*ARCHIVED* development moved to aircraft-studio.

Change README.md to org

Better README capacity in org-mode

Commit
68aa008345d4041402020d8343b72fa155839e6f
Author
blendoit <blendoit@gmail.com>
Author date
Committer
blendoit <blendoit@gmail.com>
Committer date
Changed files
README.md
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1 Removed: # UCLA MAE 154B
2 Removed:
3 Removed: ## Spring 2019 Final Project
4 Removed:
5 Removed: This program enables the creation of NACA airfoils;\
6 Removed: the analysis of the airfoil's structural properties;\
7 Removed: the optimization via genetic algorithm of a population of airfoils;\
8 Removed: With the final objective of designing a lightweight FAR 23 compliant airfoil.
README.org
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@@ -0,0 +1,7 @@
1 Added: #+TITLE: UCLA MAE 154B
2 Added: #+SUBTITLE: Spring 2019 Final Project
3 Added:
4 Added: This program enables the creation of NACA airfoils;
5 Added: the analysis of the airfoil's structural properties;
6 Added: the optimization via genetic algorithm of a population of airfoils;
7 Added: With the final objective of designing a lightweight FAR 23 compliant airfoil.
TAGS
index 00000000..9381a948 000000..100644
@@ -0,0 +1,445 @@
1 Added:
2 Added: /home/blendux/github/UCLA_MAE_154B/example_airfoil.py,842
3 Added: start_time = time.time()start_time15,374
4 Added: NACA_NUM = 2412NACA_NUM18,426
5 Added: CHORD_LENGTH = 68CHORD_LENGTH19,442
6 Added: SEMI_SPAN = 150SEMI_SPAN20,460
7 Added: SPAR_THICKNESS = 0.4SPAR_THICKNESS23,491
8 Added: SKIN_THICKNESS = 0.1SKIN_THICKNESS24,512
9 Added: AIRFOIL_MASS = 10AIRFOIL_MASS27,559
10 Added: SPAR_MASS = 10SPAR_MASS28,577
11 Added: STRINGER_MASS = 5STRINGER_MASS29,592
12 Added: SPAR_CAP_AREA = 0.3SPAR_CAP_AREA32,625
13 Added: STRINGER_AREA = 0.1STRINGER_AREA33,645
14 Added: TOP_STRINGERS = 6TOP_STRINGERS36,688
15 Added: BOTTOM_STRINGERS = 4BOTTOM_STRINGERS37,706
16 Added: NOSE_TOP_STRINGERS = 3NOSE_TOP_STRINGERS38,727
17 Added: NOSE_BOTTOM_STRINGERS = 5NOSE_BOTTOM_STRINGERS39,750
18 Added: SAVE_PATH = '/home/blendux/github/UCLA_MAE_154B/save/'SAVE_PATH41,777
19 Added: af = creator.Airfoil.from_dimensions(CHORD_LENGTH, SEMI_SPAN)af45,860
20 Added: eval = evaluator.Evaluator(af)eval81,2026
21 Added: pop = generator.Population(10)pop89,2245
22 Added:
23 Added: /home/blendux/github/UCLA_MAE_154B/wing_scripts/my_progress.m,7747
24 Added: Vx = 1; Vz = 1; My = 1; %test loads will be applied individuallyVx5,40
25 Added: numStringers = numTopStringers;numStringers15,163
26 Added: stringerGap = upperStringerGap;stringerGap16,195
27 Added: webThickness = t_upper;webThickness17,227
28 Added: tempStringers = topStringers;tempStringers18,251
29 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx34,786
30 Added: tempInt = get_int(web(i).xStart/chord,web(i).xEnd/chord,1)*chord^2; %integral of airfoil futempInt40,1142
31 Added: triangle1 = abs( (web(i).xStart - sparCaps(1).posX)*web(i).zStart/2);triangle141,1245
32 Added: triangle2 = abs((web(i).xEnd - sparCaps(1).posX)*web(i).zEnd/2);triangle242,1319
33 Added: webTop = web;webTop56,2080
34 Added: web = [];web57,2094
35 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx67,2319
36 Added: webRearSpar = web;webRearSpar87,3367
37 Added: web = [];web88,3386
38 Added: numStringers = numBottomStringers;numStringers92,3410
39 Added: stringerGap = lowerStringerGap;stringerGap93,3445
40 Added: webThickness = t_lower;webThickness94,3477
41 Added: tempStringers = bottomStringers;tempStringers95,3501
42 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx103,3817
43 Added: tempInt = get_int(web(i).xEnd/chord,web(i).xStart/chord,0)*chord^2; %integral of airfoil futempInt118,4524
44 Added: triangle2 = abs((web(i).xStart - sparCaps(1).posX)*web(i).zStart/2);triangle2119,4627
45 Added: triangle1 = abs((web(i).xEnd - sparCaps(1).posX)*web(i).zEnd/2);triangle1120,4700
46 Added: webBottom = web;webBottom136,5535
47 Added: web = [];web137,5552
48 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx147,5779
49 Added: webFrontSpar = web;webFrontSpar165,6715
50 Added: web = [];web166,6735
51 Added: numStringers = numNoseBottomStringers;numStringers174,6781
52 Added: stringerGap = lowerNoseStringerGap;stringerGap175,6820
53 Added: webThickness = t_lower_front;webThickness176,6856
54 Added: tempStringers = noseBottomStringers;tempStringers177,6886
55 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx185,7206
