Rotary-wing Aerodynamics, Τόμος 1Dover Publications, 1984 - 601 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 313
... Reynolds number . Restd = 8 X 10 ° . The maximum section - lift coefficient , Camax , at Re other than 8 X 10 ° can be found from that obtained at the standard Reynolds number by adding or sub- tracting a correction term , Acemax : = C ...
... Reynolds number . Restd = 8 X 10 ° . The maximum section - lift coefficient , Camax , at Re other than 8 X 10 ° can be found from that obtained at the standard Reynolds number by adding or sub- tracting a correction term , Acemax : = C ...
Σελίδα 358
... Reynolds Number and Airfoil Geometry . NACA TN 3963 , March 1957 . 19 . van den Berg , B. Reynolds Number and Mach Number Effects on the Maximum Lift and the Stalling Characteristics of Wings at Low Speeds . NLR TR 69025U , March 1969 ...
... Reynolds Number and Airfoil Geometry . NACA TN 3963 , March 1957 . 19 . van den Berg , B. Reynolds Number and Mach Number Effects on the Maximum Lift and the Stalling Characteristics of Wings at Low Speeds . NLR TR 69025U , March 1969 ...
Σελίδα 25
... number well with the Prandtl - Glauert expression ( see Vol I , Ch VI ) = ceac ce a ; √√1 - M2 where ciac is the ... Reynolds number ( R ) corresponding to a CH - 47C helicopter rotor blade , with a chord of 25.25 inches , operating at ...
... number well with the Prandtl - Glauert expression ( see Vol I , Ch VI ) = ceac ce a ; √√1 - M2 where ciac is the ... Reynolds number ( R ) corresponding to a CH - 47C helicopter rotor blade , with a chord of 25.25 inches , operating at ...
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Notes on Metric System | 1 |
3 | 7 |
4 | 16 |
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aerodynamic airfoil airfoil sections airspeed angle-of-attack approach assumed axis Biot-Savart law blade element blade element theory blade station boundary layer calculations chord circulation computed const determined doublet downwash downwash distribution downwash velocity drag coefficient effects equation expressed Figure flapping flow fluid forward flight fuel fuselage gross weight Helicopter Rotor horizontal flight hover hypothetical helicopter induced power induced velocity integration kindh lift coefficient lifting surface located Mach number main rotor momentum theory nondimensional number of blades obtained parasite drag performance pitch angle plane power required predictions pressure profile drag profile power radius rate of climb ratio resulting rotation rotor disc rotor power rotor thrust shown in Fig single-rotor slipstream stall tail rotor tandem tandem-rotor tion tip losses trailing vortices TRUE AIRSPEED values variation vector velocity component velocity potential vortex filament vortex sheet vortex theory wake wing
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Flight Performance of Fixed and Rotary Wing Aircraft Antonio Filippone Δεν υπάρχει διαθέσιμη προεπισκόπηση - 2006 |