Transcript
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Subsonic Transport Composite Wing Model
Reference: Albers, R. G., Tuttle, M. E., and Avery, W. B., "Subsonic Transport Composite Wing Model
Airfoil
Reference: Selig, M., UIUC Airfoil Coordinates Database, Version 2.0 , URL http://www.ae.uiuc.edu/m-s
% Upper is the percent of the airfoil that lies above the neutral line, i.e., y = 0
Difference is the normalized airfoil thickness at each chord station% Lower is the percent of the airfoil that lies below the neutral line, i.e., y = 0
Thickness
Reference: Niu, M. C.-Y.,Airframe Structural Design: Practical Design Information and Data on Aircraft
WBL Model is the spanwise position
Upper Model is the waterline (z) position of the upper surface of the wing
Lower Model is the waterline (z) position of the lower surface of the wing
Thickness Model is the wing thickness of the wing
Thickness T/C Ratio is the thickness-to-chord ratio of the wing
Geometry
Keypoints that define ribs are listed here in the following order: upper surface, leading edge; lower sur
Wing Weight-Preliminary Design
Reference: Torenbeek, E., Development and Application of a Comprehensive, Design-Sensitive Weight
Reference: Roskam, J.,Airplane Design, Part 6: Preliminary Calculation of Aerodynamic, Thrust, and Po
Aerodynamic Loads
Reference: Garcelon, J. H., Balabanov V. O., and Sobieski J., Multidisciplinary Optimization of a Transp
Material PropertiesReference: Swanson, S. R., and Qian Y., Multiaxial Characterization of T800/3900-2 Carbon/Epoxy Co
Reference: Mabson, G. E., and Graesser D. L., Cost Optimization Software for Transport Aircraft Desig
Reference: Composite Materials Handbook, Vol. 2F: Polymer Matrix Composites Materials Properties ,
Laminate Design
Reference: Nelson, W. D., Bunin B. L., and Hart-Smith L. J., Critical Joints in Large Composite Aircraft St
Stringer Panel
Reference: Tuttle, M. E., Structural Analysis of Polymeric Composite Materials , Marcel Dekker, Inc., Ne
Applied Aero Loads
Chord No., Line No., and Normalized Initial Nodal Forces are taken directly from the Aero Loads worksh
Applied Forces and Applied Moments represent the point loads reacted at the structural box from the l
KP/HP are the Keypoint and Hardpoint numbers associated with the finite element model where the ap
Element and Element Area are the specific elements in the finite element model where the surface pre
Applied Tip Nodal Loads are the aerodynamic loads reacted at the tip of the wing structural box, and ar
Applied Tip Nodal Loads with Mass (3.75G) and (-1.5G) are the aerodynamic and mass loads reacted at
Applied Mass Loads
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Reference: Torenbeek, E., Synthesis of Subsonic Airplane Design: An Introduction to the Preliminary De
Reference: Roskam, J.,Airplane Design, Part 5: Component Weight Estimation , Roskam Aviation and E
Reference: Federal Aviation Administration, Pratt & Whitney Models PW 4062 Type Certificate Data S
Reference: General Electric Aviation, Model CF6-80C2 Engine Overview, URL http://www.geae.com/en
Reference: Jenkinson, L. R., Simpkin P., and Rhodes D., Civil Jet Aircraft Design , AIAA, Reston, VA, 1999
For LE and TE Mass Loads, node numbers are listed as the lower surface and upper surface
For TE Mass Loads, the first mass and force numbers are for the inner 2/3 of the mass, the second, theNote that the Tip Mass Loads are included on the Applied Aero Loads worksheet and are listed as uppe
For LG Mass Loads the nodes are listed as inboard upper and lower and outboard upper and lower
For Engine Mass Loads the nodes are listed as trailing to leading edges
Applied Fuel Pressures
Reference: Coordinating Research Council, Inc., Handbook of Aviation Fuel Properties , Society of Auto
Volume ID is the same as bay number, i.e., volume 1 is contained by ribs 1 & 2
Cell Lower Area and Fuel Load, along with bay volume, is used to calculate the Total Pressure in a given
Height is the inboard TE line or smallest inboard line height, and is used to calculate the shared rib net
KP is the keypoint at which the Z Coordinate is defined; this is used in ANSYS to define the linear variati
Emergency Landing Loads
Reference: Niu, M. C.-Y.,Airframe Stress Analysis and Sizing , Conmilit Press Ltd., Hong Kong, 1997
Reference: Howe, D.,Aircraft Loading and Structural Layout, AIAA, Reston, VA, 2004
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for Optimization Studies", Proceedings of the 12th AIAA/ISSMO Multidisciplinary Analysis and Optim
elig/ads/coord_database.html - B, Nov. 11, 2005 [cited March 13, 2006]
Structures , Conmilit Press Ltd., Hong Kong, 1988
ace, leading edge; lower surface, trailing edge; and upper surface, trailing edge
Prediction Method for Wing Structures for Transport Category Aircraft, Delft University of Technology
wer Characteristics , Roskam Aviation and Engineering Corp., Ottawa, KS, 1990
rt Aircraft Wing Using VisualDOC, Proceedings of the 40th AIAA/ASME/ASCE/AHS/ASC Structures, Stru
posites, Composites Science and Technology, Vol. 43, No. 2, 1992, pp. 197-203
Evaluation (COSTADE)--User's Manual, NASA Langley Research Center, Report NASA CR-4738, Hampt
Section 4.2.33: T700S 12k/3900-2 Plain Weave Fabric, and Section 4.2.34: T800HB 12k/3900-2 Unid
ructure, NASA, Report NASA CR 3710, Washington, DC, Aug., 1983
w York, NY, 2004
eet
eading and trailing edges
plied forces and moments are applied
sures are applied on the lower wing surface
listed from the leading to trailing edges
he tip of the wing structural box
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sign of Subsonic General Aviation and Transport Aircraft, with Emphasis on Layout, Aerodynamic Design,
ngineering Corp., Ottawa, KS, 1989
heet, FAA, Report TCDS No. E24NE, Washington, DC, Apr. 19, 2002
gines/commercial/cf6/cf6-80c2.html [cited Mar. 27, 2006]
uter 1/3 of the massleading, lower leading, upper trailing, and lower trailing edges
otive Engineers, Inc., CRC Report No. 530, Warrendale, PA, 1983
fuel bay
ressure
n of the presssure on the ribs and spars
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ization Conference , Victoria, British Columbia, Canada, AIAA, Reston, VA, September 10-12, 2008, AI
, Report LR-693, Delft, The Netherlands, Sep., 1992
ctural Dynamics, and Materials Conference, St. Louis, MO, AIAA, Reston, VA, Apr. 12-15, 1999, pp. 1306
n, VA, Aug., 1996
irectional Tape, U.S. Department of Defense, MIL-HDBK-17-2F, Washington, DC, June 17, 2002, pp. 4-2
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Propulsion, and Performance , Delft University Press, Delft, The Netherlands, 1982
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A-2008-6016
-1313
43--4-254
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Boeing BACXXX Airfoil
X Y
Upper 0 0 % Upper Difference
Surface 0.0005 0.0037 0.672727 0.0055
0.001 0.005 0.649351 0.0077
0.0025 0.0078 0.644628 0.01210.005 0.0112 0.658824 0.017
0.015 0.0207 0.678689 0.0305
0.02 0.0242 0.683616 0.0354
0.025 0.0271 0.684343 0.0396
0.0375 0.0334 0.687243 0.0486
0.05 0.0384 0.686941 0.0559
0.075 0.0465 0.682819 0.0681
0.1 0.0521 0.672258 0.0775
0.125 0.0566 0.662763 0.0854
0.15 0.0599 0.651795 0.0919
0.2 0.0643 0.631631 0.1018
0.25 0.0665 0.614603 0.1082
0.3 0.0674 0.602324 0.1119
0.35 0.0673 0.595049 0.1131
0.4 0.0667 0.593416 0.1124
0.45 0.0654 0.596171 0.1097
0.5 0.0636 0.603989 0.1053
0.55 0.0613 0.615462 0.0996
0.6 0.0585 0.629709 0.0929
0.65 0.0548 0.643948 0.0851
0.7 0.0503 0.65924 0.07630.75 0.045 0.673653 0.0668
0.8 0.0384 0.688172 0.0558
0.85 0.0307 0.699317 0.0439
0.9 0.0218 0.707792 0.0308
0.95 0.0116 0.711656 0.0163
1 0.0004 0.5 0.0008
