Rotary-wing Aerodynamics, Τόμος 1Dover Publications, 1984 - 601 σελίδες Recent 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 81
... values may be even higher . It should also be noted that the 7 in ( e ) and ( f ) does does not appcar in either of the expressions for f ( F ) or kindh . This omission is the result of the low induced velocities at the outer disc rim ...
... values may be even higher . It should also be noted that the 7 in ( e ) and ( f ) does does not appcar in either of the expressions for f ( F ) or kindh . This omission is the result of the low induced velocities at the outer disc rim ...
Σελίδα 258
... values of n . Eq ( 5.55 ) represents the load - per - unit span at discrete points ( i = 1 , 2 , ... n ) of the blade span . In order to obtain - with a limited number of points - the best possible de- termination of the F values along ...
... values of n . Eq ( 5.55 ) represents the load - per - unit span at discrete points ( i = 1 , 2 , ... n ) of the blade span . In order to obtain - with a limited number of points - the best possible de- termination of the F values along ...
Σελίδα 313
... values as would occur in actual flight . Conse- quently , a methodology is required to predict the Re scale effects on such airfoil char- acteristics as profile drag coefficient , ca ( Re ) ; maximum lift coefficient values , Cmax ( Re ) ...
... values as would occur in actual flight . Conse- quently , a methodology is required to predict the Re scale effects on such airfoil char- acteristics as profile drag coefficient , ca ( Re ) ; maximum lift coefficient values , Cmax ( Re ) ...
Περιεχόμενα
Notes on Metric System | 1 |
Fundamental Dynamic Problems of the Rotor | 7 |
4 | 16 |
Πνευματικά δικαιώματα | |
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aerodynamic airfoil airfoil section airspeed angle-of-attack approach assumed axis Biot-Savart law blade element blade element theory blade station boundary layer calculations chord circulation computed const determined downwash velocity drag coefficient effects equation expressed factor Figure flapping flow forward flight fuel fuselage gross weight Helicopter Rotor horizontal flight hover hypothetical helicopter induced power induced velocity integration kindh lift coefficient lifting surface located Mach number main rotor maximum momentum theory nondimensional number of blades obtained parasite drag percent performance pitch angle plane potential power required predictions profile drag profile power radius rate of climb ratio resulting rotation rotor disc rotor power rotor thrust shown in Fig single-rotor slipstream stall tail rotor tandem tandem-rotor tion tip losses trailing vortices TRUE AIRSPEED V₁ values variation vector velocity components velocity potential vortex filament vortex theory wake wing
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Flight Performance of Fixed and Rotary Wing Aircraft Antonio Filippone Δεν υπάρχει διαθέσιμη προεπισκόπηση - 2006 |