0 sin 0 cos ][ cos sin 0 sin cos 0 0 0 1 ] T W2B = [ cos cos cos sin
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