Rotary-Wing AerodynamicsCourier Corporation, 22 Απρ 2013 - 640 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 19
... angle from its nominal (average) value (00), and 11/1 represents the azimuth angle at which this maximum deviation occurs (Fig 1.12a) In practice, the blade collective pitch variation given by Eq (1.32) is accomplished through a ...
... angle from its nominal (average) value (00), and 11/1 represents the azimuth angle at which this maximum deviation occurs (Fig 1.12a) In practice, the blade collective pitch variation given by Eq (1.32) is accomplished through a ...
Σελίδα 20
... angle according to Eq (1.32). Without going into the refinements of aerodynamic theories, it may be anticipated that the first harmonic cyclic variation of the blade collective pitch would produce corresponding cyclic changes in the ...
... angle according to Eq (1.32). Without going into the refinements of aerodynamic theories, it may be anticipated that the first harmonic cyclic variation of the blade collective pitch would produce corresponding cyclic changes in the ...
Σελίδα 21
... angle-— which is independent of damping—amounts to 90°. This means that the maximum flapping angle of the blade occurs 90° later than the maximum blade pitch angle. In order to get some idea regarding the influence of the blade natural ...
... angle-— which is independent of damping—amounts to 90°. This means that the maximum flapping angle of the blade occurs 90° later than the maximum blade pitch angle. In order to get some idea regarding the influence of the blade natural ...
Σελίδα 22
... ANGLE: (lip - DEGREES \ 1 2 3 n/v INVERSE OF FIRST FLAPPING FREQUENCY Figure 7. 73 Effect of flapping frequency and damping on phase angle 5.2 Blade Flapoing in Forward Flight For simplicity, helicopter translations with an inplane ...
... ANGLE: (lip - DEGREES \ 1 2 3 n/v INVERSE OF FIRST FLAPPING FREQUENCY Figure 7. 73 Effect of flapping frequency and damping on phase angle 5.2 Blade Flapoing in Forward Flight For simplicity, helicopter translations with an inplane ...
Σελίδα 24
... angle [31. It should also be noted that the tip-path plane is perpendicular to an axis called the virtual axis of rotation. This axis extends through the hub and lies in a plane which passes through the rotor axis and makes an angle 4 ...
... angle [31. It should also be noted that the tip-path plane is perpendicular to an axis called the virtual axis of rotation. This axis extends through the hub and lies in a plane which passes through the rotor axis and makes an angle 4 ...
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aerodynamic airfoil airfoil section airspeed altitude angle angle-of-attack assumed autorotation axis azimuth blade element blade element theory blade station boundary layer calculations chord circulation collective pitch computed configurations cruise defined descent determined downwash downwash velocity drag coefficient effects engine equation expressed factor field Figure first flapping hinge flow fluid forward flight fuel fuselage gross weight Helicopter Rotor hover hypothetical helicopter increase induced drag induced power induced velocity influence interference drag lift coefficient lifting surface Mach number main rotor maximum momentum theory nondimensional obtained parasite drag percent performance pitch power required predictions pressure profile drag profile power radius rate of climb ratio resulting Reynolds number rotor disc rotor power rotor thrust shown in Fig significant single-rotor slipstream specific stall tail rotor tandem tandem-rotor tion TRUE AIRSPEED values variation vector velocity component velocity potential vortex filament vortex theory vortices wake wind-tunnel wing