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 actual actual, instead of mathematical, descriptions of the rules of airplane flight. This renowned textual content provides mechanical engineering and aeronautical engineering scholars an invaluable advent to the topic. The fourth version has been up to date to incorporate very important contemporary advancements akin to unmanned air autos and the low orbit space-plane

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The use of two rotors considerably increases the cost and complexity of the aircraft. There are also problems due to interference between the two rotor wakes. On a simple single rotor helicopter, direct control of the amount of lift generated by the main rotor blades is provided by the collective pitch mechanism which changes the incidence or ‘pitch angle’ of all of the blades by the same amount simultaneously. In addition, a cyclic pitch mechanism is provided. This causes the incidence of the blades to increase and decrease once per cycle.

High speed helicopters and convertiplanes One way to get around the problems of high speed flight in helicopters is to equip them with wings and a conventional propulsion system in addition to the rotor. In high speed flight, the wings take over the provision of lift, and the rotor blades can rotate slowly, or even be folded back. The co-axial contra-rotating helicopter rotor mentioned above also has an advantage in high speed flight, as it can be arranged that the lift is provided only by the advancing pairs of blades (one on each side of the aircraft) which, therefore, do not need to move much faster than the aircraft.

11. An elliptical spanwise variation of lift thus represents a theoretical ideal case for minimum trailing vortex drag. On aircraft with unswept wings, an elliptical variation of lift can be produced by using a wing where the chord varies elliptically with distance along the span. QXD 14/9/09 15:20 Page 49 WING PLAN SHAPE Fig. 11 Elliptical variation of lift along the span This variation gives a constant downwash along the span, and the minimum amount of trailing vortex (induced) drag shown in Fig.

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