By J. Seddon

This quantity is a wonderful creation to the aerodynamics of helicopters. uncomplicated Helicopter Aerodynamics presents an account of the 1st ideas within the fluid mechanics and flight dynamics of single-rotor helicopters. The textual content is meant to supply, in a quick quantity, an advent to the idea of rotary-wing plane to be used by means of undergraduate and graduate scholars, whereas supplying an in depth description of the actual phenomena concerned. The textual content assumes that the reader already has a few wisdom of adjustments among the fastened- and rotary-wing airplane. Many diagrams, drawings, graphs, and consultant units of information increase the textual content.

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Additional resources for Basic Helicopter Aerodynamics: An Account of First Principles in the Fluid Mechanics and Flight Dynamics of the Single Rotor Helicopter

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On rotor thrust. This provides a limit to forward speed. As an example, the World Speed Record Lynx achieved approximately 250 mph in 1986. A fixed-wing aircraft, (Curtiss R4) exceeded that speed in 1923, fully 65 years ahead. The other rotorcraft variants within this second group are the tilt rotor and tilt wing layouts. The tilt rotor, in which, as the name implies, has rotors, which face upwards for vertical takeoff and hover and rotate forwards for horizontal flight. It offers considerable potential to enable the vertical take-off and landing of a helicopter but also being able to bypass the forward speed limitation.

Since the book is now under joint authorship, it would have been unfeeling to have pursued the former option since the original concept of John Seddon would have disappeared. For that reason I decided to pursue the latter option of revising the text and adding to it – particularly in the field of illustrations. The design, manufacture and operation of the helicopter rotor tend to be rather esoteric for the newcomer and long textual descriptions can be dry and not helpful. I have added, therefore, a substantial number of images to illustrate and clarify the discussions.

The tip jet exhausts show the wake structures in several different flight regimes. 5(a) illustrates a hovering condition close to the ground surface. The wake can be seen to contract immediately below the rotor but then expand as the downflow from the rotor is interrupted by the ground forcing it to spill outwards. This phenomenon is called ‘ground effect’ and is a very important feature of helicopter performance. The wake structure shows not only the ‘tube’ of vorticity, but also the individual blade tip vortices.

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