56 Added: tempInt = get_int(web(i).xEnd/chord,web(i).xStart/chord,0)*chord^2; %integral of airfoil futempInt200,7761
57 Added: triangle1 = abs((web(i).xStart - sparCaps(2).posX)*web(i).zStart/2);triangle1201,7864
58 Added: triangle2 = abs((web(i).xEnd - sparCaps(2).posX)*web(i).zEnd/2);triangle2202,7937
59 Added: webLowerNose = web;webLowerNose218,8776
60 Added: web = [];web219,8796
61 Added: numStringers = numNoseTopStringers;numStringers222,8824
62 Added: stringerGap = upperNoseStringerGap;stringerGap223,8860
63 Added: webThickness = t_upper_front;webThickness224,8896
64 Added: tempStringers = noseTopStringers;tempStringers225,8926
65 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx233,9205
66 Added: tempInt = get_int(web(i).xStart/chord,web(i).xEnd/chord,1)*chord^2; %integral of airfoil futempInt247,9864
67 Added: triangle2 = abs((web(i).xStart - sparCaps(2).posX)*web(i).zStart/2);triangle2248,9967
68 Added: triangle1 = abs((web(i).xEnd - sparCaps(2).posX)*web(i).zEnd/2);triangle1249,10040
69 Added: webUpperNose = web;webUpperNose264,10802
70 Added: web = [];web265,10822
71 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx276,11050
72 Added: webFrontSparCell2 = web;webFrontSparCell2294,11994
73 Added: web = [];web295,12019
74 Added: Fx = sum([webTop.qp_dx_X])+webRearSpar.qp_dx_X+ sum([webBottom.qp_dx_X])+webFrontSpar.qp_dx_X; Fx300,12064
75 Added: Fx = Fx + sum([webLowerNose.qp_dx_X])+ sum([webUpperNose.qp_dx_X]); %cell 2Fx301,12168
76 Added: Fz = sum([webTop.qp_dz_X])+webRearSpar.qp_dz_X+ sum([webBottom.qp_dz_X])+webFrontSpar.qp_dz_X; Fz303,12248
77 Added: Fz = Fz + sum([webLowerNose.qp_dz_X])+ sum([webUpperNose.qp_dz_X]); %cell 2Fz304,12352
78 Added: Fx = sum([webTop.qp_dx_Z])+webRearSpar.qp_dx_Z+ sum([webBottom.qp_dx_Z])+webFrontSpar.qp_dx_Z; Fx310,12467
79 Added: Fx = Fx + sum([webLowerNose.qp_dx_Z])+ sum([webUpperNose.qp_dx_Z]); %cell 2Fx311,12571
80 Added: Fz = sum([webTop.qp_dz_Z])+webRearSpar.qp_dz_Z+ sum([webBottom.qp_dz_Z])+webFrontSpar.qp_dz_Z; Fz313,12651
81 Added: Fz = Fz + sum([webLowerNose.qp_dz_Z])+ sum([webUpperNose.qp_dz_Z]); %cell 2Fz314,12755
82 Added: A11 = sum([webTop.dS_over_t])+webRearSpar.dS_over_t+ sum([webBottom.dS_over_t])+webFrontSpar.dS_A11323,12925
83 Added: A22 = sum([webLowerNose.dS_over_t])+ sum([webUpperNose.dS_over_t])+webFrontSparCell2.dS_over_t;A22324,13029
84 Added: A12 = -webFrontSpar.dS_over_t;A12325,13125
85 Added: A21 = -webFrontSparCell2.dS_over_t;A21326,13156
86 Added: B1_X = sum([webTop.q_dS_over_t_X])+webRearSpar.q_dS_over_t_X+ sum([webBottom.q_dS_over_t_X])+webB1_X328,13193
87 Added: B2_X = sum([webLowerNose.q_dS_over_t_X])+ sum([webUpperNose.q_dS_over_t_X])+webFrontSparCell2.q_B2_X329,13314
88 Added: B1_Z = sum([webTop.q_dS_over_t_Z])+webRearSpar.q_dS_over_t_Z+ sum([webBottom.q_dS_over_t_Z])+webB1_Z330,13423
89 Added: B2_Z = sum([webLowerNose.q_dS_over_t_Z])+ sum([webUpperNose.q_dS_over_t_Z])+webFrontSparCell2.q_B2_Z331,13544
90 Added: Amat = [A11 A12; A21 A22];Amat333,13654
91 Added: Bmat_X = -[B1_X;B2_X];Bmat_X334,13681
92 Added: Bmat_Z = -[B1_Z;B2_Z];Bmat_Z335,13704
93 Added: qs_X = inv(Amat)*Bmat_X;qs_X337,13728
94 Added: qs_Z = inv(Amat)*Bmat_Z;qs_Z338,13753
95 Added: sum_2_a_q_X = sum([webTop.two_A_qprime_X])+webRearSpar.two_A_qprime_X+ sum([webBottom.two_A_qprisum_2_a_q_X342,13781
96 Added: sum_2_a_q_X = sum_2_a_q_X + sum([webLowerNose.two_A_qprime_X])+ sum([webUpperNose.two_A_qprime_Xsum_2_a_q_X343,13902
97 Added: sum_2_a_q_X = sum_2_a_q_X + 2*qs_X(1)*(sum([webTop.Area])+webRearSpar.Area+ sum([webBottom.Areasum_2_a_q_X344,14020
98 Added: sum_2_a_q_X = sum_2_a_q_X + 2*qs_X(2)*(sum([webLowerNose.Area])+ sum([webUpperNose.Area]));sum_2_a_q_X345,14121
99 Added: sum_2_a_q_Z = sum([webTop.two_A_qprime_Z])+webRearSpar.two_A_qprime_Z+ sum([webBottom.two_A_qprisum_2_a_q_Z347,14215
100 Added: sum_2_a_q_Z = sum_2_a_q_Z + sum([webLowerNose.two_A_qprime_Z])+ sum([webUpperNose.two_A_qprime_Zsum_2_a_q_Z348,14336
101 Added: sum_2_a_q_Z = sum_2_a_q_Z + 2*qs_Z(1)*(sum([webTop.Area])+webRearSpar.Area+ sum([webBottom.Areasum_2_a_q_Z349,14454
102 Added: sum_2_a_q_Z = sum_2_a_q_Z + 2*qs_Z(2)*(sum([webLowerNose.Area])+ sum([webUpperNose.Area]));sum_2_a_q_Z350,14555
103 Added: torque_Z = Vz*(sc.posX - 0.25*chord);torque_Z360,14875
104 Added: torque_X = -Vx*sc.posZ;torque_X361,14913
105 Added: Area1 = sum([webTop.Area]) + webRearSpar.Area + sum([webBottom.Area]);Area1364,14939
106 Added: Area1_check = get_int(frontSpar,backSpar,1)*chord^2 + get_int(frontSpar,backSpar,0)*chord^2;Area1_check366,15022
