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| -rw-r--r-- | README.md | 8 | ||||
| -rw-r--r-- | README.org | 7 | ||||
| -rw-r--r-- | TAGS | 445 | ||||
| -rw-r--r-- | example_airfoil.py | 29 | ||||
| -rw-r--r-- | tools/creator.py | 18 |
5 files changed, 476 insertions, 31 deletions
diff --git a/README.md b/README.md deleted file mode 100644 index 5427162..0000000 --- a/README.md +++ /dev/null @@ -1,8 +0,0 @@ -# UCLA MAE 154B - -## Spring 2019 Final Project - -This program enables the creation of NACA airfoils;\ -the analysis of the airfoil's structural properties;\ -the optimization via genetic algorithm of a population of airfoils;\ -With the final objective of designing a lightweight FAR 23 compliant airfoil. diff --git a/README.org b/README.org new file mode 100644 index 0000000..caa04a9 --- /dev/null +++ b/README.org @@ -0,0 +1,7 @@ +#+TITLE: UCLA MAE 154B +#+SUBTITLE: Spring 2019 Final Project + +This program enables the creation of NACA airfoils; +the analysis of the airfoil's structural properties; +the optimization via genetic algorithm of a population of airfoils; +With the final objective of designing a lightweight FAR 23 compliant airfoil. @@ -0,0 +1,445 @@ + +/home/blendux/github/UCLA_MAE_154B/example_airfoil.py,842 +start_time = time.time()start_time15,374 +NACA_NUM = 2412NACA_NUM18,426 +CHORD_LENGTH = 68CHORD_LENGTH19,442 +SEMI_SPAN = 150SEMI_SPAN20,460 +SPAR_THICKNESS = 0.4SPAR_THICKNESS23,491 +SKIN_THICKNESS = 0.1SKIN_THICKNESS24,512 +AIRFOIL_MASS = 10AIRFOIL_MASS27,559 +SPAR_MASS = 10SPAR_MASS28,577 +STRINGER_MASS = 5STRINGER_MASS29,592 +SPAR_CAP_AREA = 0.3SPAR_CAP_AREA32,625 +STRINGER_AREA = 0.1STRINGER_AREA33,645 +TOP_STRINGERS = 6TOP_STRINGERS36,688 +BOTTOM_STRINGERS = 4BOTTOM_STRINGERS37,706 +NOSE_TOP_STRINGERS = 3NOSE_TOP_STRINGERS38,727 +NOSE_BOTTOM_STRINGERS = 5NOSE_BOTTOM_STRINGERS39,750 +SAVE_PATH = '/home/blendux/github/UCLA_MAE_154B/save/'SAVE_PATH41,777 +af = creator.Airfoil.from_dimensions(CHORD_LENGTH, SEMI_SPAN)af45,860 +eval = evaluator.Evaluator(af)eval81,2026 +pop = generator.Population(10)pop89,2245 + +/home/blendux/github/UCLA_MAE_154B/wing_scripts/my_progress.m,7747 +Vx = 1; Vz = 1; My = 1; %test loads will be applied individuallyVx5,40 +numStringers = numTopStringers;numStringers15,163 +stringerGap = upperStringerGap;stringerGap16,195 +webThickness = t_upper;webThickness17,227 +tempStringers = topStringers;tempStringers18,251 + dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx34,786 + tempInt = get_int(web(i).xStart/chord,web(i).xEnd/chord,1)*chord^2; %integral of airfoil futempInt40,1142 + triangle1 = abs( (web(i).xStart - sparCaps(1).posX)*web(i).zStart/2);triangle141,1245 + triangle2 = abs((web(i).xEnd - sparCaps(1).posX)*web(i).zEnd/2);triangle242,1319 +webTop = web;webTop56,2080 +web = [];web57,2094 +dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx67,2319 +webRearSpar = web;webRearSpar87,3367 +web = [];web88,3386 +numStringers = numBottomStringers;numStringers92,3410 +stringerGap = lowerStringerGap;stringerGap93,3445 +webThickness = t_lower;webThickness94,3477 +tempStringers = bottomStringers;tempStringers95,3501 + dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx103,3817 + tempInt = get_int(web(i).xEnd/chord,web(i).xStart/chord,0)*chord^2; %integral of airfoil futempInt118,4524 + triangle2 = abs((web(i).xStart - sparCaps(1).posX)*web(i).zStart/2);triangle2119,4627 + triangle1 = abs((web(i).xEnd - sparCaps(1).posX)*web(i).zEnd/2);triangle1120,4700 +webBottom = web;webBottom136,5535 +web = [];web137,5552 +dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx147,5779 +webFrontSpar = web;webFrontSpar165,6715 +web = [];web166,6735 +numStringers = numNoseBottomStringers;numStringers174,6781 +stringerGap = lowerNoseStringerGap;stringerGap175,6820 +webThickness = t_lower_front;webThickness176,6856 +tempStringers = noseBottomStringers;tempStringers177,6886 + dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx185,7206 + tempInt = get_int(web(i).xEnd/chord,web(i).xStart/chord,0)*chord^2; %integral of airfoil futempInt200,7761 + triangle1 = abs((web(i).xStart - sparCaps(2).posX)*web(i).zStart/2);triangle1201,7864 + triangle2 = abs((web(i).xEnd - sparCaps(2).posX)*web(i).zEnd/2);triangle2202,7937 +webLowerNose = web;webLowerNose218,8776 +web = [];web219,8796 +numStringers = numNoseTopStringers;numStringers222,8824 +stringerGap = upperNoseStringerGap;stringerGap223,8860 +webThickness = t_upper_front;webThickness224,8896 +tempStringers = noseTopStringers;tempStringers225,8926 + dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx233,9205 + tempInt = get_int(web(i).xStart/chord,web(i).xEnd/chord,1)*chord^2; %integral of airfoil futempInt247,9864 + triangle2 = abs((web(i).xStart - sparCaps(2).posX)*web(i).zStart/2);triangle2248,9967 + triangle1 = abs((web(i).xEnd - sparCaps(2).posX)*web(i).zEnd/2);triangle1249,10040 +webUpperNose = web;webUpperNose264,10802 +web = [];web265,10822 +dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx276,11050 +webFrontSparCell2 = web;webFrontSparCell2294,11994 +web = [];web295,12019 +Fx = sum([webTop.qp_dx_X])+webRearSpar.qp_dx_X+ sum([webBottom.qp_dx_X])+webFrontSpar.qp_dx_X; Fx300,12064 +Fx = Fx + sum([webLowerNose.qp_dx_X])+ sum([webUpperNose.qp_dx_X]); %cell 2Fx301,12168 +Fz = sum([webTop.qp_dz_X])+webRearSpar.qp_dz_X+ sum([webBottom.qp_dz_X])+webFrontSpar.qp_dz_X; Fz303,12248 +Fz = Fz + sum([webLowerNose.qp_dz_X])+ sum([webUpperNose.qp_dz_X]); %cell 2Fz304,12352 +Fx = sum([webTop.qp_dx_Z])+webRearSpar.qp_dx_Z+ sum([webBottom.qp_dx_Z])+webFrontSpar.qp_dx_Z; Fx310,12467 +Fx = Fx + sum([webLowerNose.qp_dx_Z])+ sum([webUpperNose.qp_dx_Z]); %cell 2Fx311,12571 +Fz = sum([webTop.qp_dz_Z])+webRearSpar.qp_dz_Z+ sum([webBottom.qp_dz_Z])+webFrontSpar.qp_dz_Z; Fz313,12651 +Fz = Fz + sum([webLowerNose.qp_dz_Z])+ sum([webUpperNose.qp_dz_Z]); %cell 2Fz314,12755 +A11 = sum([webTop.dS_over_t])+webRearSpar.dS_over_t+ sum([webBottom.dS_over_t])+webFrontSpar.dS_A11323,12925 +A22 = sum([webLowerNose.dS_over_t])+ sum([webUpperNose.dS_over_t])+webFrontSparCell2.dS_over_t;A22324,13029 +A12 = -webFrontSpar.dS_over_t;A12325,13125 +A21 = -webFrontSparCell2.dS_over_t;A21326,13156 +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 +B2_X = sum([webLowerNose.q_dS_over_t_X])+ sum([webUpperNose.q_dS_over_t_X])+webFrontSparCell2.q_B2_X329,13314 +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 +B2_Z = sum([webLowerNose.q_dS_over_t_Z])+ sum([webUpperNose.q_dS_over_t_Z])+webFrontSparCell2.q_B2_Z331,13544 +Amat = [A11 A12; A21 A22];Amat333,13654 +Bmat_X = -[B1_X;B2_X];Bmat_X334,13681 +Bmat_Z = -[B1_Z;B2_Z];Bmat_Z335,13704 +qs_X = inv(Amat)*Bmat_X;qs_X337,13728 +qs_Z = inv(Amat)*Bmat_Z;qs_Z338,13753 +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 +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 +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 +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 +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 +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 +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 +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 +torque_Z = Vz*(sc.posX - 0.25*chord);torque_Z360,14875 +torque_X = -Vx*sc.posZ;torque_X361,14913 +Area1 = sum([webTop.Area]) + webRearSpar.Area + sum([webBottom.Area]);Area1364,14939 +Area1_check = get_int(frontSpar,backSpar,1)*chord^2 + get_int(frontSpar,backSpar,0)*chord^2;Area1_check366,15022 +Area2 = sum([webLowerNose.Area]) + sum([webUpperNose.Area]);Area2368,15116 +Area2_check = get_int(0,frontSpar,1)*chord^2 + get_int(0,frontSpar,0)*chord^2;Area2_check369,15177 +q1t_over_q2t = (A22/Area2 + webFrontSpar.dS_over_t/Area1)/(A11/Area1 + webFrontSpar.dS_over_t/Arq1t_over_q2t374,15312 +q2t = torque_X/(2*Area1*q1t_over_q2t + 2*Area2);q2t376,15415 +q1t = q2t*q1t_over_q2t;q1t377,15464 +qt_X = [q1t;q2t];qt_X378,15488 +q2t = torque_Z/(2*Area1*q1t_over_q2t + 2*Area2);q2t380,15507 +q1t = q2t*q1t_over_q2t;q1t381,15556 +qt_Z = [q1t;q2t];qt_Z382,15580 +xChord = 0:.01:1;xChord403,15777 +xChord = xChord*chord;xChord404,15795 +upperSurface = zeros(1,length(xChord));upperSurface405,15818 +lowerSurface = zeros(1,length(xChord));lowerSurface406,15858 + vecX = [frontSpar*chord webTop(i).xStart webTop(i).xEnd];vecX421,16255 + vecZ = [0 webTop(i).zStart webTop(i).zEnd];vecZ422,16316 + vecX = [frontSpar*chord webBottom(i).xStart webBottom(i).xEnd];vecX427,16429 + vecZ = [0 webBottom(i).zStart webBottom(i).zEnd];vecZ428,16496 + vecX = [frontSpar*chord webUpperNose(i).xStart webUpperNose(i).xEnd];vecX433,16618 + vecZ = [0 webUpperNose(i).zStart webUpperNose(i).zEnd];vecZ434,16691 + vecX = [frontSpar*chord webLowerNose(i).xStart webLowerNose(i).xEnd];vecX439,16819 + vecZ = [0 webLowerNose(i).zStart webLowerNose(i).zEnd];vecZ440,16892 + vecX = [frontSpar*chord sparCaps(3).posX sparCaps(4).posX];vecX444,16989 + vecZ = [0 sparCaps(3).posZ sparCaps(4).posZ];vecZ445,17052 +sparCapSize = 18;sparCapSize449,17136 +stringerSize = 18;stringerSize450,17154 + +/home/blendux/github/UCLA_MAE_154B/wing_scripts/get_z.m,481 +function z = get_z(x,u)get_z1,0 +M = 0.02;M9,66 +P = 0.4;P10,76 +T = 0.12;T11,85 +a0 = 0.2969;a012,95 +a1 = -0.126;a113,108 +a2 = -0.3516;a214,121 +a3 = 0.2843;a315,135 +a4 = -0.1015;a416,148 + z_camber = M/P^2*(2*P*x - x^2);z_camber19,171 + z_camber = (M/(1-P)^2)*(1 - 2*P +2*P*x - x^2);z_camber21,212 +z_thickness = (T/0.2)*(a0*x^.5+a1*x+a2*x^2+a3*x^3+a4*x^4);z_thickness25,301 + z = z_camber + z_thickness;z28,369 + z = z_camber - z_thickness;z30,406 + +/home/blendux/github/UCLA_MAE_154B/wing_scripts/get_dp.m,169 +function z = get_dp(xDist,zDist,Vx,Vz,Ix,Iz,Ixz,A)get_dp1,0 +denom = (Ix*Iz-Ixz^2);denom3,52 +z = -A*xDist*(Ix*Vx-Ixz*Vz)/denom - A*zDist*(Iz*Vz-Ixz*Vx)/denom;z4,75 + +/home/blendux/github/UCLA_MAE_154B/wing_scripts/get_int.m,925 +function z = get_int(xi,xf,u)get_int1,0 +M = 0.02;M3,31 +P = 0.4;P4,41 +T = 0.12;T5,50 +a0 = 0.2969;a06,60 +a1 = -0.126;a17,73 +a2 = -0.3516;a28,86 +a3 = 0.2843;a39,100 +a4 = -0.1015;a410,113 + 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 + 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 + 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 + 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 +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 +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 + z = intCamb + intThickness; z32,964 + z = abs(intCamb - intThickness);z34,1001 + +/home/blendux/github/UCLA_MAE_154B/wing_scripts/eye_beam_example.m,1004 +length = 20; % inlength4,44 +force = 10000; %lbsforce5,62 +max_width = 4; % inmax_width9,105 +min_width = 1; % inmin_width10,125 +y_max = 4; % iny_max11,145 +center_y = 2; % incenter_y12,161 +M = force*length;M17,218 +I = min_width*(2*center_y)^3/12 + 2*( max_width*(y_max-center_y)^3/12 + ...I19,237 +sigma_max = M * y_max / I;sigma_max22,370 +tempCoeff = force / (I * max_width);tempCoeff29,542 +int_y_da = ((y_max+center_y)/2) * max_width*(y_max-center_y);int_y_da30,579 +shear_1 = tempCoeff*int_y_da;shear_131,641 +tempCoeff = force / (I * min_width);tempCoeff34,749 +shear_2 = tempCoeff*int_y_da;shear_235,786 +tempCoeff = force / (I * min_width);tempCoeff39,857 +int_y_da = (center_y/2) * min_width*center_y;int_y_da40,894 +shear_3 = shear_2+tempCoeff*int_y_da;shear_341,940 +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 +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 + +/home/blendux/github/UCLA_MAE_154B/wing_scripts/get_ds.m,378 +function ds = get_ds(xi,xf,u)get_ds1,0 +dist = 0;dist3,31 +numSteps = 10;numSteps4,41 +dx = (xf-xi)/numSteps;dx5,56 +z0 = get_z(xi,u);z06,79 +x0 = xi;x07,97 + tempX = x0+dx;tempX9,117 + tempZ = get_z(tempX,u);tempZ11,153 + tempZ = 0;tempZ13,195 + dist = dist + (dx^2+(tempZ-z0)^2)^.5;dist15,222 + z0 = tempZ;z016,264 + x0 = tempX;x017,280 + +/home/blendux/github/UCLA_MAE_154B/wing_scripts/stringersBeamExample.m,837 +force = 8000; % lbsforce2,12 +stringer_A = 0.5; % in^2stringer_A3,32 +thickness = 0.04; % inthickness4,57 +top_stringers_y = 6; % intop_stringers_y6,81 +middle_stringers_y = 2; % inmiddle_stringers_y7,107 +I = 2*stringer_A*top_stringers_y^2 + 2*stringer_A*middle_stringers_y^2;I9,137 +shear_top_web = force / (I*thickness) * top_stringers_y * stringer_A;shear_top_web15,381 +shear_middle_web = shear_top_web + (force / (I*thickness) * middle_stringers_y * stringer_A);shear_middle_web16,451 +d_sigma = force * top_stringers_y / I; %(lbs/in^2)d_sigma36,1520 +d_force_top = d_sigma * stringer_A;d_force_top37,1572 +d_sigma = force * middle_stringers_y / I; %(lbs/in^2)d_sigma40,1631 +d_force_middle = d_force_top + d_sigma*stringer_A;d_force_middle41,1686 +check_load = 2*d_force_top*4 + d_force_middle*4;check_load44,1762 + +/home/blendux/github/UCLA_MAE_154B/wing_scripts/wingAnalysis_190422.m,10240 +Vx = 1; Vz = 1; My = 1; %test loads will be applied individuallyVx8,43 +numTopStringers = 6;numTopStringers11,124 +numBottomStringers = 8;numBottomStringers12,145 +numNoseTopStringers = 4;numNoseTopStringers13,169 +numNoseBottomStringers = 4;numNoseBottomStringers14,194 +t_upper = 0.02/12;t_upper16,223 +t_lower = 0.02/12;t_lower17,242 +t_upper_front = 0.02/12;t_upper_front18,261 +t_lower_front = 0.02/12;t_lower_front19,286 +t_frontSpar = 0.04/12;t_frontSpar20,311 +t_rearSpar = 0.04/12;t_rearSpar21,334 +frontSpar = 0.2;frontSpar23,357 +backSpar = 0.7;backSpar24,374 +chord = 5;chord25,390 +upperStringerGap = (sparCaps(3).posX - sparCaps(1).posX)/(numTopStringers + 1);upperStringerGap42,817 +lowerStringerGap = (sparCaps(3).posX - sparCaps(1).posX)/(numBottomStringers + 1);lowerStringerGap43,897 +upperNoseStringerGap = (sparCaps(1).posX - 0)/(numNoseTopStringers + 1);upperNoseStringerGap44,980 +lowerNoseStringerGap = (sparCaps(1).posX - 0)/(numNoseBottomStringers + 1);lowerNoseStringerGap45,1053 +Ix = 0; Iz = 0; Ixz = 0;Ix98,3144 + Ix = Ix + sparCaps(i).area*(sparCaps(i).posZ-centroid.posZ)^2;Ix101,3191 + Iz = Iz + sparCaps(i).area*(sparCaps(i).posX-centroid.posX)^2;Iz102,3258 + Ixz = Ixz + sparCaps(i).area*(sparCaps(i).posX-centroid.posX)*(sparCaps(i).posZ-centroid.posIxz103,3325 + Ix = Ix + topStringers(i).area*(topStringers(i).posZ-centroid.posZ)^2;Ix108,3470 + Iz = Iz + topStringers(i).area*(topStringers(i).posX-centroid.posX)^2;Iz109,3545 + Ixz = Ixz + topStringers(i).area*(topStringers(i).posX-centroid.posX)*(topStringers(i).posZ-Ixz110,3620 + Ix = Ix + bottomStringers(i).area*(bottomStringers(i).posZ-centroid.posZ)^2;Ix113,3781 + Iz = Iz + bottomStringers(i).area*(bottomStringers(i).posX-centroid.posX)^2;Iz114,3862 + Ixz = Ixz + bottomStringers(i).area*(bottomStringers(i).posX-centroid.posX)*(bottomStringersIxz115,3943 + Ix = Ix + noseTopStringers(i).area*(noseTopStringers(i).posZ-centroid.posZ)^2;Ix118,4116 + Iz = Iz + noseTopStringers(i).area*(noseTopStringers(i).posX-centroid.posX)^2;Iz119,4199 + Ixz = Ixz + noseTopStringers(i).area*(noseTopStringers(i).posX-centroid.posX)*(noseTopStringIxz120,4282 + Ix = Ix + noseBottomStringers(i).area*(noseBottomStringers(i).posZ-centroid.posZ)^2;Ix123,4464 + Iz = Iz + noseBottomStringers(i).area*(noseBottomStringers(i).posX-centroid.posX)^2;Iz124,4553 + Ixz = Ixz + noseBottomStringers(i).area*(noseBottomStringers(i).posX-centroid.posX)*(noseBotIxz125,4642 +numStringers = numTopStringers;numStringers135,4835 +stringerGap = upperStringerGap;stringerGap136,4867 +webThickness = t_upper;webThickness137,4899 +tempStringers = topStringers;tempStringers138,4923 + dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx154,5458 + tempInt = get_int(web(i).xStart/chord,web(i).xEnd/chord,1)*chord^2; %integral of airfoil futempInt160,5814 + triangle1 = abs( (web(i).xStart - sparCaps(1).posX)*web(i).zStart/2);triangle1161,5917 + triangle2 = abs((web(i).xEnd - sparCaps(1).posX)*web(i).zEnd/2);triangle2162,5991 +webTop = web;webTop176,6752 +web = [];web177,6766 +dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx187,6991 +webRearSpar = web;webRearSpar207,8039 +web = [];web208,8058 +numStringers = numBottomStringers;numStringers212,8082 +stringerGap = lowerStringerGap;stringerGap213,8117 +webThickness = t_lower;webThickness214,8149 +tempStringers = bottomStringers;tempStringers215,8173 + dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx223,8489 + tempInt = get_int(web(i).xEnd/chord,web(i).xStart/chord,0)*chord^2; %integral of airfoil futempInt238,9196 + triangle2 = abs((web(i).xStart - sparCaps(1).posX)*web(i).zStart/2);triangle2239,9299 + triangle1 = abs((web(i).xEnd - sparCaps(1).posX)*web(i).zEnd/2);triangle1240,9372 +webBottom = web;webBottom256,10207 +web = [];web257,10224 +dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx267,10451 +webFrontSpar = web;webFrontSpar285,11387 +web = [];web286,11407 +numStringers = numNoseBottomStringers;numStringers294,11453 +stringerGap = lowerNoseStringerGap;stringerGap295,11492 +webThickness = t_lower_front;webThickness296,11528 +tempStringers = noseBottomStringers;tempStringers297,11558 + dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx305,11878 + tempInt = get_int(web(i).xEnd/chord,web(i).xStart/chord,0)*chord^2; %integral of airfoil futempInt320,12433 + triangle1 = abs((web(i).xStart - sparCaps(2).posX)*web(i).zStart/2);triangle1321,12536 + triangle2 = abs((web(i).xEnd - sparCaps(2).posX)*web(i).zEnd/2);triangle2322,12609 +webLowerNose = web;webLowerNose338,13448 +web = [];web339,13468 +numStringers = numNoseTopStringers;numStringers342,13496 +stringerGap = upperNoseStringerGap;stringerGap343,13532 +webThickness = t_upper_front;webThickness344,13568 +tempStringers = noseTopStringers;tempStringers345,13598 + dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx353,13877 + tempInt = get_int(web(i).xStart/chord,web(i).xEnd/chord,1)*chord^2; %integral of airfoil futempInt367,14536 + triangle2 = abs((web(i).xStart - sparCaps(2).posX)*web(i).zStart/2);triangle2368,14639 + triangle1 = abs((web(i).xEnd - sparCaps(2).posX)*web(i).zEnd/2);triangle1369,14712 +webUpperNose = web;webUpperNose384,15474 +web = [];web385,15494 +dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ;dx396,15722 +webFrontSparCell2 = web;webFrontSparCell2414,16666 +web = [];web415,16691 +Fx = sum([webTop.qp_dx_X])+webRearSpar.qp_dx_X+ sum([webBottom.qp_dx_X])+webFrontSpar.qp_dx_X; Fx420,16736 +Fx = Fx + sum([webLowerNose.qp_dx_X])+ sum([webUpperNose.qp_dx_X]); %cell 2Fx421,16840 +Fz = sum([webTop.qp_dz_X])+webRearSpar.qp_dz_X+ sum([webBottom.qp_dz_X])+webFrontSpar.qp_dz_X; Fz423,16920 +Fz = Fz + sum([webLowerNose.qp_dz_X])+ sum([webUpperNose.qp_dz_X]); %cell 2Fz424,17024 +Fx = sum([webTop.qp_dx_Z])+webRearSpar.qp_dx_Z+ sum([webBottom.qp_dx_Z])+webFrontSpar.qp_dx_Z; Fx430,17139 +Fx = Fx + sum([webLowerNose.qp_dx_Z])+ sum([webUpperNose.qp_dx_Z]); %cell 2Fx431,17243 +Fz = sum([webTop.qp_dz_Z])+webRearSpar.qp_dz_Z+ sum([webBottom.qp_dz_Z])+webFrontSpar.qp_dz_Z; Fz433,17323 +Fz = Fz + sum([webLowerNose.qp_dz_Z])+ sum([webUpperNose.qp_dz_Z]); %cell 2Fz434,17427 +A11 = sum([webTop.dS_over_t])+webRearSpar.dS_over_t+ sum([webBottom.dS_over_t])+webFrontSpar.dS_A11443,17597 +A22 = sum([webLowerNose.dS_over_t])+ sum([webUpperNose.dS_over_t])+webFrontSparCell2.dS_over_t;A22444,17701 +A12 = -webFrontSpar.dS_over_t;A12445,17797 +A21 = -webFrontSparCell2.dS_over_t;A21446,17828 +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 +B2_X = sum([webLowerNose.q_dS_over_t_X])+ sum([webUpperNose.q_dS_over_t_X])+webFrontSparCell2.q_B2_X449,17986 +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 +B2_Z = sum([webLowerNose.q_dS_over_t_Z])+ sum([webUpperNose.q_dS_over_t_Z])+webFrontSparCell2.q_B2_Z451,18216 +Amat = [A11 A12; A21 A22];Amat453,18326 +Bmat_X = -[B1_X;B2_X];Bmat_X454,18353 +Bmat_Z = -[B1_Z;B2_Z];Bmat_Z455,18376 +qs_X = inv(Amat)*Bmat_X;qs_X457,18400 +qs_Z = inv(Amat)*Bmat_Z;qs_Z458,18425 +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 +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 +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 +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 +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 +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 +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 +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 +torque_Z = Vz*(sc.posX - 0.25*chord);torque_Z480,19547 +torque_X = -Vx*sc.posZ;torque_X481,19585 +Area1 = sum([webTop.Area]) + webRearSpar.Area + sum([webBottom.Area]);Area1484,19611 +Area1_check = get_int(frontSpar,backSpar,1)*chord^2 + get_int(frontSpar,backSpar,0)*chord^2;Area1_check486,19694 +Area2 = sum([webLowerNose.Area]) + sum([webUpperNose.Area]);Area2488,19788 +Area2_check = get_int(0,frontSpar,1)*chord^2 + get_int(0,frontSpar,0)*chord^2;Area2_check489,19849 +q1t_over_q2t = (A22/Area2 + webFrontSpar.dS_over_t/Area1)/(A11/Area1 + webFrontSpar.dS_over_t/Arq1t_over_q2t494,19984 +q2t = torque_X/(2*Area1*q1t_over_q2t + 2*Area2);q2t496,20087 +q1t = q2t*q1t_over_q2t;q1t497,20136 +qt_X = [q1t;q2t];qt_X498,20160 +q2t = torque_Z/(2*Area1*q1t_over_q2t + 2*Area2);q2t500,20179 +q1t = q2t*q1t_over_q2t;q1t501,20228 +qt_Z = [q1t;q2t];qt_Z502,20252 +xChord = 0:.01:1;xChord523,20449 +xChord = xChord*chord;xChord524,20467 +upperSurface = zeros(1,length(xChord));upperSurface525,20490 +lowerSurface = zeros(1,length(xChord));lowerSurface526,20530 + vecX = [frontSpar*chord webTop(i).xStart webTop(i).xEnd];vecX541,20927 + vecZ = [0 webTop(i).zStart webTop(i).zEnd];vecZ542,20988 + vecX = [frontSpar*chord webBottom(i).xStart webBottom(i).xEnd];vecX547,21101 + vecZ = [0 webBottom(i).zStart webBottom(i).zEnd];vecZ548,21168 + vecX = [frontSpar*chord webUpperNose(i).xStart webUpperNose(i).xEnd];vecX553,21290 + vecZ = [0 webUpperNose(i).zStart webUpperNose(i).zEnd];vecZ554,21363 + vecX = [frontSpar*chord webLowerNose(i).xStart webLowerNose(i).xEnd];vecX559,21491 + vecZ = [0 webLowerNose(i).zStart webLowerNose(i).zEnd];vecZ560,21564 + vecX = [frontSpar*chord sparCaps(3).posX sparCaps(4).posX];vecX564,21661 + vecZ = [0 sparCaps(3).posZ sparCaps(4).posZ];vecZ565,21724 +sparCapSize = 18;sparCapSize569,21808 +stringerSize = 18;stringerSize570,21826 + +/home/blendux/github/UCLA_MAE_154B/gui.py,393 +import tkinter as tktk20,820 +import tkinter.ttk as ttkttk21,841 +class MainWindow(tk.Frame):MainWindow27,963 + def __init__(self, *args, **kwargs):__init__30,1022 + def create_window(self):create_window64,2364 +def new_field(parent, name):new_field72,2661 +def set_naca(name):set_naca80,2826 +def set_chord(name):set_chord85,2894 +def set_semi_span(name):set_semi_span90,2957 + +/home/blendux/github/UCLA_MAE_154B/README.md,94 +# UCLA MAE 154BUCLA MAE 154B1,0 +## Spring 2019 Final ProjectSpring 2019 Final Project3,17 + +/home/blendux/github/UCLA_MAE_154B/tools/evaluator.py,1051 +import numpy as npnp24,959 +import matplotlib.pyplot as pltplt26,1000 +class Evaluator:Evaluator29,1034 + def __init__(self, airfoil):__init__32,1130 + def __str__(self):__str__56,1932 + def info_print(self, round):info_print59,1991 + def info_save(self, save_path, number):info_save74,2570 + def get_lift_rectangular(self, lift):get_lift_rectangular92,3362 + def get_lift_elliptical(self, L_0):get_lift_elliptical96,3507 + def get_lift_total(self):get_lift_total103,3719 + def get_mass_distribution(self, total_mass):get_mass_distribution108,3900 + def get_drag(self, drag):get_drag112,4047 + def get_centroid(self):get_centroid124,4473 + def get_inertia_terms(self):get_inertia_terms147,5377 + def get_dx(self, component):get_dx180,6841 + def get_dz(self, component):get_dz183,6940 + def get_dP(self, xDist, zDist, V_x, V_z, area):get_dP186,7039 + def analysis(self, V_x, V_z):analysis199,7491 +def plot_geom(evaluator):plot_geom219,8423 +def plot_lift(evaluator):plot_lift272,10194 + +/home/blendux/github/UCLA_MAE_154B/tools/creator.py,1569 +import numpy as npnp31,1142 +import bisect as bibi33,1193 +import matplotlib.pyplot as pltplt34,1213 +class Airfoil:Airfoil37,1247 + chord = 100chord51,1727 + semi_span = 200semi_span52,1743 + def __init__(self):__init__54,1764 + def from_dimensions(cls, chord, semi_span):from_dimensions65,2007 + def __str__(self):__str__75,2337 + def add_naca(self, naca_num):add_naca78,2396 + def get_camber(x):get_camber99,3112 + def get_thickness(x):get_thickness113,3714 + def get_theta(x):get_theta124,4162 + def get_upper_coord(x):get_upper_coord132,4452 + def get_lower_coord(x):get_lower_coord137,4637 + def add_mass(self, mass):add_mass165,5804 + def info_print(self, round):info_print168,5860 + def info_save(self, save_path, number):info_save183,6442 +class Spar(Airfoil):Spar200,7175 + def __init__(self):__init__203,7242 + def add_coord(self, airfoil, x_loc_percent):add_coord211,7427 + def add_spar_caps(self, spar_cap_area):add_spar_caps238,8357 + def add_mass(self, mass):add_mass242,8460 + def add_webs(self, thickness):add_webs246,8550 +class Stringer(Airfoil):Stringer257,8896 + def __init__(self):__init__260,8975 + def add_coord(self, airfoil,add_coord269,9188 + def add_area(self, area):add_area329,11686 + def add_mass(self, mass):add_mass333,11762 + def add_webs(self, thickness):add_webs337,11873 + def info_print(self, round):info_print347,12223 +def plot_geom(airfoil, view: False):plot_geom353,12375 +def main():main410,14137 + +/home/blendux/github/UCLA_MAE_154B/tools/generator.py,332 +def default_airfoil():default_airfoil23,867 +class Population(creator.Airfoil):Population45,1474 + def __init__(self, size):__init__48,1551 + def mutate(self, prob_mt):mutate54,1720 + def crossover(self, prob_cx):crossover57,1824 + def reproduce(self, prob_rp):reproduce60,1923 + def fitness():fitness63,2034 diff --git a/example_airfoil.py b/example_airfoil.py index 0fd0aba..e0eb532 100644 --- a/example_airfoil.py +++ b/example_airfoil.py @@ -10,26 +10,27 @@ Generate a population of