Lower 0 0 % Lower
Surface 0.0005 -0.0018 0.327273 1
0.001 -0.0027 0.350649 1
0.0025 -0.0043 0.355372 1
0.005 -0.0058 0.341176 1
0.015 -0.0098 0.321311 1
0.02 -0.0112 0.316384 1
0.025 -0.0125 0.315657 1
0.0375 -0.0152 0.312757 1
0.05 -0.0175 0.313059 1
0.075 -0.0216 0.317181 1
0.1 -0.0254 0.327742 1
-0.3
-0.2
-0.1
0
0.1
0.2
0.3
0 0.1 0.2
0 0.1 0.2
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0.125 -0.0288 0.337237 1
0.15 -0.032 0.348205 1
0.2 -0.0375 0.368369 1
0.25 -0.0417 0.385397 1
0.3 -0.0445 0.397676 1
0.35 -0.0458 0.404951 1
0.4 -0.0457 0.406584 10.45 -0.0443 0.403829 1
0.5 -0.0417 0.396011 1
0.55 -0.0383 0.384538 1
0.6 -0.0344 0.370291 1
0.65 -0.0303 0.356052 1
0.7 -0.026 0.34076 1
0.75 -0.0218 0.326347 1
0.8 -0.0174 0.311828 1
0.85 -0.0132 0.300683 1
0.9 -0.009 0.292208 1
0.95 -0.0047 0.288344 1
1 -0.0004 0.5 1
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y = -4.5841x6 + 15.483x5 - 20.573x4 + 13.558x3 - 4.7301x2 + 0.8405x + 0.0057R = 0.9933
y = 1.9658x6 - 5.8973x5 + 6.6877x4 - 3.7444x3 + 1.3244x2 - 0.3328x - 0.0032R = 0.9951
0.3 0.4 0.5 0.6 0.7 0.8 0.9 1
Series1
Series2
Poly. (Series1)
Poly. (Series2)
0.3 0.4 0.5 0.6 0.7 0.8 0.9 1
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WBL Model (m) Upper Model (m) Lower Model (m) Thickness Model (m) Thickness T/C Ratio
0 0.71558463 -0.817376808 1.532961438 1.532961438
2.4304625 0.71558463 -0.817376808 1.532961438 1.532961438
3.057525 0.654092854 -0.690536999 1.344629853 1.463712413
3.72745 0.603711297 -0.625910716 1.229622013 1.392100378
4.397375 0.561679724 -0.571995265 1.133674988 1.321783631
5.0673 0.525619892 -0.525739988 1.05135988 1.2526236995.737225 0.494044094 -0.485236545 0.979280639 1.184656111
6.40715 0.465959479 -0.449211372 0.915170851 1.117846076
7.077075 0.440670327 -0.416772044 0.857442371 1.052227645
7.747 0.417670168 -0.38726889 0.804939058 0.99673918
8.512175 0.393717188 -0.356543518 0.750260706 0.934128408
9.27735 0.371827437 -0.328464727 0.700292164 0.88601358
9.8218625 0.357323482 -0.309859967 0.667183449 0.854401582
10.3647875 0.343641258 -0.292309274 0.635950531 0.823259215
10.9093 0.330620744 -0.275607379 0.606228123 0.792521583
11.4538125 0.318234552 -0.259719154 0.577953705 0.764393697
11.9967375 0.306457386 -0.244612149 0.551069535 0.73238886
12.54125 0.295169397 -0.230132628 0.525302026 0.702963463
13.084175 0.284392094 -0.216308183 0.500700277 0.674003414
13.6286875 0.274023403 -0.20300788 0.477031283 0.645452057
14.1732 0.264060968 -0.190228698 0.454289666 0.617338562
14.716125 0.254501584 -0.177966522 0.432468106 0.589688253
15.2606375 0.24526211 -0.166114708 0.411376817 0.562449116
15.8035625 0.236372141 -0.154711216 0.391083357 0.535671726
16.348075 0.227757788 -0.143661268 0.371419056 0.509306947
16.8925875 0.219425709 -0.132973402 0.352399111 0.48337941
17.4355125 0.211381142 -0.12265434 0.334035482 0.45791205617.980025 0.203560821 -0.112622925 0.316183746 0.433589461
18.52295 0.195995629 -0.102918774 0.298914403 0.412405266
19.0674625 0.188627835 -0.093467832 0.282095666 0.391703313
19.3278125 0.185179076 -0.089043982 0.274223057 0.38184329
19.58975 0.181755855 -0.084652889 0.266408744 0.372054454
20.170775 0.174323097 -0.075118617 0.249441713 0.350556528
20.7533875 0.167081978 -0.065830166 0.232912143 0.329460839
21.3344125 0.160060273 -0.056823166 0.216883439 0.308790056
21.9154375 0.153227253 -0.048058199 0.201285452 0.288532561
22.49805 0.146555097 -0.039499578 0.186054675 0.268678998
23.079075 0.140071026 -0.03118222 0.171253246 0.249462918
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Rib
1
2
3
4
7
89
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
2930
31
32
33
34
35
36
37
38
39
40
-1
-0.8
-0.6
-0.4
-0.2
0
0.2
0.4
0.6
0.8
0 5 10 15 20
WaterlineStat
ion(m)
Semi-Span (m)
Waterline vs. Span for the Wing Model Upper an
Surfaces
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5
Lower
Upper Model (m)
Lower Model (m)
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Structure Geometry Wing Panel Stringers
Rib Keypoints X (m) Y (m) Z (m) Stringer Spacing 0.205 m
1 14 2.43 1.98 -0.649 8.070866142 in
17 2.43 1.98 0.472 Panel No. No. of Stringers
16 2.43 6.84 0.378 1 21
15 2.43 6.84 -0.537 2 21
2 1 1.63 1.98 -0.649 3 212 1.63 1.98 0.472 4 6
3 1.63 6.84 0.378 5 12
4 1.63 6.84 -0.537 6 20
3 5 0.80 1.98 -0.649 7 19
6 0.80 1.98 0.472 8 18
7 0.80 6.84 0.378 9 18
8 0.80 6.84 -0.537 10 17
4 146 0.00 1.98 -0.649 11 17
147 0.00 1.98 0.472 12 16
148 0.00 6.84 0.378 13 15
13 0.00 6.84 -0.537 14 15
5 158 -0.74 2.48 -0.659 15 14
155 -0.74 2.46 0.488 16 14
156 0.00 3.60 0.558 17 13
157 0.00 3.62 -0.683 18 13
6 154 -1.48 2.97 -0.667 19 12
151 -1.48 2.95 0.504 20 12
152 0.00 5.22 0.506 21 11
153 0.00 5.24 -0.639 22 11
7 149 -2.22 3.43 -0.674 23 10
150 -2.22 3.43 0.474 24 10148 0.00 6.84 0.378 25 9
13 0.00 6.84 -0.537 26 9
8 145 -2.80 3.80 -0.663 27 8
142 -2.80 3.80 0.428 28 8
143 -0.64 7.14 0.279 29 7
144 -0.64 7.14 -0.523 30 7
9 141 -3.36 4.17 -0.646 31 6
138 -3.36 4.17 0.417 32 6
139 -1.24 7.42 0.272 33 6
140 -1.24 7.42 -0.510 34 5
10 137 -3.91 4.53 -0.629 35 5
134 -3.91 4.53 0.406 36 4
135 -1.85 7.71 0.265 37 4
136 -1.85 7.71 -0.497 38 3
11 133 -4.47 4.89 -0.612 39 3
130 -4.47 4.89 0.395
131 -2.46 7.99 0.258
132 -2.46 7.99 -0.483
12 129 -5.03 5.25 -0.595
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126 -5.03 5.25 0.385
127 -3.06 8.27 0.251
128 -3.06 8.27 -0.470
13 125 -5.75 5.72 -0.573
122 -5.75 5.72 0.370
123 -3.85 8.64 0.242
124 -3.85 8.64 -0.45314 121 -6.48 6.19 -0.551
118 -6.48 6.19 0.356
119 -4.64 9.01 0.232
120 -4.64 9.01 -0.436
15 117 -6.99 6.52 -0.535
114 -6.99 6.52 0.346
115 -5.21 9.27 0.226
116 -5.21 9.27 -0.424
16 113 -7.50 6.86 -0.520
110 -7.50 6.86 0.336
111 -5.77 9.53 0.219
112 -5.77 9.53 -0.412
17 109 -8.02 7.19 -0.504
106 -8.02 7.19 0.326
107 -6.33 9.80 0.213
108 -6.33 9.80 -0.400
18 105 -8.54 7.53 -0.488
102 -8.54 7.53 0.316
103 -6.89 10.10 0.207
104 -6.89 10.10 -0.387
19 101 -9.05 7.86 -0.47398 -9.05 7.86 0.305
99 -7.45 10.30 0.200
100 -7.45 10.30 -0.375
20 97 -9.56 8.20 -0.457
94 -9.56 8.20 0.295
95 -8.02 10.60 0.194
96 -8.02 10.60 -0.363
21 93 -10.10 8.53 -0.441
90 -10.10 8.53 0.285
91 -8.58 10.80 0.187
92 -8.58 10.80 -0.351
22 89 -10.60 8.86 -0.426
86 -10.60 8.86 0.275
87 -9.14 11.10 0.181
88 -9.14 11.10 -0.339
23 85 -11.10 9.20 -0.410
82 -11.10 9.20 0.265
83 -9.70 11.40 0.174
84 -9.70 11.40 -0.327
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24 81 -11.60 9.53 -0.394
78 -11.60 9.53 0.255
79 -10.30 11.60 0.168
80 -10.30 11.60 -0.314
25 77 -12.10 9.87 -0.379
74 -12.10 9.87 0.245
75 -10.80 11.90 0.16176 -10.80 11.90 -0.302
26 73 -12.70 10.20 -0.363
70 -12.70 10.20 0.235
71 -11.40 12.20 0.155
72 -11.40 12.20 -0.290
27 69 -13.20 10.50 -0.347
66 -13.20 10.50 0.224
67 -11.90 12.40 0.148
68 -11.90 12.40 -0.278
28 65 -13.70 10.90 -0.332
62 -13.70 10.90 0.214
63 -12.50 12.70 0.142
64 -12.50 12.70 -0.266
29 61 -14.20 11.20 -0.316
58 -14.20 11.20 0.204
59 -13.10 12.90 0.135
60 -13.10 12.90 -0.254
30 57 -14.70 11.50 -0.300
54 -14.70 11.50 0.194
55 -13.60 13.20 0.129
56 -13.60 13.20 -0.24131 53 -15.20 11.90 -0.285
50 -15.20 11.90 0.184
51 -14.20 13.50 0.122
52 -14.20 13.50 -0.229
32 49 -15.70 12.20 -0.269
46 -15.70 12.20 0.174
47 -14.80 13.70 0.116
48 -14.80 13.70 -0.217
33 45 -16.00 12.40 -0.262
42 -16.00 12.40 0.169
43 -15.00 13.80 0.113
44 -15.00 13.80 -0.211
34 41 -16.20 12.50 -0.254
38 -16.20 12.50 0.164
39 -15.30 14.00 0.110
40 -15.30 14.00 -0.205
35 37 -16.80 12.90 -0.237
34 -16.80 12.90 0.153
35 -15.90 14.30 0.103
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ANSYS Model Areas
Upper Skin Lower Skin Front Spar Rear Spar Ribs
Panel No. Area Panel No. Area Panel No. Area Panel No. Area No.
