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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Αποτελέσματα 6 - 10 από τα 93.
Σελίδα 21
... equation is now reduced to am, e Aaomx. (1.37a) Eqs (1.35) and (1.37a) indicate that by applying a first-harmonic variation of the cyclic pitch to a hovering rotor with flapping hinges (zero offset hinges perpendicular to the rotor axis) ...
... equation is now reduced to am, e Aaomx. (1.37a) Eqs (1.35) and (1.37a) indicate that by applying a first-harmonic variation of the cyclic pitch to a hovering rotor with flapping hinges (zero offset hinges perpendicular to the rotor axis) ...
Σελίδα 22
... equation describes this kind of motion: 1,)? + a3 + k6 = M,(¢). (1.39) It may be expected that the steady-state solution of this equation is a harmonic function of 11/ which can be expressed in terms of a Fourier series representing ...
... equation describes this kind of motion: 1,)? + a3 + k6 = M,(¢). (1.39) It may be expected that the steady-state solution of this equation is a harmonic function of 11/ which can be expressed in terms of a Fourier series representing ...
Σελίδα 24
... equation of motion (1.39) would be identical to Eq (1.33) and thus, for the case of (v/n) = 7, a 90° phase lag shift may be expected. In the expression forB as given by Eq (1.41), this would mean that 1111 = 0 and the blade would ...
... equation of motion (1.39) would be identical to Eq (1.33) and thus, for the case of (v/n) = 7, a 90° phase lag shift may be expected. In the expression forB as given by Eq (1.41), this would mean that 1111 = 0 and the blade would ...
Σελίδα 25
... equation and Fig 1.17, it may be assumed as a first approximation that in translatory flight with an inplane velocity component ()1 > 0), an aerodynamic forcing moment proportional to sin 11) will be present. Furthermore, it can be seen ...
... equation and Fig 1.17, it may be assumed as a first approximation that in translatory flight with an inplane velocity component ()1 > 0), an aerodynamic forcing moment proportional to sin 11) will be present. Furthermore, it can be seen ...
Σελίδα 26
... equation that the influence of the angle-of-attack variation due to coning will be first harmonic in character. This, in turn, would generate variation of the aerodynamic moment of the same character. It may be expected hence, that a ...
... equation that the influence of the angle-of-attack variation due to coning will be first harmonic in character. This, in turn, would generate variation of the aerodynamic moment of the same character. It may be expected hence, that a ...
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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