airfoils & optimize. from tools import creator, evaluator, generator + import time start_time = time.time() -# Airfoil dimensions +# Airfoil dimensions (in) NACA_NUM = 2412 -CHORD_LENGTH = 68 # inches -SEMI_SPAN = 150 # inches +CHORD_LENGTH = 68 +SEMI_SPAN = 150 # Thicknesses SPAR_THICKNESS = 0.4 SKIN_THICKNESS = 0.1 -# Component masses -AIRFOIL_MASS = 10 # lbs -SPAR_MASS = 10 # lbs -STRINGER_MASS = 5 # lbs +# Component masses (lbs) +AIRFOIL_MASS = 10 +SPAR_MASS = 10 +STRINGER_MASS = 5 -# Area -SPAR_CAP_AREA = 0.3 # sqin -STRINGER_AREA = 0.1 # sqin +# Area (sqin) +SPAR_CAP_AREA = 0.3 +STRINGER_AREA = 0.1 # Amount of stringers TOP_STRINGERS = 6 @@ -37,7 +38,7 @@ BOTTOM_STRINGERS = 4 NOSE_TOP_STRINGERS = 3 NOSE_BOTTOM_STRINGERS = 5 -SAVE_PATH = 'C:/Users/blend/github/UCLA_MAE_154B/save' +SAVE_PATH = '/home/blendux/github/UCLA_MAE_154B/save/' # Create airfoil instance @@ -87,9 +88,9 @@ evaluator.plot_lift(eval) pop = generator.Population(10) -print(help(creator)) -print(help(evaluator)) -print(help(generator)) +# print(help(creator)) +# print(help(evaluator)) +# print(help(generator)) # Print final execution time print("--- %s seconds ---" % (time.time() - start_time)) diff --git a/tools/creator.py b/tools/creator.py index 01f73ad..6d074f8 100644 --- a/tools/creator.py +++ b/tools/creator.py @@ -37,7 +37,7 @@ import matplotlib.pyplot as plt class Airfoil: """This class represents a single NACA airfoil. - Please note: the coordinates are saved as two lists + The coordinates are saved as two lists for the x- and z-coordinates. The coordinates start at the leading edge, travel over the airfoil's upper edge, then loop back to the leading edge via the lower edge. @@ -69,7 +69,7 @@ class Airfoil: else: cls.chord = 20 print('Chord too small, using minimum value of 20.') - cls.semi_span = semi_span + cls.semi_span = semi_span return Airfoil() def __str__(self): @@ -175,7 +175,7 @@ class Airfoil: for k, v in self.__dict__.items(): if type(v) != list: print('{}:\n'.format(k), v) - print(num_of_dashes * '-') + print(num_of_dashes * '-') for k, v in self.__dict__.items(): if type(v) == list: print('{}:\n'.format(k), np.around(v, round)) @@ -251,7 +251,7 @@ class Spar(Airfoil): self.x_end.append(self.x[_][1]) self.z_start.append(self.z[_][0]) self.z_end.append(self.z[_][1]) - self.thickness = thickness + self.thickness = thickness return None @@ -296,8 +296,8 @@ class Stringer(Airfoil): self.x.append(airfoil.x[i]) self.z.append(airfoil.z[i]) x += interval - # Add upper stringers from first spar until last spar - # TODO: stringer placement if only one spar is created + # Add upper stringers from first spar until last spar + # TODO: stringer placement if only one spar is created interval = (airfoil.spar.x[-1][0] - airfoil.spar.x[0][0]) / (stringer_u_2 + 1) x = interval + airfoil.spar.x[0][0] @@ -316,7 +316,7 @@ class Stringer(Airfoil): self.x.append(airfoil.x[-i]) self.z.append(airfoil.z[-i]) x += interval - # Add lower stringers from first spar until last spar + # Add lower stringers from first spar until last spar interval = (airfoil.spar.x[-1][1] - airfoil.spar.x[0][1]) / (stringer_l_2 + 1) x = interval + airfoil.spar.x[0][1] @@ -342,7 +342,7 @@ class Stringer(Airfoil): self.x_end.append(self.x[_ + 1]) self.z_start.append(self.z[_]) self.z_end.append(self.z[_ + 1]) - self.thickness = thickness + self.thickness = thickness return None def info_print(self, round): @@ -379,7 +379,7 @@ def plot_geom(airfoil, view: False): ax.plot(x, y, '-', color='y', linewidth='4') except AttributeError: print('No spars to plot.') - # Plot stringers + # Plot stringers try: for _ in range(0, len(airfoil.stringer.x)): x = airfoil.stringer.x[_] |