1 40 1 1 1 118 1 157 1
2 41 2 2 2 119 2 158 2
3 48 3 193 3 120 3 159 3
4 6 4 4 4 121 4 160 45 7 5 5 5 122 5 161 5
6 43 6 82 6 123 6 162 6
7 42 7 44 7 124 7 163 7
8 83 8 8 8 125 8 164 8
9 84 9 9 9 126 9 165 9
10 88 10 10 10 127 10 166 10
11 89 11 11 11 128 11 167 11
12 90 12 12 12 129 12 168 12
13 91 13 13 13 130 13 169 13
14 92 14 14 14 131 14 170 14
15 93 15 15 15 132 15 171 15
16 94 16 16 16 133 16 172 16
17 95 17 17 17 134 17 173 17
18 96 18 18 18 135 18 174 18
19 97 19 19 19 136 19 175 19
20 98 20 20 20 137 20 176 20
21 99 21 21 21 138 21 177 21
22 100 22 22 22 139 22 178 22
23 101 23 23 23 140 23 179 23
24 102 24 24 24 141 24 180 24
25 103 25 25 25 142 25 181 2526 104 26 26 26 143 26 182 26
27 105 27 27 27 144 27 183 27
28 106 28 28 28 145 28 184 28
29 107 29 29 29 146 29 185 29
30 108 30 30 30 147 30 186 30
31 109 31 31 31 148 31 187 31
32 110 32 32 32 149 32 188 32
33 111 33 33 33 150 33 189 33
34 112 34 34 34 151 34 190 34
35 113 35 35 35 152 35 191 35
36 114 36 36 36 153 36 192 36
37 115 37 37 37 154 37
38 116 38 38 38 155 38
39 117 39 39 39 156 39
40
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Area
49
45
46
4887
86
85
81
80
79
78
77
76
75
74
73
72
71
70
69
68
67
66
65
6463
62
61
60
59
58
57
56
55
54
53
52
51
50
47
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Model Wing Weight Prediction
Design Weights
Maximum Take-off Weight (MTOW) 1332550.74 N
Maximum Landing Weight (MLW) 1158744.96 N
Maximum Zero Fuel Weight (MZFW) 1073770.78 N
GeometryReference Area S 283.3 m^2
Span b 42.2 m
Mid-chord sweep angle 1/2 26
Leading edge sweep angle le 33
Quarter-chord sweep angle 1/4 31.5
Root chord (y=0) cr 11.53180505 m
Tip chord (y=b/2) ct 2.197963411 m
Aspect ratio A 6.286057183
Taper ratio 0.190600119 0.245
Center section span bcs 4.860925 m
Thickness/chord ratio - root t/c 0.132933347
Thickness/chord ratio - 40% span t/c 0.084799149 Rib 14
Thickness/chord ratio - 70% span t/cref 0.087786217 Rib 26
Thickness at root (y=0) tr 1.532961438 m
Thickness at y = bcs/2 (SOB) tcs 1.532961438 m
Thickness at tip tt 0.171253246 m
Taper ratio of wing tank bar 0.241422481
Span of fuel tank bF 37.79582386 m
Mean geometric chord cbar 6.713270142 m
Mean profile thickness tref 1 m
Fixed leading edge area Sfle 50.994 m^2
Fixed trailing edge area Stfe 30.5964 m^2
Leading edge slat area Sslat 28.3 m^2
Trailing edge flap area Stef 36.88 m^2
Trailing edge spoiler area Slift 15.83 m^2
Aileron area Sa 11.2 m^2
Structural wing box area 142.8876 m^2
Design Conditions
Design cruising speed VC 236.64 m/s
Design cruising Mach number MC 0.8
Design dive speed VD 333.42576 m/s
Design dive Mach number MD 0.8624
Design dive dynamic pressure qD 68093.30168 N/m^2
Design gust speed Ude 15.25 m/s
Calculation of Input Data
Structural span bs 46.95180189 m
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Cantilever ratio RC 16.32618855
Lateral position of center of pressure cp 0.497307785
Lift-curve slope CL 5.940598648 1/rad Roskam
Mass parameter 37.74082928
Gust relief factor Kg 0.771637776
Lateral position of fuel ybar/bF/2 0.318860141
Lateral position of fuel ybar 6.025790862 mLateral position of fuel f/Lateral position of cp cp 0.574257057
Root bending moment, lift and fuel mass MBr 25916726.81 N-m
Root bending moment, gust load MBr 9402002.695 N-m
Mass relief, fuel, bending and shear (WB+S/WB+S)F -0.013550496
Estmated wing weight 12% MTOW 159906.0888 N
Mass relief, mass, bending and shear (WB+S/WB+S)W -0.096
Mass relief, powerplant (WB+S/WB+S)P -0.035
Relief factor r 0.855449504
Mean root stress level g/barr 8.09526E-05 1/m
Structural efficiency t 0.8Mean root stress / shear stress barr/bar 2.4
Weight Calculations
Bending and shear material weight, 1st term, WBASIC 69059.05433 N
Rib weight, 2nd term, WBASIC 7372.063241 N
Primary wing box weight WBASIC 76431.117573 N
Weight correction, sheet taper & joints W NOsheet 4655.428128 N 6.091011
Weight correction, SOB joint WNOsob 1332.55074 N 1.743466
Weight correction, LG attachment WNOlg 4634.97984 N 6.064258
Weight correction, engine attachment WNOeng
1838.146784 N 2.404972
Total non-optimum weight correction WNO 12461.10549 N 16.30371
Weight correction, aeroelasticity WST 19972.26556 N 26.13107
Primary Wing Structure Weight WPRIM 108864.488627 N
Fixed leading edge structure weight W fle 11535.2492 N
Fixed trailing edge structure weight W tfe 6603.275735 N
Leading edge slat weight Wslat = Wlef 8186.864577 N
Trailing edge flap weight W tef 15890.57128 N
Aileron weight (inboard & outboard) Wa 2152.088553 N
Spoiler average specific weight 110 N/m^2
Spoiler weight W lift 1741.3 N
Aileron and spoiler weight Wa+s 3893.388553 N
Flap support extra rib weight 794.5285639 N
Ailerons support extra rib weight 430.4177106 N
Support structure/extra rib weight Wmisc 1224.946275 N
Secondary Wing Structure Weight WSEC 47334.29562 N
Wing Weight Ww 156198.784250 N
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AtmosphereDensity 20000 ft. 0.65283 kg/m^3
Acceleration of gravity g 20000 ft. 9.807 m/s^s
Density SL 0 ft. 1.225 kg/m^3
Manoeuver Load Factor
nult 3.75
Powerplant
Nacelle & engine weight WP 52518.48 N
% of MTOW 7.8823985 %
Number of engines Ne 2
Materials
Specific weight, aluminum 28.1 N/m^3
Shear modulus, aluminum 2.81E+10 Pa
Constants
Correction factor for rib weight k r 5.00E-01
Non-optimum extra panel thickness NO 0.0005 m