107 Added: Area2 = sum([webLowerNose.Area]) + sum([webUpperNose.Area]);Area2368,15116
108 Added: Area2_check = get_int(0,frontSpar,1)*chord^2 + get_int(0,frontSpar,0)*chord^2;Area2_check369,15177
109 Added: q1t_over_q2t = (A22/Area2 + webFrontSpar.dS_over_t/Area1)/(A11/Area1 + webFrontSpar.dS_over_t/Arq1t_over_q2t374,15312
110 Added: q2t = torque_X/(2*Area1*q1t_over_q2t + 2*Area2);q2t376,15415
111 Added: q1t = q2t*q1t_over_q2t;q1t377,15464
112 Added: qt_X = [q1t;q2t];qt_X378,15488
113 Added: q2t = torque_Z/(2*Area1*q1t_over_q2t + 2*Area2);q2t380,15507
114 Added: q1t = q2t*q1t_over_q2t;q1t381,15556
115 Added: qt_Z = [q1t;q2t];qt_Z382,15580
116 Added: xChord = 0:.01:1;xChord403,15777
117 Added: xChord = xChord*chord;xChord404,15795
118 Added: upperSurface = zeros(1,length(xChord));upperSurface405,15818
119 Added: lowerSurface = zeros(1,length(xChord));lowerSurface406,15858
120 Added: vecX = [frontSpar*chord webTop(i).xStart webTop(i).xEnd];vecX421,16255
121 Added: vecZ = [0 webTop(i).zStart webTop(i).zEnd];vecZ422,16316
122 Added: vecX = [frontSpar*chord webBottom(i).xStart webBottom(i).xEnd];vecX427,16429
123 Added: vecZ = [0 webBottom(i).zStart webBottom(i).zEnd];vecZ428,16496
124 Added: vecX = [frontSpar*chord webUpperNose(i).xStart webUpperNose(i).xEnd];vecX433,16618
125 Added: vecZ = [0 webUpperNose(i).zStart webUpperNose(i).zEnd];vecZ434,16691
126 Added: vecX = [frontSpar*chord webLowerNose(i).xStart webLowerNose(i).xEnd];vecX439,16819
127 Added: vecZ = [0 webLowerNose(i).zStart webLowerNose(i).zEnd];vecZ440,16892
128 Added: vecX = [frontSpar*chord sparCaps(3).posX sparCaps(4).posX];vecX444,16989
129 Added: vecZ = [0 sparCaps(3).posZ sparCaps(4).posZ];vecZ445,17052
130 Added: sparCapSize = 18;sparCapSize449,17136
131 Added: stringerSize = 18;stringerSize450,17154
132 Added:
133 Added: /home/blendux/github/UCLA_MAE_154B/wing_scripts/get_z.m,481
134 Added: function z = get_z(x,u)get_z1,0
135 Added: M = 0.02;M9,66
136 Added: P = 0.4;P10,76
137 Added: T = 0.12;T11,85
138 Added: a0 = 0.2969;a012,95
139 Added: a1 = -0.126;a113,108
140 Added: a2 = -0.3516;a214,121
141 Added: a3 = 0.2843;a315,135
142 Added: a4 = -0.1015;a416,148
143 Added: z_camber = M/P^2*(2*P*x - x^2);z_camber19,171
144 Added: z_camber = (M/(1-P)^2)*(1 - 2*P +2*P*x - x^2);z_camber21,212
145 Added: z_thickness = (T/0.2)*(a0*x^.5+a1*x+a2*x^2+a3*x^3+a4*x^4);z_thickness25,301
146 Added: z = z_camber + z_thickness;z28,369
147 Added: z = z_camber - z_thickness;z30,406
148 Added:
149 Added: /home/blendux/github/UCLA_MAE_154B/wing_scripts/get_dp.m,169
150 Added: function z = get_dp(xDist,zDist,Vx,Vz,Ix,Iz,Ixz,A)get_dp1,0
151 Added: denom = (Ix*Iz-Ixz^2);denom3,52
152 Added: z = -A*xDist*(Ix*Vx-Ixz*Vz)/denom - A*zDist*(Iz*Vz-Ixz*Vx)/denom;z4,75
153 Added:
154 Added: /home/blendux/github/UCLA_MAE_154B/wing_scripts/get_int.m,925
155 Added: function z = get_int(xi,xf,u)get_int1,0
156 Added: M = 0.02;M3,31
157 Added: P = 0.4;P4,41
158 Added: T = 0.12;T5,50
159 Added: a0 = 0.2969;a06,60
160 Added: a1 = -0.126;a17,73
161 Added: a2 = -0.3516;a28,86
162 Added: a3 = 0.2843;a39,100
163 Added: a4 = -0.1015;a410,113
164 Added: intCamb = M/P^2*(2*P*xf^2/2 - xf^3/3) - M/P^2*(2*P*xi^2/2 - xi^3/3); intCamb16,214
165 Added: intCamb = (M/(1-P)^2)*((1 - 2*P)*xf +2*P*xf^2/2 - xf^3/3) - (M/(1-P)^2)*((1 - 2*P)*P +2*P*P^intCamb18,303
166 Added: intCamb = intCamb + M/P^2*(2*P*P^2/2 - P^3/3) - M/P^2*(2*P*xi^2/2 - xi^3/3);intCamb19,413
167 Added: intCamb = (M/(1-P)^2)*((1 - 2*P)*xf +2*P*xf^2/2 - xf^3/3) - (M/(1-P)^2)*((1 - 2*P)*xi +2*P*xintCamb21,499
168 Added: intThickness = (T/0.2)*(a0*xf^1.5/1.5 + a1*xf^2/2 + a2*xf^3/3 + a3*xf^4/4 +a4*xf^5/5);intThickness27,710
169 Added: intThickness = intThickness - (T/0.2)*(a0*xi^1.5/1.5 + a1*xi^2/2 + a2*xi^3/3 + a3*xi^4/4 +a4*xi^intThickness28,797
170 Added: z = intCamb + intThickness; z32,964
171 Added: z = abs(intCamb - intThickness);z34,1001
172 Added:
173 Added: /home/blendux/github/UCLA_MAE_154B/wing_scripts/eye_beam_example.m,1004
174 Added: length = 20; % inlength4,44
175 Added: force = 10000; %lbsforce5,62
176 Added: max_width = 4; % inmax_width9,105
177 Added: min_width = 1; % inmin_width10,125
178 Added: y_max = 4; % iny_max11,145
179 Added: center_y = 2; % incenter_y12,161
180 Added: M = force*length;M17,218
181 Added: I = min_width*(2*center_y)^3/12 + 2*( max_width*(y_max-center_y)^3/12 + ...I19,237
182 Added: sigma_max = M * y_max / I;sigma_max22,370
