Aircraft Design: Synthesis and Analysis - part 3 ppt
Aircraft Design: Synthesis and Analysis - part 3 ppt
... 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 117 seats at 32 " ... 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...
Aircraft Design: Synthesis and Analysis - part 2 pptx
... 431 137 .3
1982 30 136 .4 98 1 63. 3 30 3 125.7 442 140.8
19 83 31 140.9 105 175.0 32 1 133 .2 468 149.0
1984 34 154.5 118 196.7 35 2 146.1 5 13 1 63. 4
1985 34 154.5 124 206.7 38 2 158.5 561 178.7
1986 36 ... 100 31 4 100
1977 23 104.5 66 110.0 259 107.5 33 8 107.6
1978 25 1 13. 6 78 130 .0 2 93 121.6 39 3 125.2
1979 30 136 .4 95 158 .3 334 138 .6 455 144.9
1980 31 140.9 9...
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
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 mark...
Aircraft Design: Synthesis and Analysis - part 4 potx
... fitting a couple of popular airfoils of the time:
+- y = (t/0.2) * (.2969*x
0.5
- .126*x - .35 37*x
2
+ .28 43* x
3
- .1015*x
4
)
The camberline of 4-digit sections was defined as a parabola from ... 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...
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, ... 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 0.257 0
DC-6 0.589 Double Slot 0.266 0
DC-7C 0....
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 ... with gear attached to
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...
Aircraft Design: Synthesis and Analysis - part 7 pps
... 2000
F124 630 0 0.81 36 " 70" 1100
Aero Vodochody L- 139
ALF502/507 670 0-7 800 0.4 3- 0 .41 50" 65" 135 0
Ch 600, Bae-146, AvroRJ
Allison
http://www.allison.com/
AE3007 7200 0 .39 43& quot; ... Phoenix FanJet
TFE 731 35 0 0-5 000 0.51 40 40" 50" 73 4-9 88
Cessna/Falcon/Lear/Astra
ATF3 5400 0.50 34 " 1 03& quot; 1120
Falcon, HU25
CFE 738 6000 0 ....
Aircraft Design: Synthesis and Analysis - part 8 docx
...
Stiffners
15,416 24,652 7,119
Ribs 1,4 63 2 ,33 3 825
Wing Box Weight 22,718 33 ,6 23 10 ,38 7
Total Wing Weight 33 ,604 49,298 20,861
Bending / Total .38 7 .4 43 .287
Box / Total .676 .682 .498
Detailed ... 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, 830 5,9 83
Wing Spars, Webs,
Stiffe...
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-81 at 500 n.mi. 6.15 8.79
MD-11 at 30 00 n.mi. 5.81 17. 03
74 7-4 00 at 30 00 n.mi. 5. 43 22.58
Figure 12.
Figure 13.
Propulsion-Relate...
Aircraft Design: Synthesis and Analysis - part 10 doc
... 32 0.1 32 1 .3 322 .3 322.8
32 3.5 32 4.5 32 5.5 32 6.6 32 7.4 32 2.2
1986 32 8.4 32 7.5 32 6.0 32 5 .3 326 .3 327.9 32 8.0
32 8.6 33 0.2 33 0.5 33 0.8 33 1.1 32 8.4
1987 33 3.1 33 4.4 33 5.9 33 7.7 33 8.7 34 0.1 34 0.8
34 2.7 ... 289.1
19 83 2 93. 1 2 93. 2 2 93. 4 295.5 297.1 298.1 299 .3
30 0 .3 301.8 30 2.6 30 3.1 30 3.5 298.4
1984 30 5.2 30 6.6 30...
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