Correction factor for stiffness weight penalty f() 0.05
Correction factor for fixed leading edge/slat strengthening k fle 1.4
Correction factor for fixed trailing edge/double slotted flaps 45
Correction factor for trailing edge double slotted variable flaps ktef 2
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4.673187017 1/rad
Aluminum
Mass (kg) Old Mass (kg)
1st term, WBASIC 25.640355 7031.05827
2nd term, WBASIC 1.8521073 750.5664061
17182.405 lbf 7781.624676
% WBASIC 473.9796506
% WBASIC 135.67
% WBASIC 471.8977642
% WBASIC
187.145875
% WBASIC 1268.69329
% WBASIC 2033.421458
24473.71952 lbf 11083.73942
1174.42977
672.2944141
833.5231702 326.4168
1617.854946 718
219.1089954 248.52
177.2856852 352.008
396.3946806 600.528
124.7145464
10641.17684 lbf 4819.211527 2245.4728
35114.89635 lbf 15902.95095
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Composite
Mass (kg) Weight (N)
8866.9915 87091.591
939.54382 9228.1994
537.83553 5282.6206
666.81854 6549.4917
1294.284 12712.457
175.2872 1721.6708
141.82855 1393.04
317.11574 3114.7108
99.771637 979.95702
3855.3692 37867.436
12722.361 124959.03
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Torenbeek Transport Airfoil Pressure Distributions
Span:
Chord (LPi) Normalized Pressure Chord Length (m)
1 1 11.53
2 0.95 10.36
3 0.85 9.19
4 0.8 8.035 0.7 6.86
6 0.6 5.69
7 0.5 4.53
8 0.15 3.36
9 0.05 2.27
Chord:
Line (CPj) Normalized Pressure
1 0.4
2 1
3 1
4 0.5
5 0.25
Torenbeek Transport Airfoil Pressure Distributions
Node Number Line Number Chord Number
1 1 1
2 2
3 3
4 4
5 5
6 6
7 7
8 8
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9 9
10 2 1
11 2
12 3
13 4
14 5
15 616 7
17 8
18 9
19 3 1
20 2
21 3
22 4
23 5
24 6
25 7
26 8
27 9
28 4 1
29 2
30 3
31 4
32 5
33 6
34 7
35 8
36 937 5 1
38 2
39 3
40 4
41 5
42 6
43 7
44 8
45 9
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Node Areas (Ai,j) (m^2) Aero Panel # Area (in^2) Area (m^2)
8.054485826 1 12484.478 8.054485826
7.629801708 2 12488.6004 8.057145434
6.779118345 3 12487.5139 8.056444468
5.924437796 4 12475.7194 8.048835128
5.075121398 5 11167.9546 7.20511759
4.225805 6 11168.0913 7.205205783
3.371124451 7 11167.1498 7.204598365
2.515598066 8 11112.5766 7.169389919
10.95
0.850.8
0
0.2
0.4
0.6
0.8
1
1.2
1 2 3 4 5
NormalizedPressure
Chord Num
Span
0.4
1
0
0.2
0.4
0.6
0.8
1
1.2
1 2 3
Normalized
Pressure
Line Numb
Chord
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2.086070925 9 9847.3543 6.3531191
8.05581563 10 9847.5822 6.353266132
7.630488658 11 9846.7856 6.352752198
6.779177151 12 9749.4337 6.289944646
5.914486848 13 8518.4396 5.495756492
5.065199918 14 8456.5157 5.455805669
4.225952096 15 8566.9999 5.5270856553.371300903 16 8386.2908 5.410499373
2.51580342 17 7214.4682 4.654486304
2.086290473 18 7214.8788 4.654751207
8.056794951 19 7255.0357 4.680658832
7.630848512 20 7023.148 4.531054164
6.778955619 21 5885.5535 3.797123696
5.922227414 22 5886.0549 3.797447179
5.079575341 23 5885.6932 3.797213825
4.232517761 24 5660.0051 3.65160889
3.371384048 25 4564.9532 2.945125207
2.515962226 26 4565.5458 2.945507528
2.086486859 27 4565.329 2.945367658
8.052639798 28 4296.8622 2.772163617
7.61981697 29 3233.4164 2.086070925
6.754171282 30 3234.097 2.086510021
5.895070468 31 3234.0252 2.086463698
5.037324506 32 2924.1856 1.886567582
4.165133928
3.291588497
2.422640639
1.986515648.048835128
7.609112524
6.729667283
5.850222009
4.970776768
4.091331527
3.211886254
2.329365599
1.886567582
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Normalized Initial Nodal Forces (N)
17479.76782
15730.2163
12505.18092
10285.72642
7709.785816
5502.480866
3657.990961
818.8990158
0.70.6
0.5
0.150.05
6 7 8 9
ber
1
0.5
0.25
4 5
er
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226.3585547
43706.63436
39329.08143
31263.22349
25671.12516
19236.78441
13756.681019145.456068
2047.414661
565.9559444
43711.94764
39330.93619
31262.20187
25704.72216
19291.37987
13778.05412
9145.681618
2047.543901
566.009219
21844.70198
19637.0387
15573.95253
12793.42534
9565.459124
6779.350249
4464.608599
985.7983981
269.444823210917.19045
9804.726127
7758.72527
6348.047821
4719.54526
3329.613151
2178.251473
473.9218933
127.9440892
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Material Properties
T800HB / 3900-2 Carbon/Epoxy Unidirectional Laminate
E11 155.8 GPa Swanson
E22 8.89 GPa Swanson
E33 8.89 GPa COSTADE
12 0.3 Swanson
13 0.3 COSTADE23 0.3675 COSTADE
G12 5.14 GPa Swanson
G13 5.14 GPa COSTADE
G23 3.517 GPa COSTADE
t 0.0001905 m MIL-HDBK-17
density 1550 kg/m^3 MIL-HDBK-17
T700S / 3900-2 Carbon/Epoxy Plain Weave Laminate MIL-HDBK-17
*E11t 73.65 GPa MIL-HDBK-17 *Knockdown facters b
*E11c 70.82 GPa MIL-HDBK-17 4.2.35, T650-35 3K / 9
*E22t 60.38 GPa MIL-HDBK-17
*E22c 70.82 GPa COSTADE E11t 22
E33 10.26 GPa COSTADE E11c
*G12 5.52 GPa MIL-HDBK-17 E22t 1.3
G13 3.83 GPa COSTADE E22c 1.38
G23 3.83 GPa COSTADE G12 0.745
*12 0.046 COSTADE t 0.0052
13 0.4 COSTADE E11t 10.4
23 0.4 COSTADE E11c 10
t 0.000201 m MIL-HDBK-17 E22t 8.83
density 1530 kg/m^3 MIL-HDBK-17 E22c 8.82G12 0.8
Titanium 6Al4V MIL-HDBK-5 t 0.0069
Et 116.52 GPa
Ec 118.59 GPa E11t 47.27273
0.31 E11c 96.15385
G 44.82 GPa E22t 679.2308
density 4428.78 kg/m^3 E22c 639.1304
G12 107.3826
t 132.6923
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sed on material 4.2.29, T650-35 12K / 976 Uni Tape vs.
