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 47
... necessary to consider the power (P) required in the process. This can be done by examining the difference in the rate of flow of kinetic energy through a cross-section of the streamtube far downstream in the ultimate wake (Eu) and far ...
... necessary to consider the power (P) required in the process. This can be done by examining the difference in the rate of flow of kinetic energy through a cross-section of the streamtube far downstream in the ultimate wake (Eu) and far ...
Σελίδα 48
... power required is always positive. in other words, a power input is always required to cover energy losses associated with the induced velocity needed in the process of dynamic thrust generation. The first term (T- V) in the parentheses ...
... power required is always positive. in other words, a power input is always required to cover energy losses associated with the induced velocity needed in the process of dynamic thrust generation. The first term (T- V) in the parentheses ...
Σελίδα 57
W. Z. Stepniewski. 3.3 Ideal Power in Climb and Hovering As in the case of the simplest thrust generator model, power required by the actuator disc either for climb or hover may again be called the ideal power. This is iustified by the ...
W. Z. Stepniewski. 3.3 Ideal Power in Climb and Hovering As in the case of the simplest thrust generator model, power required by the actuator disc either for climb or hover may again be called the ideal power. This is iustified by the ...
Σελίδα 58
... required: Tv/735. (5|) Pia), (2.21) (ENG) Pidh = TV/ISSO. The above result could have been obtained directly from Eq ... power available to the ideal power required in hovering (K EPIdaV/Pidh ), Eq (2.22) can be plotted as shown in Fig ...
... required: Tv/735. (5|) Pia), (2.21) (ENG) Pidh = TV/ISSO. The above result could have been obtained directly from Eq ... power available to the ideal power required in hovering (K EPIdaV/Pidh ), Eq (2.22) can be plotted as shown in Fig ...
Σελίδα 60
... power required to produce a given amount of thrust becomes lower than that required in hovering (K < 7.0). Conversely, when power supplied to the rotor is reduced below the hovering level, it starts to descend in the so-called partial-power ...
... power required to produce a given amount of thrust becomes lower than that required in hovering (K < 7.0). Conversely, when power supplied to the rotor is reduced below the hovering level, it starts to descend in the so-called partial-power ...
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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