183 Added: tempCoeff = force / (I * max_width);tempCoeff29,542
184 Added: int_y_da = ((y_max+center_y)/2) * max_width*(y_max-center_y);int_y_da30,579
185 Added: shear_1 = tempCoeff*int_y_da;shear_131,641
186 Added: tempCoeff = force / (I * min_width);tempCoeff34,749
187 Added: shear_2 = tempCoeff*int_y_da;shear_235,786
188 Added: tempCoeff = force / (I * min_width);tempCoeff39,857
189 Added: int_y_da = (center_y/2) * min_width*center_y;int_y_da40,894
190 Added: shear_3 = shear_2+tempCoeff*int_y_da;shear_341,940
191 Added: int_y_da_4 = force / (I * max_width)*4*(y_max^2/2 - (center_y:.1:y_max).^2/2);int_y_da_444,1027
192 Added: int_y_da_1 = shear_2 + force / (I * min_width)*1*(center_y^2/2 - (0:.1:center_y).^2/2);int_y_da_147,1155
193 Added:
194 Added: /home/blendux/github/UCLA_MAE_154B/wing_scripts/get_ds.m,378
195 Added: function ds = get_ds(xi,xf,u)get_ds1,0
196 Added: dist = 0;dist3,31
197 Added: numSteps = 10;numSteps4,41
198 Added: dx = (xf-xi)/numSteps;dx5,56
199 Added: z0 = get_z(xi,u);z06,79
200 Added: x0 = xi;x07,97
201 Added: tempX = x0+dx;tempX9,117
202 Added: tempZ = get_z(tempX,u);tempZ11,153
203 Added: tempZ = 0;tempZ13,195
204 Added: dist = dist + (dx^2+(tempZ-z0)^2)^.5;dist15,222
205 Added: z0 = tempZ;z016,264
206 Added: x0 = tempX;x017,280
207 Added:
208 Added: /home/blendux/github/UCLA_MAE_154B/wing_scripts/stringersBeamExample.m,837
209 Added: force = 8000; % lbsforce2,12
210 Added: stringer_A = 0.5; % in^2stringer_A3,32
211 Added: thickness = 0.04; % inthickness4,57
212 Added: top_stringers_y = 6; % intop_stringers_y6,81
213 Added: middle_stringers_y = 2; % inmiddle_stringers_y7,107
214 Added: I = 2*stringer_A*top_stringers_y^2 + 2*stringer_A*middle_stringers_y^2;I9,137
215 Added: shear_top_web = force / (I*thickness) * top_stringers_y * stringer_A;shear_top_web15,381
216 Added: shear_middle_web = shear_top_web + (force / (I*thickness) * middle_stringers_y * stringer_A);shear_middle_web16,451
217 Added: d_sigma = force * top_stringers_y / I; %(lbs/in^2)d_sigma36,1520
218 Added: d_force_top = d_sigma * stringer_A;d_force_top37,1572
219 Added: d_sigma = force * middle_stringers_y / I; %(lbs/in^2)d_sigma40,1631
220 Added: d_force_middle = d_force_top + d_sigma*stringer_A;d_force_middle41,1686
221 Added: check_load = 2*d_force_top*4 + d_force_middle*4;check_load44,1762
222 Added:
223 Added: /home/blendux/github/UCLA_MAE_154B/wing_scripts/wingAnalysis_190422.m,10240
224 Added: Vx = 1; Vz = 1; My = 1; %test loads will be applied individuallyVx8,43
225 Added: numTopStringers = 6;numTopStringers11,124
226 Added: numBottomStringers = 8;numBottomStringers12,145
227 Added: numNoseTopStringers = 4;numNoseTopStringers13,169
228 Added: numNoseBottomStringers = 4;numNoseBottomStringers14,194
229 Added: t_upper = 0.02/12;t_upper16,223
230 Added: t_lower = 0.02/12;t_lower17,242
231 Added: t_upper_front = 0.02/12;t_upper_front18,261
232 Added: t_lower_front = 0.02/12;t_lower_front19,286
233 Added: t_frontSpar = 0.04/12;t_frontSpar20,311
234 Added: t_rearSpar = 0.04/12;t_rearSpar21,334
235 Added: frontSpar = 0.2;frontSpar23,357
236 Added: backSpar = 0.7;backSpar24,374
237 Added: chord = 5;chord25,390
238 Added: upperStringerGap = (sparCaps(3).posX - sparCaps(1).posX)/(numTopStringers + 1);upperStringerGap42,817
239 Added: lowerStringerGap = (sparCaps(3).posX - sparCaps(1).posX)/(numBottomStringers + 1);lowerStringerGap43,897
240 Added: upperNoseStringerGap = (sparCaps(1).posX - 0)/(numNoseTopStringers + 1);upperNoseStringerGap44,980
241 Added: lowerNoseStringerGap = (sparCaps(1).posX - 0)/(numNoseBottomStringers + 1);lowerNoseStringerGap45,1053
242 Added: Ix = 0; Iz = 0; Ixz = 0;Ix98,3144
243 Added: Ix = Ix + sparCaps(i).area*(sparCaps(i).posZ-centroid.posZ)^2;Ix101,3191
244 Added: Iz = Iz + sparCaps(i).area*(sparCaps(i).posX-centroid.posX)^2;Iz102,3258
245 Added: Ixz = Ixz + sparCaps(i).area*(sparCaps(i).posX-centroid.posX)*(sparCaps(i).posZ-centroid.posIxz103,3325
246 Added: Ix = Ix + topStringers(i).area*(topStringers(i).posZ-centroid.posZ)^2;Ix108,3470
247 Added: Iz = Iz + topStringers(i).area*(topStringers(i).posX-centroid.posX)^2;Iz109,3545
248 Added: Ixz = Ixz + topStringers(i).area*(topStringers(i).posX-centroid.posX)*(topStringers(i).posZ-Ixz110,3620
249 Added: Ix = Ix + bottomStringers(i).area*(bottomStringers(i).posZ-centroid.posZ)^2;Ix113,3781
250 Added: Iz = Iz + bottomStringers(i).area*(bottomStringers(i).posX-centroid.posX)^2;Iz114,3862