6 Plain Weave Fabric
Msi
Msi
Msi
Msi
Msi
in
Msi
Msi
Msi
MsiMsi
in
%
%
%
%
%
%
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Composite Joint Laminate Design
Ply Thickness (m) 0.000191
Plain Weave Ply Thickness (m) 0.000201
Orientation () 0 plies 45 plies 90 plies
PW 45
1 45 1
2 0 13 0 1
4 -45 1
5 90 1
6 -45 1
7 0 1
8 45 1
9 45 1
10 0 1
11 0 1
12 -45 1
13 90 1
14 -45 1
15 0 1
16 45 1
17 45 1
18 0 1
19 0 1
20 -45 1
21 90 1
22 -45 1
23 0 124 45 1
25 45 1
26 0 1
27 0 1
28 -45 1
29 90 1
30 -45 1
31 0 1
32 45 1
33 45 1
34 0 1
35 0 1
36 -45 1
37 90 1
38 -45 1
39 0 1
40 45 1
41 45 1
42 0 1
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43 0 1
44 -45 1
45 90 1
46 -45 1
47 0 1
48 45 1
98 Count 18 24 61 % 0.375 0.5 0.125
0.018689 Thickness 0.006858 0.009144 0.002286
Laminate Stacking Sequence Rules (Nelson 1983)
1. Changes of only 45 degrees are allowed between interior plies
2. No stacked plies except at the midplane
3. Symmetry required
4. 37.5% 0 / 50% 45 / 12.5% 90
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Equivalent I-stringer Stiffness Ply
Composite I-Beam
bbf (m) bbf (in) tbf (m) h (m) h (in)
0.0635 2.5 0.018689 0.1016 4
a11bf a11w a11tf d11bf d11tf
7.225E-10 7.225E-10 7.23E-10 0.000025067 0.000025067
Composite Panel Stiffness Bay 5 12 stringers
tsk (m) tst (m) wsk (m) wst (m) Ask (m^2)
0.01868932 0.01868932 2.979029 0.2286 0.055676029
Composite I-Beam Plate Equivalent
s (m) tI (m) tsk (m) Ebarxxex/I (Pa) Ebarxxex/sk (Pa)
0.205 0.086328904 0.018689 17890000000 74057431998
Density:
Prepreg Density (kg/m^3) Stringer Mass (kg) Stringer Density (kg/m^3)
1550 6.622186756 374.1893
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tw (m) btf (m) btf (in) ttf (m) Abf (m^2) Aw (m^2)
0.01868932 0.0635 2.5 0.01868932 0.001186772 0.001899
Ebarxxex/bf (Pa) Ebarxxex/w (Pa) Ebarxxex/tf (Pa) Ebarxxfl/bf (Pa) Ebarxxfl/tf (Pa) zb (m)
74057431998 74057431998 74057431998 73332819771 73332819771 0.069489
Ast (m^2) a11sk a11st Ebarxxsk (Pa) Ebarxxst (Pa)
0.004272379 7.225E-10 7.225E-10 74057431998 74057431998 0.520606
a11I AI (m^2) Ask (m^2) Isk (m^4) Ebarxxfl/sk (Pa) zb (m)
6.47491E-10 0.017697425 0.003831311 1.1152E-07 73332819771 0.067982
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Atf (m^2) Ibf (m^4) Itf (m^4) Total Height (m) Total Height (in)
0.001187 3.4544E-08 3.4544E-08 0.13897864 5.4716
zb (in) AEbarxx/beam (N) IEbarxx/beam (N-m^2)
2.7358 316401384.1 761889.8832
a11sk-st
3.76E-10 Constant cross section I stringer
zb (in) AEbarxxbeam (N) EIbarxxbeam (N-m^2)
2.676438 600343964.5 390681.3388
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Chord No. (Span) Line No. (Chord) Normalized Initial Nodal Forces (N) Applied Forces (N)
1 1 17479.76782
2 43706.63436 61186.40218
3 43711.94764 43711.94764
4 21844.70198 32761.89243
5 10917.19045
2 1 15730.2163 15730.21632 39329.08143 39329.08143
3 39330.93619 39330.93619
4 19637.0387 29441.76482
5 9804.726127
3 1 12505.18092 12505.18092
2 31263.22349 31263.22349
3 31262.20187 31262.20187
4 15573.95253 23332.6778
5 7758.72527
4 1 10285.72642 10285.72642
2 25671.12516 25671.12516
3 25704.72216 25704.72216
4 12793.42534 19141.47316
5 6348.047821
5 1 7709.785816 7709.785816
2 19236.78441 19236.78441
3 19291.37987 19291.37987
4 9565.459124 14285.00438
5 4719.54526
6 1 5502.480866 5502.480866
2 13756.68101 13756.681013 13778.05412 13778.05412
4 6779.350249 10108.9634
5 3329.613151
7 1 3657.990961 3657.990961
2 9145.456068 9145.456068
3 9145.681618 9145.681618
4 4464.608599 6642.860072
5 2178.251473
8 1 818.8990158
2 2047.414661 2866.313677
3 2047.543901 2047.543901
4 985.7983981 1459.720291
5 473.9218933
9 1 226.3585547
2 565.9559444 170.91
3 566.009219 1105.4
4 269.4448232 479.39
5 127.9440892
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Applied Tip Nodal Loads
Node FX (N) FY (N) MX (N-M)
9198 0 0.41933 -68.8
9197 0 0.41933 -68.8
6031 -1.3369 0.41933 -68.8
6099 -1.3369 0 0
6100 -1.3369 0 06101 -4.593 -1.389867 -196.367
6102 -4.593 -1.389867 -196.367
6103 -4.593 -1.389867 -196.367
6104 5.93 0 0
6105 5.93 0 0
6032 5.93 0.9705333 -109.7867
7197 0 0.9705333 -109.7867
7198 0 0.9705333 -109.7867
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Applied Moments (N-m) KP/HP Element Element Area (m^2)
17 847
61529.61579 17 847 0.08134066
0 316 855 0.131492351
-52769.62743 16 863 0.077316967
16 863
23138.25242 317 986 0.0396681520 318 990 0.048097575
0 319 3960 0.067477113
-70701.67068 320 3984 0.057599803
320 3984
17297.12971 321 3404 0.088794123
0 322 3398 0.106622506
0 323 3456 0.109169418
-48002.97498 324 3496 0.080190269
324 3496
13325.22423 325 3522 0.082512454
0 326 3556 0.083908975
0 327 3586 0.08345952
-32861.08761 328 3611 0.073603613
328 3611
9312.146823 329 3658 0.092213192
0 330 3667 0.098259432
0 331 3702 0.094904571
-19628.79238 332 3715 0.052029771
332 3715
6163.680091 333 3765 0.083122428
0 334 3774 0.0938718950 335 3794 0.094915272
-10397.82109 336 3812 0.094085921
336 3812
3758.854018 50 3851 0.089323838
0 337 3858 0.081035673
0 338 3876 0.085273392
-4613.915481 339 3885 0.066273215
339 3885
340 3930
773.6848849 340 3930 0.081180141
0 341 3936 0.129908557
-419.0059835 342 3941 0.082046947
342 3941
340 3930
NA 340 3930 0.081180141
NA 343 3948 0.11890761
NA 12 3949 0.055759178
12 3949
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Applied Tip Nodal Loads with Mass (3.75G)
MY (N-m) MZ (N-m) Node
0 0.94124 9198
0 0.94124 9197
-214.5033 0.94124 6031
-214.5033 0.94124 6099
-214.5033 0.94124 6100-612.733 5.60933 6101
-612.733 5.60633 6102
-612.733 5.60633 6103
-389.433 -1.90056 6104
-389.433 -1.90056 6105
-389.433 -1.90056 6032
0 -1.9705333 7197
0 -1.90056 7198
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Applied Surface Pressure (Pa)
752224.0667
332429.5842
423734.8348
396545.2223817693.6529
582878.1744
511143.4977
140833.4304
293214.1129
286364.0981
290966.4477
124656.6545
305940.1603
307990.2961
260061.5981
83608.27437
195775.4492
203271.3457
274554.4348
66197.3065
146547.3885145161.6139
107443.9545
40952.01298
112857.1622
107251.2941
100234.4621
35308.06499
15761.42437
17791.2811
2105.317864
9296.293129
8597.508422
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FX (N) FY (N) FZ (N) MX (N-M)
0 0.41933 0 -68.8
0 0.41933 0 -68.8
-1.3369 0.41933 -191.55 -198.22
-1.3369 0 0 0
-1.3369 0 0 0-4.593 -1.389867 0 -196.367
-4.593 -1.389867 0 -196.367
-4.593 -1.389867 0 -196.367
5.93 0 0 0
5.93 0 0 0
5.93 0.9705333 -75.138 -177.6587
0 0.9705333 0 -109.7867
0 0.9705333 0 -109.7867
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Applied Tip Nodal Loads with Mass (-1.5G)
