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 68
... given by the graph in Fig 2.14, as well as the other relationship of -> V'= Vho + vho. \ v-HV') \ \ HOVERING v ' V' l 1 ti '— v'h—Il asumve VELOCITY AT oisc v' I V. 'I Figure 2. 74 induced velocity vs relative velocity at the disc By ...
... given by the graph in Fig 2.14, as well as the other relationship of -> V'= Vho + vho. \ v-HV') \ \ HOVERING v ' V' l 1 ti '— v'h—Il asumve VELOCITY AT oisc v' I V. 'I Figure 2. 74 induced velocity vs relative velocity at the disc By ...
Σελίδα 86
... (Fig 2.24). The total induced power of the helicopter will be the sum of all ... shown as computed for a non'overlapped tandem on the basis of the Mangler ... shown in this figure. The lower of the two Boeing curves represents direct total ...
... (Fig 2.24). The total induced power of the helicopter will be the sum of all ... shown as computed for a non'overlapped tandem on the basis of the Mangler ... shown in this figure. The lower of the two Boeing curves represents direct total ...
Σελίδα 87
... shown in Fig 2.20, including the assumption that V),o > vho. However, to facilitate the present study, special coordinate systems and notations were introduced as shown in Fig 2.26. Figure 2.26 Notations and coordinate systems for ...
... shown in Fig 2.20, including the assumption that V),o > vho. However, to facilitate the present study, special coordinate systems and notations were introduced as shown in Fig 2.26. Figure 2.26 Notations and coordinate systems for ...
Σελίδα 95
... (Fig 3.1). PARALLEL T0 ROTOR orsc Q \ \\§ NOTE: THE BLADE ELEMENT IS SHOWN STATIONARY WHILE THE AIR FLOWS PAST IT Figure 3.7 Blade element concept The rotor is composed of b blades, and is assumed to be turning at a rotational velocity 9 ...
... (Fig 3.1). PARALLEL T0 ROTOR orsc Q \ \\§ NOTE: THE BLADE ELEMENT IS SHOWN STATIONARY WHILE THE AIR FLOWS PAST IT Figure 3.7 Blade element concept The rotor is composed of b blades, and is assumed to be turning at a rotational velocity 9 ...
Σελίδα 108
... Fig 3.6). Figure 3.6 Typical cl vs a curve The above discussion of the hovering case should enable the reader to ... shown in Fig 3.7.. Knowing Pind, the induced power factor kind E P,-,,d/P,'d can be determined; again following ...
... Fig 3.6). Figure 3.6 Typical cl vs a curve The above discussion of the hovering case should enable the reader to ... shown in Fig 3.7.. Knowing Pind, the induced power factor kind E P,-,,d/P,'d can be determined; again following ...
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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