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 vi
... altitude over sea level and geographic latitude. Consequently, the definition of the kilogram of force as the weight of a kilogram of mass on the earth surface required additional specifications of earth coordinates as to where the ...
... altitude over sea level and geographic latitude. Consequently, the definition of the kilogram of force as the weight of a kilogram of mass on the earth surface required additional specifications of earth coordinates as to where the ...
Σελίδα 6
... altitude which maximize R, and 0,. Specific distances for helicopters, tilt-rotors in the airplane mode of flight, automobiles, and dirigibles are shown in Fig 1.3 as a function of speed while for other fixedwing aircraft, D, values are ...
... altitude which maximize R, and 0,. Specific distances for helicopters, tilt-rotors in the airplane mode of flight, automobiles, and dirigibles are shown in Fig 1.3 as a function of speed while for other fixedwing aircraft, D, values are ...
Σελίδα 44
... altitude or height ratio of actual power to ideal power download factor mass distance power pressure rotor or slipstream radius radial distance th rust velocity weight, or gross weight area, disc loading angle of thrust inclination ...
... altitude or height ratio of actual power to ideal power download factor mass distance power pressure rotor or slipstream radius radial distance th rust velocity weight, or gross weight area, disc loading angle of thrust inclination ...
Σελίδα 58
... altitude becomes of interest. Dimensional rates of climb for T = W can easil be obtained from Eq (2.22) by multiplying both sides of this equation by vid = \/ W/21rR2p and expressing the K ratio in terms of ideal available power (Pidav) ...
... altitude becomes of interest. Dimensional rates of climb for T = W can easil be obtained from Eq (2.22) by multiplying both sides of this equation by vid = \/ W/21rR2p and expressing the K ratio in terms of ideal available power (Pidav) ...
Σελίδα 59
... altitude should be known, then HPidavl W can easily be computed for any altitude h. The same applies to W2 /1rR2 p HPidav, and the vertical rate of climb at any altitude can readily be obtained from Eq (2.23). If the relationship ...
... altitude should be known, then HPidavl W can easily be computed for any altitude h. The same applies to W2 /1rR2 p HPidav, and the vertical rate of climb at any altitude can readily be obtained from Eq (2.23). If the relationship ...
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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