MY (N-m) MZ (N-m) Node FX (N) FY (N) FZ (N)
0 0.94124 9198 0 0.41933 0
0 0.94124 9197 0 0.41933 0
-512.7133 0.94124 6031 -1.3369 0.41933 76.618
-214.5033 0.94124 6099 -1.3369 0 0
-214.5033 0.94124 6100 -1.3369 0 0-612.733 5.60933 6101 -4.593 -1.38987 0
-612.733 5.60633 6102 -4.593 -1.38987 0
-612.733 5.60633 6103 -4.593 -1.38987 0
-389.433 -1.90056 6104 5.93 0 0
-389.433 -1.90056 6105 5.93 0 0
-556.413 -1.90056 6032 5.93 0.970533 30.055
0 -1.97053 7197 0 0.970533 0
0 -1.90056 7198 0 0.970533 0
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MX (N-M) MY (N-m) MZ (N-m)
-68.8 0 0.94124
-68.8 0 0.94124
-17.031 -95.2233 0.94124
0 -214.503 0.94124
0 -214.503 0.94124-196.367 -612.733 5.60933
-196.367 -612.733 5.60633
-196.367 -612.733 5.60633
0 -389.433 -1.90056
0 -389.433 -1.90056
-82.6377 -322.641 -1.90056
-109.787 0 -1.97053
-109.787 0 -1.90056
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Wing Model Point Mass Loads 36.8325 m/s2
LE Mass Loads 3.75 G Applied Loads
Rib Mass (kg) Node 3.75 G Force (N) FZ (N) MX (N-m) MY (N-m)
5 13.79437 1155 -508.0811533 -295.92 296.29 -204.83
1156 -212.16 251.09 -171.08
6 14.51386 1153 -534.581679 -309.52 308.08 -213.11
1154 -225.06 263.22 -179.387 26.93789 1152 -992.1896947 -586.58 571.92 -388.45
1151 -405.61 473.59 -321.66
8 26.65452 3362 -981.7525438 -598.39 566.5 -384.76
3365 -383.36 451.77 -306.84
9 26.37115 3358 -971.3153929 -591.25 553.8 -376.14
3361 -380.07 442.91 -300.82
10 26.08778 3354 -960.8782421 -584.08 541.12 -367.53
3357 -376.8 434.02 -294.78
11 25.80441 3350 -950.4410912 -576.9 528.48 -358.94
3353 -373.54 425.09 -288.72
12 25.52105 3346 -940.0039403 -569.7 515.87 -350.38
3349 -370.31 416.14 -282.64
13 25.19739 3342 -928.0828344 -561.3 500.43 -339.89
3345 -366.79 405.19 -275.2
14 24.87373 3338 -916.1617284 -552.86 485.05 -329.44
3341 -363.3 394.21 -267.75
15 24.64341 3334 -907.6784518 -546.84 474.15 -322.04
3337 -360.84 386.38 -262.43
16 24.41376 3330 -899.2199077 -540.81 463.32 -314.68
3333 -358.41 378.57 -257.12
17 24.18344 3326 -890.736631 -534.74 452.5 -307.343329 -356 370.74 -251.81
18 23.95312 3322 -882.2533544 -528.65 441.74 -300.03
3325 -353.6 362.92 -246.49
19 23.72347 3318 -873.7948103 -522.56 431.07 -292.78
3321 -351.24 355.13 -241.2
20 23.49315 3314 -865.3115337 -516.42 420.43 -285.55
3317 -348.89 347.34 -235.91
21 23.2635 3310 -856.8529896 -510.27 409.88 -278.39
3313 -346.58 339.6 -230.66
22 23.03318 3306 -848.369713 -504.37 399.61 -271.41
3309 -344.48 332.06 -225.53
23 22.80286 3302 -839.8864363 -497.86 388.96 -264.18
3305 -342.03 324.18 -220.18
24 22.57321 3298 -831.4278922 -491.62 378.65 -257.18
3301 -339.81 316.56 -215.01
25 22.34289 3294 -822.9446156 -485.33 368.4 -250.21
3297 -337.62 308.97 -209.85
26 22.11324 6085 -814.4860715 -479.01 358.26 -243.33
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6088 -335.48 301.46 -204.75
27 21.88292 6081 -806.0027949 -472.63 348.2 -236.49
6084 -333.37 294 -199.68
28 21.6526 6077 -797.5195182 -466.19 338.23 -229.73
6080 -331.32 286.61 -194.67
29 21.42295 6073 -789.0609742 -459.72 328.4 -223.05
6076 -329.34 279.33 -189.7230 21.19263 6069 -780.5776975 -453.16 318.64 -216.42
6072 -327.41 272.12 -184.82
31 20.96299 6065 -772.1191534 -446.55 308.81 -210.21
6068 -325.57 264.84 -180.28
32 20.73266 6061 -763.6358768 -439.84 299.5 -203.42
6064 -323.8 258.02 -175.24
33 20.62254 6057 -759.5797329 -436.59 294.98 -200.35
6060 -322.99 254.71 -173
34 20.51175 6053 -755.4988563 -433.3 290.47 -197.28
6056 -322.19 251.41 -170.75
35 20.26598 6049 -746.4467302 -425.92 280.55 -190.55
6052 -320.53 244.18 -165.85
36 20.01954 6045 -737.3698715 -418.37 270.74 -183.89
6048 -319 237.1 -161.03
37 19.77378 6041 -728.3177454 -410.69 261.1 -177.34
6044 -317.63 230.19 -156.34
38 19.52802 6037 -719.2656193 -402.81 251.6 -170.88
6040 -316.45 223.46 -151.77
39 19.28158 6033 -710.1887606 -394.71 242.22 -164.51
6036 -315.48 216.9 -147.32
40 16.42816 6031 -605.0903109 -333.47 201.09 -136.586030 6030 -271.62 181.71 -123.41
TE Flaps/Spoilers/Ailerons Mass Loads 3.75 G Applied Loads
Rib Mass (kg) Node 3.75 G Force (N) FZ (N) MX (N-m) MY (N-m)
9 3359 -966.26 -1513.6 1001.8
3360 -743.25 -1357.7 897.72
35.43895 -1305.305202
10.97411 -404.203773
10 3355 -959.59 -1456.5 964.69
3356 -731.55 -1303.8 862.64
35.05815 -1291.279204
10.85619 -399.8604508
11 3351 -953.02 -1400.1 927.58
3352 -719.75 -1250.5 827.61
34.67734 -1277.253207
10.73826 -395.5171285
12 3347 -946.51 -1344.3 891.26
3348 -707.89 -1197.9 793.41
34.29654 -1263.227209
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10.62034 -391.1738063
13 3343 -939.81 -1274.9 845.7
3344 -693.61 -1132.5 750.44
33.86159 -1247.206994
10.48566 -386.2129501
14 3339 -1096.7 -1443.9 957.54
3340 -802.68 -1283.1 849.9238.64652 -1423.447993
12.92196 -475.9479156
15 3335 -436.58 -467.84 311.82
3336 -300.62 -399.49 266
17.46766 -643.3776235
2.547179 -93.81897785
16 3331 -434.63 -448.18 298.88
3332 -295.7 -381.43 254.1
17.30488 -637.3820664
2.523442 -92.94469031
17 3327 -1080.4 -1272.5 845.43
3328 -766.28 -1122.8 744.95
37.57401 -1383.944811
12.56335 -462.7395249
18 3323 -915.01 -1015.9 675.51
3324 -637.75 -890.66 591.39
32.18948 -1185.618905
9.967866 -367.1414426
19 3319 -910.51 -969.55 644.94
3320 -627.36 -847.85 563.15
31.88086 -1174.2518659.8723 -363.621499
20 3315 -905.97 -923.51 614.47
3316 -616.97 -805.57 535.15
31.57135 -1162.851587
9.776455 -360.0912632
21 3311 -901.38 -877.99 584.53
3312 -606.67 -764 507.79
31.26273 -1151.484546
9.680888 -356.5713195
22 3307 -896.69 -832.77 554.81
3308 -596.43 -722.97 480.8
30.95321 -1140.084269
9.585043 -353.0410837
23 3303 -891.87 -787.94 525.51
3304 -586.33 -682.59 454.36
30.6437 -1128.683991
9.489197 -349.5108478
24 3299 -886.89 -743.78 496.5
3300 -576.41 -643.08 428.41
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30.33508 -1117.316951
9.393631 -345.9909042
25 3295 -881.68 -699.96 467.66
3296 -566.7 -604.18 402.78
30.02557 -1105.916673
9.297785 -342.4606683
26 6086 -876.22 -656.72 439.36087 -557.27 -566.12 377.8
29.71695 -1094.549632
9.202219 -338.9407247
27 6082 -870.43 -613.87 411.2
6083 -548.13 -528.7 353.25
29.40744 -1083.149355
9.106373 -335.4104888
28 6078 -864.28 -571.6 383.35
6079 -539.35 -492.09 329.1
29.09792 -1071.749077
9.010527 -331.880253
29 6074 -857.76 -529.96 356.18
6075 -530.98 -456.3 305.78
28.7893 -1060.382036
8.914961 -328.3603094
30 6070 -850.82 -488.79 329.36
6071 -523 -421.19 282.88
28.47979 -1048.981759
8.819116 -324.8300735
31 6066 -843.48 -448.44 303.05
6067 -515.44 -387 260.628.17117 -1037.614718
8.723549 -321.3101299
32 6062 -983.41 -492.76 333.84
6063 -603.06 -428.1 288.91
32.2724 -1188.673186
