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 Study Wing Bending Material 13,115 21 ,83 0 5, 983 Wing Spars, Webs, Stiffeners 2,301 2 ,82 2 1,136 Bending, ... 24,652 7,119 Ribs 1,463 2,333 82 5 Wing Box Weight 22,7 18 33,623 10, 387 Total Wing Weight 33,604 49,2 98 20 ,86 1 Bending / Total . 387 .443 . 287 Box / Total .676 . 6...
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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 Industry In order to understand how new aircraft might fit into the current m...
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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 68 149.0 1 984 34 154.5 1 18 196.7 352 146.1 513 163.4 1 985 34 154.5 124 206.7 382 1 58. 5 561 1 78. 7 1 986 36 163.6 125 2 08. 3 431 1 78. 8 ... for the aircraft. 1990 55 250.0 221 3 68. 3 485 201.2 783 249.4 1991 51 231 .8 212 353.3 469 194.6 760 242.0 1992 55 250.0 239 3 98. 3 484 200 .8 806 256.7 1993 57 259.1 245...
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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 (C L and Re are assumed to be constant.) Zero-lift drag is the drag at M=0...
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Aircraft Design: Synthesis and Analysis - part 4 potx
... popular airfoils of the time: +- y = (t/0.2) * (.2969*x 0.5 - .126*x - .3537*x 2 + . 284 3*x 3 - .1015*x 4 ) 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 vor...
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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, ... 0 DC-7C 0.630 Double Slot 0.266 0 DC -8 0. 587 Double Slot 0. 288 30.5 DC- 9-3 0 0.590 Double Slot 0.360 24.5 Figure 12. C Lmax Values for a variety of transport aircraft. Here...
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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 length Kf .1 .115 .2 .172 .3 .344 .4 . 487 .5 . 688 .6 .88 8 .7 1.146 Finally, nac...
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Aircraft Design: Synthesis and Analysis - part 7 pps
... 0.551 Rolls Tandem Fan 0.95 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 source 1.0 . 38 . 38 Douglas CR ... HU25 CFE 7 38 6000 0.37 48& quot; 99" 1325 With GE. Falcon 2000 F124 6300 0 .81 36" 70" 1100 Aero Vodochody L-139 ALF502/507 670 0-7 80 0 0.4 3-0 .41 50" 65&q...
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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. 79 MD-11 at 3000 n.mi. 5 .81 17.03 74 7-4 00 at 3000 n.mi. 5.43 22. 58 Figure 12. Figure 13. Propulsion-Related No...
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Aircraft Design: Synthesis and Analysis - part 10 doc
... 84 .3 19 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 .6 1959 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 .3 1960 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 .2 1956 80 .3 80 .3 80 .4 80 .5 80 .9 81 .4 82...
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