251 Added: Ixz = Ixz + bottomStringers(i).area*(bottomStringers(i).posX-centroid.posX)*(bottomStringersIxz115,3943
252 Added: Ix = Ix + noseTopStringers(i).area*(noseTopStringers(i).posZ-centroid.posZ)^2;Ix118,4116
253 Added: Iz = Iz + noseTopStringers(i).area*(noseTopStringers(i).posX-centroid.posX)^2;Iz119,4199
254 Added: Ixz = Ixz + noseTopStringers(i).area*(noseTopStringers(i).posX-centroid.posX)*(noseTopStringIxz120,4282
255 Added: Ix = Ix + noseBottomStringers(i).area*(noseBottomStringers(i).posZ-centroid.posZ)^2;Ix123,4464
256 Added: Iz = Iz + noseBottomStringers(i).area*(noseBottomStringers(i).posX-centroid.posX)^2;Iz124,4553
257 Added: Ixz = Ixz + noseBottomStringers(i).area*(noseBottomStringers(i).posX-centroid.posX)*(noseBotIxz125,4642
258 Added: numStringers = numTopStringers;numStringers135,4835
259 Added: stringerGap = upperStringerGap;stringerGap136,4867
260 Added: webThickness = t_upper;webThickness137,4899
261 Added: tempStringers = topStringers;tempStringers138,4923
262 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx154,5458
263 Added: tempInt = get_int(web(i).xStart/chord,web(i).xEnd/chord,1)*chord^2; %integral of airfoil futempInt160,5814
264 Added: triangle1 = abs( (web(i).xStart - sparCaps(1).posX)*web(i).zStart/2);triangle1161,5917
265 Added: triangle2 = abs((web(i).xEnd - sparCaps(1).posX)*web(i).zEnd/2);triangle2162,5991
266 Added: webTop = web;webTop176,6752
267 Added: web = [];web177,6766
268 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx187,6991
269 Added: webRearSpar = web;webRearSpar207,8039
270 Added: web = [];web208,8058
271 Added: numStringers = numBottomStringers;numStringers212,8082
272 Added: stringerGap = lowerStringerGap;stringerGap213,8117
273 Added: webThickness = t_lower;webThickness214,8149
274 Added: tempStringers = bottomStringers;tempStringers215,8173
275 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx223,8489
276 Added: tempInt = get_int(web(i).xEnd/chord,web(i).xStart/chord,0)*chord^2; %integral of airfoil futempInt238,9196
277 Added: triangle2 = abs((web(i).xStart - sparCaps(1).posX)*web(i).zStart/2);triangle2239,9299
278 Added: triangle1 = abs((web(i).xEnd - sparCaps(1).posX)*web(i).zEnd/2);triangle1240,9372
279 Added: webBottom = web;webBottom256,10207
280 Added: web = [];web257,10224
281 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx267,10451
282 Added: webFrontSpar = web;webFrontSpar285,11387
283 Added: web = [];web286,11407
284 Added: numStringers = numNoseBottomStringers;numStringers294,11453
285 Added: stringerGap = lowerNoseStringerGap;stringerGap295,11492
286 Added: webThickness = t_lower_front;webThickness296,11528
287 Added: tempStringers = noseBottomStringers;tempStringers297,11558
288 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx305,11878
289 Added: tempInt = get_int(web(i).xEnd/chord,web(i).xStart/chord,0)*chord^2; %integral of airfoil futempInt320,12433
290 Added: triangle1 = abs((web(i).xStart - sparCaps(2).posX)*web(i).zStart/2);triangle1321,12536
291 Added: triangle2 = abs((web(i).xEnd - sparCaps(2).posX)*web(i).zEnd/2);triangle2322,12609
292 Added: webLowerNose = web;webLowerNose338,13448
293 Added: web = [];web339,13468
294 Added: numStringers = numNoseTopStringers;numStringers342,13496
295 Added: stringerGap = upperNoseStringerGap;stringerGap343,13532
296 Added: webThickness = t_upper_front;webThickness344,13568
297 Added: tempStringers = noseTopStringers;tempStringers345,13598
298 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx353,13877
299 Added: tempInt = get_int(web(i).xStart/chord,web(i).xEnd/chord,1)*chord^2; %integral of airfoil futempInt367,14536
300 Added: triangle2 = abs((web(i).xStart - sparCaps(2).posX)*web(i).zStart/2);triangle2368,14639
301 Added: triangle1 = abs((web(i).xEnd - sparCaps(2).posX)*web(i).zEnd/2);triangle1369,14712
302 Added: webUpperNose = web;webUpperNose384,15474
303 Added: web = [];web385,15494
304 Added: dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx396,15722
305 Added: webFrontSparCell2 = web;webFrontSparCell2414,16666
306 Added: web = [];web415,16691
307 Added: Fx = sum([webTop.qp_dx_X])+webRearSpar.qp_dx_X+ sum([webBottom.qp_dx_X])+webFrontSpar.qp_dx_X; Fx420,16736
308 Added: Fx = Fx + sum([webLowerNose.qp_dx_X])+ sum([webUpperNose.qp_dx_X]); %cell 2Fx421,16840
309 Added: Fz = sum([webTop.qp_dz_X])+webRearSpar.qp_dz_X+ sum([webBottom.qp_dz_X])+webFrontSpar.qp_dz_X; Fz423,16920
310 Added: Fz = Fz + sum([webLowerNose.qp_dz_X])+ sum([webUpperNose.qp_dz_X]); %cell 2Fz424,17024
