Rotary-wing Aerodynamics, Τόμος 1Recent literature related to rotary-wing aerodynamics has increased geometrically; yet, the field has long been without the benefit of a solid, practical basic text. To fill that void in technical data, NASA (National Aeronautics and Space Administration) commissioned the highly respected practicing engineers and authors W. Z. Stepniewski and C. N. Keys to write one. The result: Rotary-Wing Aerodynamics, a clear, concise introduction, highly recommended by U.S. Army experts, that provides students of helicopter and aeronautical engineering with an understanding of the aerodynamic phenomena of the rotor. In addition, it furnishes the tools for quantitative evaluation of both rotor performance and the helicopter as a whole. Now both volumes of the original have been reprinted together in this inexpensive Dover edition. In Volume I: "Basic Theories of Rotor Aerodynamics," the concept of rotary-wing aircraft in general is defined, followed by comparison of the energy effectiveness of helicopters with that of other static-thrust generators in hover, as well as with various air and ground vehicles in forward translation. Volume II: "Performance Prediction of Helicopters" offers practical application of the rotary-wing aerodynamic theories discussed in Volume I, and contains complete and detailed performance calculations for conventional single-rotor, winged, and tandem-rotor helicopters. Graduate students with some background in general aerodynamics, or those engaged in other fields of aeronautical or nonaeronautical engineering, will find this an essential and thoroughly practical reference text on basic rotor dynamics. While the material deals primarily with the conventional helicopter and its typical regimes of flight, Rotary-Wing Aerodynamics also provides a comprehensive insight into other fields of rotary-wing aircraft analysis as well. |
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Σελίδα 27
Inclination of the rotor shaft whose axis in this case is identical to that of the
control axis ( Fig 1 . 19a ) . Inclination of the hub only , which would be equivalent
to the displacement of the control axis ( Fig 1 . 19b ) . Inclination of the
swashplate ...
Inclination of the rotor shaft whose axis in this case is identical to that of the
control axis ( Fig 1 . 19a ) . Inclination of the hub only , which would be equivalent
to the displacement of the control axis ( Fig 1 . 19b ) . Inclination of the
swashplate ...
Σελίδα 28
axis . This phenomenon of deviation of the thrust vector from the control axis is
important when making a trim analysis of the whole aircraft . Feathering which is
presently achieved through mechanical inputs from a swashplate - either directly
to ...
axis . This phenomenon of deviation of the thrust vector from the control axis is
important when making a trim analysis of the whole aircraft . Feathering which is
presently achieved through mechanical inputs from a swashplate - either directly
to ...
Σελίδα 29
calculate the position of the tip - path plane ( to which thrust is assumed to be
perpendicular ) with respect to the rotor - shaft axis . Before establishing the
necessary relationships , it should be recalled that there is no feathering with
respect to ...
calculate the position of the tip - path plane ( to which thrust is assumed to be
perpendicular ) with respect to the rotor - shaft axis . Before establishing the
necessary relationships , it should be recalled that there is no feathering with
respect to ...
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Περιεχόμενα
Hover | 4 |
Blade Flapping Motion | 10 |
Effect of Flapping Hinge Offset | 16 |
Πνευματικά δικαιώματα | |
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Συχνά εμφανιζόμενοι όροι και φράσεις
actual aerodynamic aircraft airfoil analysis angle angle-of-attack application approach assumed average axis becomes blade body boundary layer calculations characteristics chord circulation climb coefficient component computed Consequently considered correction corresponding defined determined developed direction disc discussed distance distribution downwash drag effects element engine equation example expressed factor field Figure flapping flight flow fluid forces forward fuel function fuselage geometry given gross weight helicopter higher hover hypothetical increase indicated induced velocity influence integration lift limits loading located maximum means method momentum noted obtained operating performance pitch plane position potential power required practical predictions presented pressure problems radius range ratio relationship represents respect resulting rotor shape shown in Fig speed stall station strength surface theory thrust tion trailing usually values variation various vortex vortices wake wing
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Flight Performance of Fixed and Rotary Wing Aircraft Antonio Filippone Δεν υπάρχει διαθέσιμη προεπισκόπηση - 2006 |