UW Wing Design

8/3/2019 UW Wing Design

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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


28/71

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


29/71

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


30/71


31/71

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


32/71

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


33/71

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


34/71

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


35/71

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


36/71

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


37/71

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


39/71

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

%

%

%

%

%

%


40/71

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


41/71

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


42/71

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


43/71

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


44/71

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


45/71

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


46/71

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


47/71

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


48/71

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


49/71

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


50/71

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


51/71


52/71

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


53/71


54/71

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


55/71

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


56/71

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


57/71

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


58/71

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


59/71

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


60/71

-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


61/71

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 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


62/71

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


63/71

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


64/71

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


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


65/71

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


66/71

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


67/71

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


68/71

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


69/71

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

UW Wing Design

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