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Aircraft Design: Synthesis and Analysis - part 8 docx

Aircraft Design: Synthesis and Analysis - part 8 docx

Aircraft Design: Synthesis and Analysis - part 8 docx

... a fully-stressed beam. A derivation is given here.Wing Weight Breakdown DC- 8- 5 5 DC-1 0-1 0 STOL StudyWing Bending Material 13,115 21 ,83 0 5, 983 Wing Spars, Webs, Stiffeners2,301 2 ,82 2 1,136Bending, ... 24,652 7,119Ribs 1,463 2,333 82 5Wing Box Weight 22,7 18 33,623 10, 387 Total Wing Weight 33,604 49,2 98 20 ,86 1Bending / Total . 387 .443 . 287 Box / Total .676 . 682 .4 98 Detailed Wing Weight Buildup ... Subtract 8. 5% for all-cargo aircraft. 5. Landing GearGear weight is about 4.0% of the take-off weight. This is the total landing gear weight including structure, actuating system, and the...
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Aircraft Design: Synthesis and Analysis - part 1 doc

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 -8 0 and MD-90 series. The MD-90 weighs as much as 172,000 lbs and can carry ... first to fly. Aircraft Design: Synthesis and Analysis The Airline IndustryIn order to understand how new aircraft might fit into the current market, one must understand the ?customer?. ... McGraw-Hill.Raymer, D., Aircraft Design-A Conceptual Approach, AIAA, 1992.Roskam, J., Aircraft Design, Published by the author as an 8 volume set, 1 98 5-1 990. Nicolai, L.M., Fundamentals of Aircraft...
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Aircraft Design: Synthesis and Analysis - part 2 pptx

Aircraft Design: Synthesis and Analysis - part 2 pptx

... 98 163.3 303 125.7 442 140 .8 1 983 31 140.9 105 175.0 321 133.2 4 68 149.01 984 34 154.5 1 18 196.7 352 146.1 513 163.41 985 34 154.5 124 206.7 382 1 58. 5 561 1 78. 71 986 36 163.6 125 2 08. 3 431 1 78. 8 ... for the aircraft. 1990 55 250.0 221 3 68. 3 485 201.2 783 249.41991 51 231 .8 212 353.3 469 194.6 760 242.01992 55 250.0 239 3 98. 3 484 200 .8 806 256.71993 57 259.1 245 4 08. 3 487 202.1 81 4 259.2* ... 1 78. 71 986 36 163.6 125 2 08. 3 431 1 78. 8 622 1 98. 11 987 42 190.9 151 251.7 459 190.5 681 216.91 988 48 2 18. 2 180 300.0 475 197.1 726 231.21 989 50 227.3 197 3 28. 3 472 195.9 744 236.9ShortcutsGoInside...
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Aircraft Design: Synthesis and Analysis - part 3 ppt

Aircraft Design: Synthesis and Analysis - part 3 ppt

... 717. Note the fuselage nose and tailcone shapes.Two-Class 717 configuration with 8 first-class seats with 36" pitch and 98 coach seats with 32" pitch.Single-class 717 configuration with ... component at zero-lift and a lift-dependent component but includes only the increments due to Mach number (CL and Re are assumed to be constant.)Zero-lift drag is the drag at M=0.5 and CL = 0. ... drag, and miscellaneous items.The Lift-Dependent drag, sometimes called induced drag, includes the usual lift- dependent vortex drag together with lift-dependent components of skin friction and...
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Aircraft Design: Synthesis and Analysis - part 4 potx

Aircraft Design: Synthesis and Analysis - part 4 potx

... popular airfoils of the time: +- y = (t/0.2) * (.2969*x0.5 - .126*x - .3537*x2 + . 284 3*x3 - .1015*x4)The camberline of 4-digit sections was defined as a parabola from the leading edge ... numbers for which the above analysis is not appropriate.In supersonic flow an aircraft has lift and volume-dependent wave drag in addition to the viscous friction and vortex drag terms:This ... airplane components and the fuselage cross-sectional variation so that the total aircraft cross-sectional area, in a plane perpendicular to the line of flight, has a smooth and prescribed variation...
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Aircraft Design: Synthesis and Analysis - part 5 pdf