311 Added: Fx = sum([webTop.qp_dx_Z])+webRearSpar.qp_dx_Z+ sum([webBottom.qp_dx_Z])+webFrontSpar.qp_dx_Z; Fx430,17139
312 Added: Fx = Fx + sum([webLowerNose.qp_dx_Z])+ sum([webUpperNose.qp_dx_Z]); %cell 2Fx431,17243
313 Added: Fz = sum([webTop.qp_dz_Z])+webRearSpar.qp_dz_Z+ sum([webBottom.qp_dz_Z])+webFrontSpar.qp_dz_Z; Fz433,17323
314 Added: Fz = Fz + sum([webLowerNose.qp_dz_Z])+ sum([webUpperNose.qp_dz_Z]); %cell 2Fz434,17427
315 Added: A11 = sum([webTop.dS_over_t])+webRearSpar.dS_over_t+ sum([webBottom.dS_over_t])+webFrontSpar.dS_A11443,17597
316 Added: A22 = sum([webLowerNose.dS_over_t])+ sum([webUpperNose.dS_over_t])+webFrontSparCell2.dS_over_t;A22444,17701
317 Added: A12 = -webFrontSpar.dS_over_t;A12445,17797
318 Added: A21 = -webFrontSparCell2.dS_over_t;A21446,17828
319 Added: B1_X = sum([webTop.q_dS_over_t_X])+webRearSpar.q_dS_over_t_X+ sum([webBottom.q_dS_over_t_X])+webB1_X448,17865
320 Added: B2_X = sum([webLowerNose.q_dS_over_t_X])+ sum([webUpperNose.q_dS_over_t_X])+webFrontSparCell2.q_B2_X449,17986
321 Added: B1_Z = sum([webTop.q_dS_over_t_Z])+webRearSpar.q_dS_over_t_Z+ sum([webBottom.q_dS_over_t_Z])+webB1_Z450,18095
322 Added: B2_Z = sum([webLowerNose.q_dS_over_t_Z])+ sum([webUpperNose.q_dS_over_t_Z])+webFrontSparCell2.q_B2_Z451,18216
323 Added: Amat = [A11 A12; A21 A22];Amat453,18326
324 Added: Bmat_X = -[B1_X;B2_X];Bmat_X454,18353
325 Added: Bmat_Z = -[B1_Z;B2_Z];Bmat_Z455,18376
326 Added: qs_X = inv(Amat)*Bmat_X;qs_X457,18400
327 Added: qs_Z = inv(Amat)*Bmat_Z;qs_Z458,18425
328 Added: sum_2_a_q_X = sum([webTop.two_A_qprime_X])+webRearSpar.two_A_qprime_X+ sum([webBottom.two_A_qprisum_2_a_q_X462,18453
329 Added: sum_2_a_q_X = sum_2_a_q_X + sum([webLowerNose.two_A_qprime_X])+ sum([webUpperNose.two_A_qprime_Xsum_2_a_q_X463,18574
330 Added: sum_2_a_q_X = sum_2_a_q_X + 2*qs_X(1)*(sum([webTop.Area])+webRearSpar.Area+ sum([webBottom.Areasum_2_a_q_X464,18692
331 Added: sum_2_a_q_X = sum_2_a_q_X + 2*qs_X(2)*(sum([webLowerNose.Area])+ sum([webUpperNose.Area]));sum_2_a_q_X465,18793
332 Added: sum_2_a_q_Z = sum([webTop.two_A_qprime_Z])+webRearSpar.two_A_qprime_Z+ sum([webBottom.two_A_qprisum_2_a_q_Z467,18887
333 Added: sum_2_a_q_Z = sum_2_a_q_Z + sum([webLowerNose.two_A_qprime_Z])+ sum([webUpperNose.two_A_qprime_Zsum_2_a_q_Z468,19008
334 Added: sum_2_a_q_Z = sum_2_a_q_Z + 2*qs_Z(1)*(sum([webTop.Area])+webRearSpar.Area+ sum([webBottom.Areasum_2_a_q_Z469,19126
335 Added: sum_2_a_q_Z = sum_2_a_q_Z + 2*qs_Z(2)*(sum([webLowerNose.Area])+ sum([webUpperNose.Area]));sum_2_a_q_Z470,19227
336 Added: torque_Z = Vz*(sc.posX - 0.25*chord);torque_Z480,19547
337 Added: torque_X = -Vx*sc.posZ;torque_X481,19585
338 Added: Area1 = sum([webTop.Area]) + webRearSpar.Area + sum([webBottom.Area]);Area1484,19611
339 Added: Area1_check = get_int(frontSpar,backSpar,1)*chord^2 + get_int(frontSpar,backSpar,0)*chord^2;Area1_check486,19694
340 Added: Area2 = sum([webLowerNose.Area]) + sum([webUpperNose.Area]);Area2488,19788
341 Added: Area2_check = get_int(0,frontSpar,1)*chord^2 + get_int(0,frontSpar,0)*chord^2;Area2_check489,19849
342 Added: q1t_over_q2t = (A22/Area2 + webFrontSpar.dS_over_t/Area1)/(A11/Area1 + webFrontSpar.dS_over_t/Arq1t_over_q2t494,19984
343 Added: q2t = torque_X/(2*Area1*q1t_over_q2t + 2*Area2);q2t496,20087
344 Added: q1t = q2t*q1t_over_q2t;q1t497,20136
345 Added: qt_X = [q1t;q2t];qt_X498,20160
346 Added: q2t = torque_Z/(2*Area1*q1t_over_q2t + 2*Area2);q2t500,20179
347 Added: q1t = q2t*q1t_over_q2t;q1t501,20228
348 Added: qt_Z = [q1t;q2t];qt_Z502,20252
349 Added: xChord = 0:.01:1;xChord523,20449
350 Added: xChord = xChord*chord;xChord524,20467
351 Added: upperSurface = zeros(1,length(xChord));upperSurface525,20490
352 Added: lowerSurface = zeros(1,length(xChord));lowerSurface526,20530
353 Added: vecX = [frontSpar*chord webTop(i).xStart webTop(i).xEnd];vecX541,20927
354 Added: vecZ = [0 webTop(i).zStart webTop(i).zEnd];vecZ542,20988
355 Added: vecX = [frontSpar*chord webBottom(i).xStart webBottom(i).xEnd];vecX547,21101
356 Added: vecZ = [0 webBottom(i).zStart webBottom(i).zEnd];vecZ548,21168
357 Added: vecX = [frontSpar*chord webUpperNose(i).xStart webUpperNose(i).xEnd];vecX553,21290
358 Added: vecZ = [0 webUpperNose(i).zStart webUpperNose(i).zEnd];vecZ554,21363
359 Added: vecX = [frontSpar*chord webLowerNose(i).xStart webLowerNose(i).xEnd];vecX559,21491
360 Added: vecZ = [0 webLowerNose(i).zStart webLowerNose(i).zEnd];vecZ560,21564