10.80016 -397.7968882
33 6058 -332.29 -133.21 91.485
6059 -191.98 -111.88 76.528
12.07416 -444.7214972
2.159963 -79.55684285
34 6054 -330.63 -126.46 87.106
6055 -190.73 -106.45 73.01
12.00749 -442.2657619
2.14747 -79.09669151
35 6050 -326.84 -111.79 77.749
6051 -188.07 -94.678 65.531
11.85977 -436.8251001
2.119846 -78.07924578
36 6046 -322.92 -97.614 68.845
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6047 -185.51 -83.366 58.472
11.71167 -431.370027
2.092153 -77.05924366
37 6042 -318.95 -84.147 60.742
6043 -183.02 -72.694 52.144
11.56395 -425.9293653
2.06453 -76.0417979238 6038 -315.43 -77.542 44.632
6039 -180.81 -68.12 39.459
11.42963 -420.9817782
2.0435 -75.26720984
39 6034 -264.1 -186.91 122.78
11.26814 6035 -489.0379805 -224.94 -172.45 113.28
2.009213
40 6032 -224.62 -137.73 90.518
9.779729 6029 -408.876713 -184.26 -124.79 82.014
1.321248
Total Tip Mass Loads 3.75 G Applied Loads -1.5 G Applied Loads
Nodes FZ (N) MX (N-m) MY (N-m) FZ (N) MX (N-m) MY (N-m)
6030 -459.4 53.53 -418.31 183.762 -21.412 167.326
6031 -525.02 71.67 -434.79 210.008 -28.665 173.91
6029 -258.919 -192.373 -84.276 103.567 76.949 33.71
6032 -299.758 -205.602 -76.462 119.903 82.241 30.585
Total LG Mass Loads 3.75 G Applied Loads -1.5 G Appli
Nodes FY (N) FZ (N) MX (N-m) MY (N-m) MZ (N-m) FY (N)
431 49.121 -20038 -32464 -8223.8 17706 -19.649430 -256.16 -17314 -29651 -6628.2 -17247 102.46
3347 54.109 -281046.51 -20571.3 276911.26 1472.8 -21.645
3348 152.93 -195887.89 -16665.9 223343.41 -952.36 -61.169
Total Engine Mass Loa 3.75 G Applied Loads
Nodes FX (N) FY (N) FZ (N) MX (N-M) MY (N-M) MZ (N-M)
3339 787.29 9610.6 33603.3 -25875.9 3418.04 -127.56
3982 -3006.2 -30815 -1115.1 64713 -6520.3 -662.3
3346 2218.9 21205 -231099.7 245185.87 -25011.4 -8.1335
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-14.733 m/s2
-1.5 G Applied Loads
-1.5 G Force (N) FZ (N) MX (N-m) MY (N-m)
203.2324613 118.37 -118.52 81.934
84.866 -100.43 68.434
213.8326716 123.81 -123.23 85.242
90.026 -105.29 71.753396.8758779 234.63 -228.77 155.38
162.24 -189.43 128.66
392.7010175 239.36 -226.6 153.9
153.34 -180.71 122.74
388.5261572 236.5 -221.52 150.45
152.03 -177.17 120.33
384.3512968 233.63 -216.45 147.01
150.72 -173.61 117.91
380.1764365 230.76 -211.39 143.58
149.42 -170.04 115.49
376.0015761 227.88 -206.35 140.15
148.12 -166.46 113.06
371.2331337 224.52 -200.17 135.96
146.71 -162.08 110.08
366.4646914 221.14 -194.02 131.78
145.32 -157.68 107.1
363.0713807 218.73 -189.66 128.81
144.34 -154.55 104.97
359.6879631 216.32 -185.33 125.87
143.37 -151.43 102.85
356.2946524 213.9 -181 122.93142.4 -148.3 100.72
352.9013418 211.46 -176.7 120.01
141.44 -145.17 98.597
349.5179241 209.02 -172.43 117.11
140.5 -142.05 96.481
346.1246135 206.57 -168.17 114.22
139.56 -138.94 94.365
342.7411958 204.11 -163.95 111.36
138.63 -135.84 92.262
339.3478852 201.63 -159.75 108.5
137.71 -132.75 90.162
335.9545745 199.14 -155.58 105.67
136.81 -129.67 88.073
332.5711569 196.65 -151.46 102.87
135.92 -126.62 86.002
329.1778462 194.13 -147.36 100.09
135.05 -123.59 83.94
325.7944286 191.6 -143.31 97.332
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134.19 -120.58 81.9
322.401118 189.05 -139.28 94.598
133.35 -117.6 79.873
319.0078073 186.48 -135.29 91.89
132.53 -114.65 77.867
315.6243897 183.89 -131.36 89.219
131.74 -111.73 75.888312.231079 181.27 -127.46 86.569
130.97 -108.85 73.929
308.8476614 178.62 -123.52 84.086
130.23 -105.93 72.113
305.4543507 175.93 -119.8 81.367
129.52 -103.21 70.098
303.8318931 174.64 -117.99 80.14
129.2 -101.88 69.199
302.1995425 173.32 -116.19 78.913
128.88 -100.56 68.301
298.5786921 170.37 -112.22 76.219
128.21 -97.674 66.34
294.9479486 167.35 -108.3 73.554
127.6 -94.838 64.414
291.3270982 164.27 -104.44 70.935
127.05 -92.076 62.538
287.7062477 161.13 -100.64 68.354
126.58 -89.384 60.709
284.0755043 157.89 -96.886 65.805
126.19 -86.759 58.926
242.0361244 133.39 -80.434 54.63108.65 -72.683 49.366
-1.5 G Applied Loads
-1.5 G Force (N) FZ (N) MX (N-m) MY (N-m)
386.5 605.45 -400.7
297.3 543.09 -359.09
522.1220808
161.6815092
383.84 582.6 -385.87
292.62 521.5 -345.06
516.5116818
159.9441803
381.21 560.04 -371.03
287.9 500.21 -331.05
510.9012828
158.2068514
378.6 537.72 -356.5
283.16 479.17 -317.36
505.2908837
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156.4695225
375.92 509.96 -338.28
277.45 453.01 -300.17
498.8827977
154.48518
438.69 577.57 -383.02
321.07 513.25 -339.97569.3791971
190.3791662
174.63 187.14 -124.73
120.25 159.8 -106.4
257.3510494
37.52759114
173.85 179.27 -119.55
118.28 152.57 -101.64
254.9528265
37.17787613
432.16 508.99 -338.17
306.51 449.1 -297.98
553.5779242
185.09581
366.01 406.38 -270.21
255.1 356.27 -236.56
474.2475622
146.8565771
364.2 387.82 -257.98
250.95 339.14 -225.26
469.7007459145.4485996
362.39 369.4 -245.79
246.79 322.23 -214.06
465.1406348
144.0365053
360.55 351.19 -233.81
242.67 305.6 -203.12
460.5938186
142.6285278
358.68 333.11 -221.92
238.57 289.19 -192.32
456.0337075
141.2164335
356.75 315.18 -210.21
234.53 273.04 -181.74
451.4735965
139.8043391
354.76 297.51 -198.6
230.57 257.23 -171.36
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446.9267802
138.3963617
352.67 279.98 -187.06
226.68 241.67 -161.11
442.3666692
136.9842673
350.49 262.69 -175.72222.91 226.45 -151.12
437.8198529
135.5762899
348.17 245.55 -164.48
219.25 211.48 -141.3
433.2597418
134.1641955
345.71 228.64 -153.34
215.74 196.83 -131.64
428.6996308
132.7521012
343.1 211.98 -142.47
212.39 182.52 -122.31
424.1528145
131.3441237
340.33 195.52 -131.74
209.2 168.48 -113.15
419.5927035
129.9320294
337.39 179.38 -121.22
206.18 154.8 -104.24415.0458872
128.524052
393.37 197.1 -133.54
241.22 171.24 -115.56
475.4692745
159.1187553
132.92 53.283 -36.594
76.793 44.75 -30.611
177.8885989
31.82273714
132.25 50.586 -34.842
76.292 42.578 -29.204
176.9063047
31.63867661
130.74 44.717 -31.1
75.227 37.871 -26.213
174.7300401
31.23169831
129.17 39.046 -27.538
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74.203 33.346 -23.389
172.5480108
30.82369746
127.58 33.659 -24.297
73.206 29.077 -20.857
170.3717461
30.41671917126.18 31.017 -17.853
72.322 27.248 -15.784
168.3927113
30.10688394
105.64 74.763 -49.113
195.6151922 89.977 68.979 -45.314
89.848 55.092 -36.207
163.5506852 73.703 49.916 -32.806
ed Loads
FZ (N) MX (N-m) MY (N-m) MZ (N-m)
8015.3 12986 3289.5 -70826925.6 11861 2651.3 6898.8
112418.6 8228.62 -110767 -589.14
78354.16 6666.47 -89338.4 380.94
-1.5 G Applied Loads
FX (N) FY (N) FZ (N) MX (N-m) MY (N-m) MZ (N-m)
-314.92 -3844.2 -13441.3 10350.27 -1367.21 51.026
1202.5 12326 446.04 -25885 2608.1 264.92