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, ... 0DC-7C 0.630 Double Slot 0.266 0DC -8 0. 587 Double Slot 0. 288 30.5DC- 9-3 0 0.590 Double Slot 0.360 24.5Figure 12. CLmax Values for a variety of transport aircraft. Here is the new section ... 3. Double-Slotted Flap and Slat SystemModern high lift systems are often quite complex with many elements and multi-bar linkages. Here is a double-slotted flap system as used on a DC -8 . For some...
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Aircraft Design: Synthesis and Analysis - part 6 pot

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 ... Airplane by Schlichting and Truckenbrodt:Position of 1/4 root chord on body as fraction of body lengthKf.1 .115.2 .172.3 .344.4 . 487 .5 . 688 .6 .88 8.7 1.146Finally, nacelles and pylons produce ... small aircraft or cargo aircraft that must operate without jet-ways. High wing designs may also be appropriate for STOL aircraft that make use of favorable engine-flap interactions and for aircraft...
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Aircraft Design: Synthesis and Analysis - part 7 pps

Aircraft Design: Synthesis and Analysis - part 7 pps

... 0.551 Rolls Tandem Fan0.95 31000 786 8 0 .81 6 0. 288 1.3 35000 12930 0 .89 3 0.354 2 60000 87 11 1.094 0.437 Overall engine efficiencies at cruise: Mach eta eta_goal source1.0 . 38 . 38 Douglas CR ... HU25CFE 7 38 6000 0.37 48& quot; 99" 1325With GE. Falcon 2000F124 6300 0 .81 36" 70" 1100Aero Vodochody L-139ALF502/507 670 0-7 80 0 0.4 3-0 .41 50" 65" 1350Ch 600, Bae-146, ... 65, 482 Overall Pressure Ratio 29.07 29. 18 18. 93Specific Fuel Consumption lb/hr/lb 0 .87 56 0 .87 28 0.9293Cruise: Cruise Altitude, ft 45000 55000 65000Installed Net Thrust, lb 29,6 28 21,911 18, 955Overall...
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Aircraft Design: Synthesis and Analysis - part 9 pot

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 ... DOC (ct/seat n.mi) $/n.mi.MD -8 1 at 500 n.mi. 6.15 8. 79MD-11 at 3000 n.mi. 5 .81 17.0374 7-4 00 at 3000 n.mi. 5.43 22. 58 Figure 12. Figure 13. Propulsion-Related Noise SourcesEngine ... in Fig. 11 where 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...
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Aircraft Design: Synthesis and Analysis - part 10 doc

Aircraft Design: Synthesis and Analysis - part 10 doc

... 84 .319 58 85.7 85 .8 86.4 86 .6 86 .6 86 .7 86 .8 86 .7 86 .7 86 .7 86 .8 86.7 86 .61959 86 .8 86.7 86 .7 86 .8 86.9 87 .3 87 .5 87 .4 87 .7 88 .0 88 .0 88 .0 87 .31960 87 .9 88 .0 88 .0 88 .5 88 .5 88 .7 88 .7 88 .7 88 .8 89.2 ... 80 .1 80 .1 80 .1 80 .4 80 .2 80 .5 80 .5 80 .6 80 .4 80 .21956 80 .3 80 .3 80 .4 80 .5 80 .9 81 .4 82 .0 81 .9 82 .0 82 .5 82 .5 82 .7 81 .41957 82 .8 83.1 83 .3 83 .6 83 .8 84.3 84 .7 84 .8 84.9 84 .9 85 .2 85 .2 84 .319 58 ... 80 .1 80 .0 80 .1 80 .1 80 .0 79.51953 79 .8 79.4 79.6 79.7 79.9 80 .2 80 .4 80 .6 80 .7 80 .9 80 .6 80 .5 80 .11954 80 .7 80 .6 80 .5 80 .3 80 .6 80 .7 80 .7 80 .6 80 .4 80 .2 80 .3 80 .1 80 .51955 80 .1 80 .1 80 .1 80 .1...
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