361 Added: vecX = [frontSpar*chord sparCaps(3).posX sparCaps(4).posX];vecX564,21661
362 Added: vecZ = [0 sparCaps(3).posZ sparCaps(4).posZ];vecZ565,21724
363 Added: sparCapSize = 18;sparCapSize569,21808
364 Added: stringerSize = 18;stringerSize570,21826
365 Added:
366 Added: /home/blendux/github/UCLA_MAE_154B/gui.py,393
367 Added: import tkinter as tktk20,820
368 Added: import tkinter.ttk as ttkttk21,841
369 Added: class MainWindow(tk.Frame):MainWindow27,963
370 Added: def __init__(self, *args, **kwargs):__init__30,1022
371 Added: def create_window(self):create_window64,2364
372 Added: def new_field(parent, name):new_field72,2661
373 Added: def set_naca(name):set_naca80,2826
374 Added: def set_chord(name):set_chord85,2894
375 Added: def set_semi_span(name):set_semi_span90,2957
376 Added:
377 Added: /home/blendux/github/UCLA_MAE_154B/README.md,94
378 Added: # UCLA MAE 154BUCLA MAE 154B1,0
379 Added: ## Spring 2019 Final ProjectSpring 2019 Final Project3,17
380 Added:
381 Added: /home/blendux/github/UCLA_MAE_154B/tools/evaluator.py,1051
382 Added: import numpy as npnp24,959
383 Added: import matplotlib.pyplot as pltplt26,1000
384 Added: class Evaluator:Evaluator29,1034
385 Added: def __init__(self, airfoil):__init__32,1130
386 Added: def __str__(self):__str__56,1932
387 Added: def info_print(self, round):info_print59,1991
388 Added: def info_save(self, save_path, number):info_save74,2570
389 Added: def get_lift_rectangular(self, lift):get_lift_rectangular92,3362
390 Added: def get_lift_elliptical(self, L_0):get_lift_elliptical96,3507
391 Added: def get_lift_total(self):get_lift_total103,3719
392 Added: def get_mass_distribution(self, total_mass):get_mass_distribution108,3900
393 Added: def get_drag(self, drag):get_drag112,4047
394 Added: def get_centroid(self):get_centroid124,4473
395 Added: def get_inertia_terms(self):get_inertia_terms147,5377
396 Added: def get_dx(self, component):get_dx180,6841
397 Added: def get_dz(self, component):get_dz183,6940
398 Added: def get_dP(self, xDist, zDist, V_x, V_z, area):get_dP186,7039
399 Added: def analysis(self, V_x, V_z):analysis199,7491
400 Added: def plot_geom(evaluator):plot_geom219,8423
401 Added: def plot_lift(evaluator):plot_lift272,10194
402 Added:
403 Added: /home/blendux/github/UCLA_MAE_154B/tools/creator.py,1569
404 Added: import numpy as npnp31,1142
405 Added: import bisect as bibi33,1193
406 Added: import matplotlib.pyplot as pltplt34,1213
407 Added: class Airfoil:Airfoil37,1247
408 Added: chord = 100chord51,1727
409 Added: semi_span = 200semi_span52,1743
410 Added: def __init__(self):__init__54,1764
411 Added: def from_dimensions(cls, chord, semi_span):from_dimensions65,2007
412 Added: def __str__(self):__str__75,2337
413 Added: def add_naca(self, naca_num):add_naca78,2396
414 Added: def get_camber(x):get_camber99,3112
415 Added: def get_thickness(x):get_thickness113,3714
416 Added: def get_theta(x):get_theta124,4162
417 Added: def get_upper_coord(x):get_upper_coord132,4452
418 Added: def get_lower_coord(x):get_lower_coord137,4637
419 Added: def add_mass(self, mass):add_mass165,5804
420 Added: def info_print(self, round):info_print168,5860
421 Added: def info_save(self, save_path, number):info_save183,6442
422 Added: class Spar(Airfoil):Spar200,7175
423 Added: def __init__(self):__init__203,7242
424 Added: def add_coord(self, airfoil, x_loc_percent):add_coord211,7427
425 Added: def add_spar_caps(self, spar_cap_area):add_spar_caps238,8357
426 Added: def add_mass(self, mass):add_mass242,8460
427 Added: def add_webs(self, thickness):add_webs246,8550
428 Added: class Stringer(Airfoil):Stringer257,8896
429 Added: def __init__(self):__init__260,8975
430 Added: def add_coord(self, airfoil,add_coord269,9188
431 Added: def add_area(self, area):add_area329,11686
432 Added: def add_mass(self, mass):add_mass333,11762
433 Added: def add_webs(self, thickness):add_webs337,11873
434 Added: def info_print(self, round):info_print347,12223
435 Added: def plot_geom(airfoil, view: False):plot_geom353,12375
436 Added: def main():main410,14137
437 Added:
438 Added: /home/blendux/github/UCLA_MAE_154B/tools/generator.py,332
439 Added: def default_airfoil():default_airfoil23,867
440 Added: class Population(creator.Airfoil):Population45,1474
441 Added: def __init__(self, size):__init__48,1551
442 Added: def mutate(self, prob_mt):mutate54,1720
443 Added: def crossover(self, prob_cx):crossover57,1824
444 Added: def reproduce(self, prob_rp):reproduce60,1923
