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 27
... hypothetical helicopter are quite close , the CH - 47C airfoil cd data is sufficiently accurate for estimating the main rotor cd values . It is not suitable , however , for use in defining tail rotor drag coefficients . The c incre ...
... hypothetical helicopter are quite close , the CH - 47C airfoil cd data is sufficiently accurate for estimating the main rotor cd values . It is not suitable , however , for use in defining tail rotor drag coefficients . The c incre ...
Σελίδα 60
... hypothetical helicopter . ) b . Correct power required for nonuniform downwash effects . c . Apply parasite power ... hypothetical single - rotor aircraft . It should be noted that all airspeeds are considered as true airspeed which ...
... hypothetical helicopter . ) b . Correct power required for nonuniform downwash effects . c . Apply parasite power ... hypothetical single - rotor aircraft . It should be noted that all airspeeds are considered as true airspeed which ...
Σελίδα 232
... hypothetical single - rotor helicopter , 3-4 tandem - rotor helicopter , 197 winged helicopter , 146 Disc loading , 35 , 98 see also tandem rotor trends in Download alleviation of , 153-55 calculation of , 37-43 in forward flight , 96 ...
... hypothetical single - rotor helicopter , 3-4 tandem - rotor helicopter , 197 winged helicopter , 146 Disc loading , 35 , 98 see also tandem rotor trends in Download alleviation of , 153-55 calculation of , 37-43 in forward flight , 96 ...
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Notes on Metric System | 1 |
3 | 7 |
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 |