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 144
... theories discussed in the two preceding chapters . The actual application of the vortex concept to modeling of airscrews started with the development of the ' vortex theory ' whose foundations were laid by Joukowsky1 in the USSR in the ...
... theories discussed in the two preceding chapters . The actual application of the vortex concept to modeling of airscrews started with the development of the ' vortex theory ' whose foundations were laid by Joukowsky1 in the USSR in the ...
Σελίδα 217
... this approach was improved through a special program called CCHAP ( Circulation Coupled Hover Analysis Program ) which couples the wake geometry to load distribution . It was indicated that accuracies similar to those 217 Vortex Theory.
... this approach was improved through a special program called CCHAP ( Circulation Coupled Hover Analysis Program ) which couples the wake geometry to load distribution . It was indicated that accuracies similar to those 217 Vortex Theory.
Σελίδα 35
... vortex theory is RHPtr = 210 hp , consisting of 87 percent induced and 13 percent profile power . The vortex theory induced power is 30 to 50 percent higher than that predicted by the simple momentum theory . This percentage difference ...
... vortex theory is RHPtr = 210 hp , consisting of 87 percent induced and 13 percent profile power . The vortex theory induced power is 30 to 50 percent higher than that predicted by the simple momentum theory . This percentage difference ...
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4 | 16 |
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actuator disc aerodynamic airfoil airfoil section airspeed altitude angle-of-attack assumed autorotation axis azimuth blade element blade element theory blade station boundary layer calculations chord circulation computed descent determined disc loading downwash velocity drag coefficient effects equation expressed factor Figure flow forward flight fuel fuselage gross weight Helicopter Rotor horizontal flight hover hypothetical helicopter increase induced power induced velocity interference drag lift coefficient lifting surface Mach number main rotor maximum momentum theory nondimensional number of blades obtained parasite drag percent performance pitch angle 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 single-rotor SL/STD slipstream stall tail rotor tandem tandem-rotor tion tip losses TRUE AIRSPEED values variation vector velocity component velocity potential vortex theory vortices wake wind-tunnel wing
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Flight Performance of Fixed and Rotary Wing Aircraft Antonio Filippone Δεν υπάρχει διαθέσιμη προεπισκόπηση - 2006 |