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 117
... CRUISE ALTITUDE 2 MIN WARMUP @ NORMAL POWER CRUISE AT BEST RANGE SPEED RANGE DESCEND TO LANDING SITE LAND WITH 10 % FUEL RESERVE TTTTTTTTT Figure 3.47 Mission profile ( 1 ) Warmup - Includes fuel consumed to start and check out the ...
... CRUISE ALTITUDE 2 MIN WARMUP @ NORMAL POWER CRUISE AT BEST RANGE SPEED RANGE DESCEND TO LANDING SITE LAND WITH 10 % FUEL RESERVE TTTTTTTTT Figure 3.47 Mission profile ( 1 ) Warmup - Includes fuel consumed to start and check out the ...
Σελίδα 135
... cruise is computed by multiplying ( A WF ) er by the cruise time ( ter ) , where ter≈ ( WF x SR ) / V , and V is the average cruise speed . This fuel increment is then set aside and is not used for distance calculations . ( 4 ) ...
... cruise is computed by multiplying ( A WF ) er by the cruise time ( ter ) , where ter≈ ( WF x SR ) / V , and V is the average cruise speed . This fuel increment is then set aside and is not used for distance calculations . ( 4 ) ...
Σελίδα 167
... cruise rotor unloading , wing CL , and incidence angle must be selected in such a way as to make the total power re ... CRUISE SELECTED 20 40 WING - LIFT / GROSS WEIGHT - 60 ( % UNLOADING ) 20 WING L / D RATIO 10- CRUISE CL SELECTED 0.4 ...
... cruise rotor unloading , wing CL , and incidence angle must be selected in such a way as to make the total power re ... CRUISE SELECTED 20 40 WING - LIFT / GROSS WEIGHT - 60 ( % UNLOADING ) 20 WING L / D RATIO 10- CRUISE CL SELECTED 0.4 ...
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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 |