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 iii
... flow fields (both instantaneous and time averaged) around the rotor still remain unanswered. In the vortex theory discussed in Ch IV, a rotor blade is modeled by means of a vortex filament(s) or vorticity surface; thus opening almost ...
... flow fields (both instantaneous and time averaged) around the rotor still remain unanswered. In the vortex theory discussed in Ch IV, a rotor blade is modeled by means of a vortex filament(s) or vorticity surface; thus opening almost ...
Σελίδα xii
... Flow . . . . 256 6.4 Aerodynamic Loads on Helicopter Blades in Unsteady Flow . . . . . 264 6.5 Actual Calculations of Blade Loads and Angles-of'Attack . . . . . . . 271 7. Determination of Flow Around Three-Dimensional, Nonrotating ...
... Flow . . . . 256 6.4 Aerodynamic Loads on Helicopter Blades in Unsteady Flow . . . . . 264 6.5 Actual Calculations of Blade Loads and Angles-of'Attack . . . . . . . 271 7. Determination of Flow Around Three-Dimensional, Nonrotating ...
Σελίδα 7
... flow (-V E velocity of flight with an opposite sign) forms an angle -ad with the rotor plane (positive when the incoming flow has a component in the thrust direction). Then the component—either inplane or parallel to the disc—can be ...
... flow (-V E velocity of flight with an opposite sign) forms an angle -ad with the rotor plane (positive when the incoming flow has a component in the thrust direction). Then the component—either inplane or parallel to the disc—can be ...
Σελίδα 47
... flow by hi, force T becomes. T=fiMW—-W. on. where the resultant velocity of flow far downstream (lfu) is V” = '17+ Consequently, Eq (2.1) becomes. i=—%Z. (no. Furthermore, since n? = VuAup, the above equation can be rewritten as. s,. 'T': " ...
... flow by hi, force T becomes. T=fiMW—-W. on. where the resultant velocity of flow far downstream (lfu) is V” = '17+ Consequently, Eq (2.1) becomes. i=—%Z. (no. Furthermore, since n? = VuAup, the above equation can be rewritten as. s,. 'T': " ...
Σελίδα 51
... flow becomes Vu = --V,, - v,,, and pressure returns to that of the surrounding air; i.e., it becomes p0. Remembering that the mass flow within the streamtube is constant, its shape will probably resemble that shown in Fig 2.3. in order ...
... flow becomes Vu = --V,, - v,,, and pressure returns to that of the surrounding air; i.e., it becomes p0. Remembering that the mass flow within the streamtube is constant, its shape will probably resemble that shown in Fig 2.3. in order ...
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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