445 Added: def fitness():fitness63,2034
example_airfoil.py
index 0fd0aba9..e0eb532c 100644..100644
@@ -10,26 +10,27 @@
10 10
11 11 from tools import creator, evaluator, generator
12 12
13 Added:
13 14 import time
14 15 start_time = time.time()
15 16
16 Removed: # Airfoil dimensions
17 Added: # Airfoil dimensions (in)
17 18 NACA_NUM = 2412
18 Removed: CHORD_LENGTH = 68 # inches
19 Removed: SEMI_SPAN = 150 # inches
19 Added: CHORD_LENGTH = 68
20 Added: SEMI_SPAN = 150
20 21
21 22 # Thicknesses
22 23 SPAR_THICKNESS = 0.4
23 24 SKIN_THICKNESS = 0.1
24 25
25 Removed: # Component masses
26 Removed: AIRFOIL_MASS = 10 # lbs
27 Removed: SPAR_MASS = 10 # lbs
28 Removed: STRINGER_MASS = 5 # lbs
26 Added: # Component masses (lbs)
27 Added: AIRFOIL_MASS = 10
28 Added: SPAR_MASS = 10
29 Added: STRINGER_MASS = 5
29 30
30 Removed: # Area
31 Removed: SPAR_CAP_AREA = 0.3 # sqin
32 Removed: STRINGER_AREA = 0.1 # sqin
31 Added: # Area (sqin)
32 Added: SPAR_CAP_AREA = 0.3
33 Added: STRINGER_AREA = 0.1
33 34
34 35 # Amount of stringers
35 36 TOP_STRINGERS = 6
@@ -37,7 +38,7 @@
37 38 NOSE_TOP_STRINGERS = 3
38 39 NOSE_BOTTOM_STRINGERS = 5
39 40
40 Removed: SAVE_PATH = 'C:/Users/blend/github/UCLA_MAE_154B/save'
41 Added: SAVE_PATH = '/home/blendux/github/UCLA_MAE_154B/save/'
41 42
42 43
43 44 # Create airfoil instance
@@ -87,9 +88,9 @@
87 88
88 89 pop = generator.Population(10)
89 90
90 Removed: print(help(creator))
91 Removed: print(help(evaluator))
92 Removed: print(help(generator))
91 Added: # print(help(creator))
92 Added: # print(help(evaluator))
93 Added: # print(help(generator))
93 94
94 95 # Print final execution time
95 96 print("--- %s seconds ---" % (time.time() - start_time))
tools/creator.py
index 01f73ade..6d074f81 100644..100644
@@ -37,7 +37,7 @@
37 37 class Airfoil:
38 38 """This class represents a single NACA airfoil.
39 39
40 Removed: Please note: the coordinates are saved as two lists
40 Added: The coordinates are saved as two lists
41 41 for the x- and z-coordinates. The coordinates start at
42 42 the leading edge, travel over the airfoil's upper edge,
43 43 then loop back to the leading edge via the lower edge.
@@ -69,7 +69,7 @@
69 69 else:
70 70 cls.chord = 20
71 71 print('Chord too small, using minimum value of 20.')
72 Removed: cls.semi_span = semi_span
72 Added: cls.semi_span = semi_span
73 73 return Airfoil()
74 74
75 75 def __str__(self):
@@ -175,7 +175,7 @@
175 175 for k, v in self.__dict__.items():
176 176 if type(v) != list:
177 177 print('{}:\n'.format(k), v)
178 Removed: print(num_of_dashes * '-')
178 Added: print(num_of_dashes * '-')
179 179 for k, v in self.__dict__.items():
180 180 if type(v) == list:
181 181 print('{}:\n'.format(k), np.around(v, round))
@@ -251,7 +251,7 @@
251 251 self.x_end.append(self.x[_][1])
252 252 self.z_start.append(self.z[_][0])
253 253 self.z_end.append(self.z[_][1])
254 Removed: self.thickness = thickness
254 Added: self.thickness = thickness
255 255 return None
256 256
257 257
@@ -296,8 +296,8 @@
296 296 self.x.append(airfoil.x[i])
297 297 self.z.append(airfoil.z[i])
298 298 x += interval
299 Removed: # Add upper stringers from first spar until last spar
300 Removed: # TODO: stringer placement if only one spar is created
299 Added: # Add upper stringers from first spar until last spar
300 Added: # TODO: stringer placement if only one spar is created
301 301 interval = (airfoil.spar.x[-1][0]
302 302 - airfoil.spar.x[0][0]) / (stringer_u_2 + 1)
303 303 x = interval + airfoil.spar.x[0][0]
@@ -316,7 +316,7 @@
316 316 self.x.append(airfoil.x[-i])
317 317 self.z.append(airfoil.z[-i])
318 318 x += interval
319 Removed: # Add lower stringers from first spar until last spar
319 Added: # Add lower stringers from first spar until last spar
320 320 interval = (airfoil.spar.x[-1][1]
321 321 - airfoil.spar.x[0][1]) / (stringer_l_2 + 1)
322 322 x = interval + airfoil.spar.x[0][1]
@@ -342,7 +342,7 @@
342 342 self.x_end.append(self.x[_ + 1])
343 343 self.z_start.append(self.z[_])
344 344 self.z_end.append(self.z[_ + 1])
345 Removed: self.thickness = thickness
345 Added: self.thickness = thickness
346 346 return None
347 347
348 348 def info_print(self, round):
@@ -379,7 +379,7 @@
379 379 ax.plot(x, y, '-', color='y', linewidth='4')
380 380 except AttributeError:
381 381 print('No spars to plot.')
382 Removed: # Plot stringers
382 Added: # Plot stringers
383 383 try:
384 384 for _ in range(0, len(airfoil.stringer.x)):
385 385 x = airfoil.stringer.x[_]