-887.57 -8481.8 92439.88 -98073.4 10004.45 3.2534
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Volume ID Volume (m^3) Fuel Load (N) Fuel Mass (kg) Cell Lower Area (m^2)
1 4.479 35317.37007 3595.7412 3.881
2 4.674 36854.96488 3752.2872 3.881
3 4.441 35017.73621 3565.2348 3.881
4 0.7162 5647.309766 574.96536 0.6002
5 2.18 17189.52149 1750.104 1.799
6 3.446 27172.06011 2766.4488 2.9979176627 2.987 23552.79848 2397.9636 2.829076
8 2.645 20856.09373 2123.406 2.612
9 2.517 19846.80073 2020.6476 2.55
10 2.392 13202.81412 1920.2976 2.488
11 2.27 12529.42644 1822.356 2.426
12 2.777 15327.849 2229.3756 3.065
13 2.582 20359.33233 2072.8296 2.96
14 1.723 13586.03006 1383.2244 2.043
15 1.626 12821.1752 1305.3528 1.984
16 1.541 12150.94157 1237.1148 1.937
17 1.454 11464.93773 1167.2712 1.883
18 1.366 10771.04879 1096.6248 1.825
19 1.288 10156.01086 1034.0064 1.777
20 1.205 9501.547428 967.374 1.719
21 1.131 8918.04991 907.9668 1.671
22 1.057 8334.552391 848.5596 1.618
23 0.9818 7741.592751 788.18904 1.56
24 0.9152 7216.444984 734.72256 1.512
25 0.8459 6670.007443 679.08852 1.454
26 0.784 6181.919654 629.3952 1.406
27 0.7222 5694.620376 579.78216 1.35228 0.6609 5211.263647 530.57052 1.296
29 0.6061 4779.16008 486.57708 1.246
30 0.5503 4339.17141 441.78084 1.19
31 0.5002 3944.12782 401.56056 1.14
32 0.2216 1747.338515 177.90048 0.5263
33 0.2119 1670.853029 170.11332 0.5173
34 0.4318 3404.786871 346.64904 1.104
35 0.3825 3016.051362 307.071 1.046
36 0.3342 2635.200955 268.29576 0.9823
37 0.2902 2288.256484 232.97256 0.9218
38 0.2498 1969.69838 200.53944 0.8636
39 0.2112 1665.333458 169.55136 0.8006
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Fuel Load 3.75 G (N) Fuel Load -1.5 G (N) Total Pressure 3.75 G (N/m^2)
132440.1377 -52976.0551 34125.26095
138206.1183 -55282.44732 35610.9555
131316.5108 -52526.60431 33835.74099
21177.41162 -8470.964649 35283.92473
64460.70558 -25784.28223 35831.40944
101895.2254 -40758.09017 33988.6671188322.9943 -35329.19772 31219.73192
78210.3515 -31284.1406 29942.70731
74425.50273 -29770.20109 29186.47166
70729.36135 -28291.74454 28428.1999
67121.92737 -26848.77095 27667.73593
82113.47679 -32845.39071 26790.69389
76347.49624 -30538.9985 25793.07305
50947.61271 -20379.04509 24937.64695
48079.40701 -19231.7628 24233.57208
45566.03087 -18226.41235 23524.02213
42993.51647 -17197.40659 22832.45697
40391.43295 -16156.57318 22132.29203
38085.04073 -15234.01629 21432.212
35630.80286 -14252.32114 20727.63401
33442.68716 -13377.07486 20013.577
31254.57147 -12501.82859 19316.79324
29030.97282 -11612.38913 18609.59796
27061.66869 -10824.66748 17897.92903
25012.52791 -10005.01117 17202.5639
23182.1987 -9272.879482 16488.05029
21354.82641 -8541.930563 15794.9899519542.23868 -7816.895471 15078.88787
17921.8503 -7168.74012 14383.50746
16271.89279 -6508.757116 13673.85949
14790.47933 -5916.19173 12974.10467
6552.51943 -2621.007772 12450.16042
6265.698859 -2506.279544 12112.31173
12767.95077 -5107.180306 11565.1728
11310.19261 -4524.077043 10812.80364
9882.00358 -3952.801432 10060.06676
8580.961816 -3432.384726 9308.919306
7386.368924 -2954.54757 8552.997827
6245.000467 -2498.000187 7800.400284
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Total Pressure -1.5 G (N/m^2) Height (m) KP* Z Coord. (m)
-13650.10438 0.9146 16 0.3780203
-14244.3822 0.9146 3 0.3780203
-13534.29639 0.9146 7 0.3780203
-14113.56989 1.12 147 0.4715195
-14332.56378 1.147 155 0.4878046
-13595.46684 1.145 152 0.5056829-12487.89277 0.9146 148 0.3780203
-11977.08292 0.8015 143 0.2787386
-11674.58866 0.7814 139 0.2717297
-11371.27996 0.7612 135 0.2647207
-11067.09437 0.7411 131 0.2577118
-10716.27756 0.7209 127 0.2507028
-10317.22922 0.6947 123 0.2415804
-9975.058779 0.6684 119 0.232458
-9693.428832 0.6498 115 0.2259664
-9409.608853 0.6312 111 0.2194936
-9132.982788 0.6125 107 0.213002
-8852.91681 0.5938 103 0.2065103
-8572.884801 0.5752 99 0.2000376
-8291.053602 0.5566 95 0.1935459
-8005.430799 0.5379 91 0.1870732
-7726.717297 0.5193 87 0.1805815
-7443.839184 0.5006 83 0.1740899
-7159.171611 0.482 79 0.1676171
-6881.025561 0.4633 75 0.1611255
-6595.220115 0.4447 71 0.1546527
-6317.995979 0.426 67 0.1481611-6031.555148 0.4074 63 0.1416694
-5753.402985 0.3888 59 0.1351967
-5469.543795 0.3701 55 0.128705
-5189.641869 0.3515 51 0.12222323
-4980.064168 0.3328 47 0.1157406
-4844.924693 0.3239 43 0.1126368
-4626.069118 0.3149 39 0.1095139
-4325.121456 0.295 35 0.102587
-4024.026705 0.275 31 0.0956411
-3723.567722 0.2551 27 0.08871414
-3421.199131 0.2352 23 0.08178717
-3120.160114 0.2152 19 0.07484129
*Inboard TE line or smallest inboard line height
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Common Rib Net Pressure 3.75G (N/m^2) Common Rib Net Pressure -1.5G (N/m^2)
2724.065274 -1089.62611
905.8774897 -362.3509959
-1082.407462 432.9629848
1081.310527 -432.5242108
418.6433081 -167.4573232
-1406.626647 562.6506588-1688.312082 675.3248328
-682.3568155 272.9427262
-393.9483594 157.5793438
-384.7976411 153.9190564
-375.7198982 150.2879593
-421.506403 168.6025612
-462.031465 184.812586
-381.1778735 152.4711494
-305.0052326 122.002093
-298.5786177 119.4314471
-282.3891082 112.9556433
-277.1719627 110.8687851
-268.4573528 107.3829411
-261.4454088 104.5781635
-256.0608434 102.4243373
-241.2265355 96.49061419
-236.0146395 94.40585578
-228.6829496 91.47317984
-214.7751089 85.91004356
-211.8294695 84.7317878
-196.8291367 78.73165467-194.4933244 77.79732977
-180.2426011 72.09704045
-175.0938107 70.03752428
-163.9758782 65.5903513
-116.2457645 46.4983058
-72.95279362 29.18111745
-114.8627008 45.94508032
-147.9659338 59.18637353
-138.001761 55.2007044
-127.745144 51.0980576
-118.5284878 47.41139513
-107.9726609 43.18906437
Rib 4 common pressure
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Wing Model Emergency Landing Loads
Wing box mass and engine mass only
Position Link Mass (kg) -6G Force (N) 9G Force (N) 3G Force (N)
TE 1 101.7525 5996.47833 -8994.717495 -2998.239165 Node
Joint TE 2 203.505 11992.95666 -17989.43499 -5996.47833 3339
Mid 3
Joint LE 4 305.2575 17989.43499 -26984.15249 -8994.717495 3982LE 5
Engine CG 4736.51 279132.0073 -418698.011 -139566.0037 3346
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Emergency Reaction Loads Gravity Axis
FX (N) FY (N) FZ (N) MX (N-M) MY (N-M) MZ (N-M) 6G z
-16208.98 -16017.1 -25036.3 11378.3 -903.68 -5817.396 9G y
3G x
-372964 12766 30712.66 -92482 -289926.6 -74002.02
51150.72 -448637.2 309780 -16118 83936.2 21949.0136
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Value (N/m^2)
58.932
88.398
29.466
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