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 70
... altitudes and plotting ( Vcf ) max values versus altitude . It is obvious that the altitude at which ( Vcf ) max reaches some pre- scribed value ; say , ( Vcf ) max = 70 m / min , will represent the service ceiling ( Fig 2.17 ) . The ...
... altitudes and plotting ( Vcf ) max values versus altitude . It is obvious that the altitude at which ( Vcf ) max reaches some pre- scribed value ; say , ( Vcf ) max = 70 m / min , will represent the service ceiling ( Fig 2.17 ) . The ...
Σελίδα 16
... altitude which occurs in North America at about 40 ° latitude6,7,8 . Pressure altitude , defined as " the altitude at which a given pressure p is found in the standard atmosphere " 8 , is again a " non - tape - measured " hypothetical ...
... altitude which occurs in North America at about 40 ° latitude6,7,8 . Pressure altitude , defined as " the altitude at which a given pressure p is found in the standard atmosphere " 8 , is again a " non - tape - measured " hypothetical ...
Σελίδα 131
... altitude ( up to 20,000 ft ) by 175 ft for every 100 lb of fuel burnoff . The cruise airspeed required is approximately 130 kn . PRESSURE ALTITUDE - 1000 FT TRUE AIRSPEED KN 12 16 160 140 120 20 STANDARD DAY BEST RANGE SPEED ( 99 ...
... altitude ( up to 20,000 ft ) by 175 ft for every 100 lb of fuel burnoff . The cruise airspeed required is approximately 130 kn . PRESSURE ALTITUDE - 1000 FT TRUE AIRSPEED KN 12 16 160 140 120 20 STANDARD DAY BEST RANGE SPEED ( 99 ...
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4 | 16 |
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actual aerodynamic aircraft airfoil angle application approach assumed average axis azimuth becomes blade blade element calculations characteristics chord circulation climb coefficient component computed Consequently considered corresponding defined determined developed direction disc discussed distance distribution downwash drag effects equal equation example expressed factor field Figure flapping flight flow forces forward flight fuel function fuselage geometry given gross weight helicopter horizontal hover hypothetical ideal increase indicated induced power induced velocity influence integration lift limits loading located losses maximum means method momentum nondimensional noted obtained performance pitch plane position potential power required predictions presented pressure problems radius ratio relationship represents respect resulting rotor shown in Fig similar speed stall station strength Substituting surface theory thrust tion trailing unit usually values variation various vortex vortices wake wing
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Flight Performance of Fixed and Rotary Wing Aircraft Antonio Filippone Δεν υπάρχει διαθέσιμη προεπισκόπηση - 2006 |