Aeronautics Astronautics

Aircraft Flight: A description of the physical principles of by D.R. Philpott, R.H. Barnard

By D.R. Philpott, R.H. Barnard

Airplane Flight presents exact actual, instead of mathematical, descriptions of the foundations of airplane flight. This renowned textual content supplies mechanical engineering and aeronautical engineering scholars an invaluable creation to the topic. The fourth version has been up-to-date to incorporate vital fresh advancements akin to unmanned air autos and the low orbit space-plane

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24. QXD 14/9/09 15:18 Page 27 LIFT GENERATION USING ENGINE THRUST Fig. 24 Lift from downward deflected engine thrust The practicality of jet lift was demonstrated by the Rolls-Royce ‘Flying Bedstead’ rig. Stability and control were provided by subsidiary jets which can be seen clearly. The same basic control system is used on the VTOL Harrier (Photo courtesy of Rolls-Royce plc) The British Aerospace Harrier (manufactured under licence in the USA as the McDonnell Douglas AV-8) shown in Fig. 12, was the first operational aircraft to use this method of generating lift, and employs rotatable nozzles to direct or ‘vector’ the engine jets.

18) Fig. QXD 14/9/09 15:20 Page 56 56 WINGS used a modest amount of sweep. Allied wartime jet aircraft, such as the Gloster Meteor, which were designed without the benefit of Betz’s theories, used unswept wings. After the war, when the information became available, many designs were hurriedly changed. The straight-winged Supermarine Attacker design was developed to produce the swept-wing Swift. Disadvantages of swept wings On a swept wing, only the normal component of velocity changes, and thus pressure changes are produced only by this component.

QXD 14/9/09 15:20 Page 52 52 WINGS Fig. 14 Wing-tip stall As the wing tip descends, the effective angle of attack is increased deepening the stall on that tip. On the opposite rising tip, the effective angle of attack is decreased, inhibiting stalling of that tip. The aircraft therefore starts to roll and yaw nose will tend to drop, the angle of attack will decrease, and stall recovery will be almost automatic. If the tips of the wing stall before the inboard section, however, one tip will invariably start to drop before the other, and as it drops, its effective angle of attack will be increased, as illustrated in Fig.

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