Aircraft Design: Synthesis and Analysis - part 2 pptx
Aircraft Design: Synthesis and Analysis - part 2 pptx
... the aircraft. 1990 55 25 0.0 22 1 368.3 485 20 1 .2 783 24 9.4 1991 51 23 1.8 21 2 353.3 469 194.6 760 24 2.0 19 92 55 25 0.0 23 9 398.3 484 20 0.8 806 25 6.7 1993 57 25 9.1 24 5 408.3 487 20 2.1 814 25 9 .2 * ... 3 82 158.5 561 178.7 1986 36 163.6 125 20 8.3 431 178.8 622 198.1 1987 42 190.9 151 25 1.7 459 190.5 681 21 6.9 1988 48 21 8 .2 180 300.0 475 197.1 726 2...
Ngày tải lên: 08/08/2014, 11:21
Aircraft Design: Synthesis and Analysis - part 1 doc
... Thus the DC- 9-1 0, a 77,000 lb, 80 passenger airplane grew into a DC- 9 -2 0, then the -3 0, -4 0, -5 0, -8 0 then on to the MD-80 and MD-90 series. The MD-90 weighs as much as 1 72, 000 lbs and can carry ... first to fly. Aircraft Design: Synthesis and Analysis The Airline Industry In order to understand how new aircraft might fit into the current m...
Ngày tải lên: 08/08/2014, 11:21
Aircraft Design: Synthesis and Analysis - part 3 ppt
... normal direction). In 2- D subsonic flow: ∆U' = C t/c cosΛ (1-M n 2 ) -0 .5 = C t/c cosΛ / β So: k = 1 + 2 C t/c cos 2 Λ / β + C 2 cos 2 Λ t/c 2 (1+5 cos 2 Λ) / 2 β 2 The value of k is given ... person ranges from 6.5 ft ^2 for narrow body aircraft to 7.5 ft ^2 for wide- bodies in an all-tourist configuration. A typical 3-class arrangement requires about 10 ft...
Ngày tải lên: 08/08/2014, 11:21
Aircraft Design: Synthesis and Analysis - part 4 potx
... couple of popular airfoils of the time: +- y = (t/0 .2) * ( .29 69*x 0.5 - . 126 *x - .3537*x 2 + .28 43*x 3 - .1015*x 4 ) The camberline of 4-digit sections was defined as a parabola from the leading ... 4-Digit Series: 4 4 1 2 max camber position max thickness in % chord of max camber in % of chord in 1/10 of c After the 4-digit sections came the 5-digit sections suc...
Ngày tải lên: 08/08/2014, 11:21
Aircraft Design: Synthesis and Analysis - part 5 pdf
... designed for efficient high-speed flight is often quite different from one designed solely for take- off and landing. Take-off and landing distances are strongly influenced by aircraft stalling speed, ... deflection of 0 deg and 20 deg. Airplane S wf / Sref Flap Type Flap Chord Ratio Sweep (deg) DC-3S 0.575 Split 0.174 10 DC-4 0.560 Single Slot 0 .25 7 0 DC-6 0.589 Double Slot 0 ....
Ngày tải lên: 08/08/2014, 11:21
Aircraft Design: Synthesis and Analysis - part 6 pot
... "good-flying" and difficult-to-fly aircraft. New aircraft designs can be simulated to determine whether they are acceptable. Such real-time, pilot-in-the- loop simulations are expensive and ... turbo-prop nacelles, the value is usually much larger. Airplane ytrack / fuse dia. (approx) 73 7 -2 00 1.39 74 7 -2 00 1.67 75 7 -2 00 1.85 76 7-3 00 1.67 E-3 Sentry 1. 62 Cita...
Ngày tải lên: 08/08/2014, 11:21
Aircraft Design: Synthesis and Analysis - part 7 pps
... which Williams/Rolls-Royce //www.rolls-royce.com/ F107/F1 12 700 N/A 12& quot; 40" 146 ALCM, Tomahawk FJX -2 700 N/A 14" 41" 100 V-Jet 2 FJ4 4-1 ,2 190 0 -2 300 0.456 21 " 40" 445 Premier, ... limit loads and must be investigated at airspeeds up to VC/MC. [Doc. No. 5066, 29 FR 1 829 1, Dec. 24 , 1964, as amended by Amdt. 2 5 -2 3, 35 FR 56 72, Apr....
Ngày tải lên: 08/08/2014, 11:21
Aircraft Design: Synthesis and Analysis - part 8 docx
... 3.0% 2. 7% 2. 4% Final Take-Off Segment 1.7% 1.5% 1 .2% Enroute Climb 1.6% 1.4% 1.1% Approach Segment 2. 7% 2. 4% 2. 1% Landing Segment 3 .2% 3 .2% 3 .2% The flight conditions are as follows: First Take-Off ... Stiffners 15,416 24 ,6 52 7,119 Ribs 1,463 2, 333 825 Wing Box Weight 22 ,718 33, 623 10,387 Total Wing Weight 33,604 49 ,29 8 20 ,861 Bending / Total .387 .443 .28 7 Box...
Ngày tải lên: 08/08/2014, 11:21
Aircraft Design: Synthesis and Analysis - part 9 pot
... area and structure capable of much greater range than the DC-1 0-1 0. The overwater DC-l 0-3 0 with a range comparable to the B747 would show about the same ¢/seat-mile as the B-747. Figures 13 and ... the $/stat-mile is plotted for very different sized aircraft. The DC-10 shown is the domestic version, the DC-1 0-1 0. The corresponding ¢/seat stat-mile is shown in the table of...
Ngày tải lên: 08/08/2014, 11:21
Aircraft Design: Synthesis and Analysis - part 10 doc
... 199.3 20 0.9 20 2.0 20 2.9 195.4 1979 20 4.7 20 7.1 20 9.1 21 1.5 21 4.1 21 6.6 21 8.9 22 1.1 22 3.4 22 5.4 22 7.5 22 9.9 21 7.4 1980 23 3 .2 236.4 23 9.8 24 2.5 24 4.9 24 7.6 24 7.8 24 9.4 25 1.7 25 3.9 25 6 .2 258.4 24 6.8 1981 ... 24 6.8 1981 26 0.5 26 3 .2 265.1 26 6.8 26 9.0 27 1.3 27 4.4 27 6.5 27 9.3 27 9.9 28 0.7 28 1.5 27 2.4 19 82 2 82. 5...
Ngày tải lên: 08/08/2014, 11:21