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 54
... influence of the rotor downwash and the airstream widens. If the downwash at the rotor itself is —v,,;, then the rate of flow through the rotor disc will obviously be V'= Vd — vd. It can be shown, as for the rate of climb, that the ...
... influence of the rotor downwash and the airstream widens. If the downwash at the rotor itself is —v,,;, then the rate of flow through the rotor disc will obviously be V'= Vd — vd. It can be shown, as for the rate of climb, that the ...
Σελίδα 81
... influence on the level of the 11 coefficient and kindh. With respect to the A13,- distribution, it can be easily seen that in addition to the previously discussed cases of uniform and triangular downwash distribution, the parabolic ...
... influence on the level of the 11 coefficient and kindh. With respect to the A13,- distribution, it can be easily seen that in addition to the previously discussed cases of uniform and triangular downwash distribution, the parabolic ...
Σελίδα 83
... influence of span losses can be ignored here, and it may be assumed that 78 = 7.0. Under this assumption, the ... influence of the rear rotor on the front rotor may be neglected. By contrast, the effects of the flow tube extending ...
... influence of span losses can be ignored here, and it may be assumed that 78 = 7.0. Under this assumption, the ... influence of the rear rotor on the front rotor may be neglected. By contrast, the effects of the flow tube extending ...
Σελίδα 85
... influenced by the front rotor penetrates that influenced by the rear one, Eq (2.77) is assumed to be valid. Consequently, the induced power of the whole helicopter can be broken down into three components and computed separately. The ...
... influenced by the front rotor penetrates that influenced by the rear one, Eq (2.77) is assumed to be valid. Consequently, the induced power of the whole helicopter can be broken down into three components and computed separately. The ...
Σελίδα 89
... influence of the spanwise location of the chord (x,,) has disappeared, which means that the expressed relationship is valid for any disc chord. At the leading edge of the disc, the induced velocity is zero and then grows linearly until ...
... influence of the spanwise location of the chord (x,,) has disappeared, which means that the expressed relationship is valid for any disc chord. At the leading edge of the disc, the induced velocity is zero and then grows linearly until ...
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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