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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... Figure 7 .2 Specific impulse of various thrust generators This figure also shows that rotary-wing aircraft with a static specific impulse of over 70 000 seconds vs a few hundred seconds for chemical rockets represent the concepts most ...
... Figure 7 .2 Specific impulse of various thrust generators This figure also shows that rotary-wing aircraft with a static specific impulse of over 70 000 seconds vs a few hundred seconds for chemical rockets represent the concepts most ...
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... Figure 7.9 Character of the {Mb/80° variation 4.3 Effect of Flapping Hinge Offset All of the preceding considerations were performed under the assumption that the flapping hinge passes through, and is perpendicular to, the rotor axis ...
... Figure 7.9 Character of the {Mb/80° variation 4.3 Effect of Flapping Hinge Offset All of the preceding considerations were performed under the assumption that the flapping hinge passes through, and is perpendicular to, the rotor axis ...
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... Figure 7. 74 Pure cosine motion - tip-path plane seen from the left 121 — coefficient representing the amplitude of a pure, first-harmonic, sine motion reaching pm,” at II! = 90°, and an,“ at w =270° (Fig 1.15). Figure 7. 75 Pure sine ...
... Figure 7. 74 Pure cosine motion - tip-path plane seen from the left 121 — coefficient representing the amplitude of a pure, first-harmonic, sine motion reaching pm,” at II! = 90°, and an,“ at w =270° (Fig 1.15). Figure 7. 75 Pure sine ...
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W. Z. Stepniewski. Figure 7.25 Small mechanically-driven, single-rotor helicopter in ground trainer configuration (Del-Mar Engineering DH-2A —— W N 295 kG) Figure 7.26 Large mechanically-driven, single-rotor helicopter (MIL Mi-lO —- Wz ...
W. Z. Stepniewski. Figure 7.25 Small mechanically-driven, single-rotor helicopter in ground trainer configuration (Del-Mar Engineering DH-2A —— W N 295 kG) Figure 7.26 Large mechanically-driven, single-rotor helicopter (MIL Mi-lO —- Wz ...
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W. Z. Stepniewski. Figure 7 .2 7 Light transport helicopter (Boeing Verto/ 7 07-” — W z 8600 kG) Figure 7.28 Artist's concept of X CH-62 heavy-lift tandem helicopter (W at 60 000 kG) As indicated in Table I-1, mutual cancellation of the ...
W. Z. Stepniewski. Figure 7 .2 7 Light transport helicopter (Boeing Verto/ 7 07-” — W z 8600 kG) Figure 7.28 Artist's concept of X CH-62 heavy-lift tandem helicopter (W at 60 000 kG) As indicated in Table I-1, mutual cancellation of the ...
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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