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Attempting to make multiple plots on multiple graphs using several arrays

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Daniel Jones
Daniel Jones 2018-4-9
回答： Aletta Wilbrink 2018-4-10
I'm trying to generate multiple plots using different columns from several matricies but at present I can only get one plot to show up with the plots on one diagram. I'm beginning to think I should have just used excel. Since I can't explain it much better than that, I've attached the code below.
% Xfoil polar. Reynolds number fixed. Mach  number fixed
% Polar key xf-naca651212-il-1000000
% Airfoil naca651212-il
% Reynolds number 1000000
% Ncrit 9
% Mach 0
% Max Cl/Cd 87.814
% Max Cl/Cd alpha 3.25
A = [
-9.5 -0.7923 0.02332 0.01914 -0.0473 0.9776 0.0123
-9.25 -0.7622 0.02202 0.01763 -0.0489 0.9698 0.0126
-9 -0.7351 0.02123 0.01666 -0.0495 0.9585 0.0129
-8.75 -0.72 0.0179 0.01298 -0.0484 0.9453 0.0135
-8.25 -0.6762 0.01677 0.01171 -0.047 0.9234 0.0143
-8 -0.654 0.01619 0.01103 -0.0462 0.9138 0.0147
-6.25 -0.4926 0.01183 0.00608 -0.0419 0.856 0.0184
-6 -0.4675 0.01151 0.00573 -0.0416 0.8488 0.0192
-5.75 -0.4421 0.01121 0.00538 -0.0413 0.8414 0.0201
-5.5 -0.4168 0.01087 0.00498 -0.041 0.8346 0.0209
-5 -0.365 0.01032 0.00433 -0.0406 0.8214 0.0221
-4.75 -0.3409 0.00969 0.00362 -0.0402 0.8145 0.0237
-4.25 -0.2878 0.00921 0.00307 -0.04 0.8017 0.0273
-4 -0.2607 0.00905 0.00287 -0.04 0.7954 0.0288
-3.75 -0.2342 0.00873 0.0025 -0.0399 0.7897 0.0328
-3.5 -0.2069 0.00853 0.00229 -0.0399 0.7835 0.0368
-3 -0.1553 0.00759 0.00178 -0.0398 0.7718 0.1581
-2.75 -0.1333 0.00642 0.00139 -0.0397 0.766 0.377
-2.5 -0.1088 0.0057 0.00121 -0.0396 0.7607 0.5377
-2.25 -0.0811 0.00555 0.00117 -0.0397 0.7551 0.5827
-1.75 -0.0246 0.00545 0.00113 -0.04 0.7446 0.6322
-1.5 0.0035 0.00541 0.00114 -0.0401 0.7393 0.6549
-1.25 0.0317 0.00543 0.00115 -0.0402 0.7342 0.6728
-0.75 0.0888 0.00543 0.00118 -0.0406 0.7242 0.6958
-0.5 0.1173 0.00545 0.00117 -0.0408 0.7194 0.7007
-0.25 0.1463 0.00546 0.00117 -0.0411 0.7147 0.7056
0 0.175 0.00545 0.00117 -0.0413 0.7099 0.7103
0.25 0.2035 0.00547 0.00118 -0.0415 0.7052 0.7153
0.5 0.2324 0.00549 0.00119 -0.0418 0.7008 0.7203
0.75 0.2611 0.00549 0.00121 -0.042 0.6961 0.7252
1 0.2896 0.00551 0.00125 -0.0422 0.6915 0.7303
1.25 0.3183 0.00554 0.00128 -0.0425 0.6859 0.7357
1.5 0.3466 0.00554 0.00129 -0.0426 0.6778 0.7408
1.75 0.3747 0.00555 0.00132 -0.0427 0.6669 0.7462
2 0.4029 0.0056 0.00134 -0.0428 0.6541 0.7518
2.25 0.4303 0.00563 0.00136 -0.0428 0.6352 0.7572
2.5 0.4579 0.00569 0.0014 -0.0428 0.6183 0.7631
2.75 0.4853 0.00579 0.00146 -0.0428 0.5958 0.7688
3.25 0.5383 0.00613 0.00163 -0.0424 0.5275 0.7808
3.5 0.5587 0.00686 0.00191 -0.0414 0.4079 0.787
3.75 0.5746 0.00812 0.00245 -0.0398 0.2379 0.794
4 0.5927 0.00915 0.00293 -0.0386 0.1086 0.8005
4.25 0.6139 0.00984 0.00333 -0.0377 0.044 0.8075
4.5 0.6387 0.01019 0.00365 -0.0373 0.0327 0.8144
4.75 0.6643 0.01041 0.00392 -0.037 0.0298 0.8215
5 0.6882 0.01083 0.00436 -0.0364 0.0252 0.8289
5.25 0.7135 0.01104 0.00462 -0.0361 0.0238 0.8361
5.5 0.7384 0.01132 0.00494 -0.0357 0.0223 0.8437
6 0.7827 0.01229 0.00602 -0.034 0.0192 0.8601
6.25 0.8056 0.01265 0.00646 -0.0332 0.0186 0.869
6.5 0.8283 0.01301 0.00688 -0.0324 0.0181 0.8778
7 0.8713 0.01383 0.00784 -0.0304 0.0169 0.8974
7.25 0.8926 0.01418 0.00823 -0.0294 0.0162 0.9081
7.5 0.9126 0.01457 0.00867 -0.0282 0.0156 0.92
8 0.9368 0.01648 0.01079 -0.023 0.0144 0.9571
8.25 0.9635 0.0172 0.01161 -0.0234 0.0142 1
8.5 0.9857 0.01781 0.01227 -0.0229 0.014 1
8.75 1.0069 0.01856 0.01308 -0.0221 0.0137 1];
% Xfoil polar. Reynolds number fixed. Mach  number fixed
% Polar key xf-naca651212-il-1000000-n5
% Airfoil naca651212-il
% Reynolds number 1000000
% Ncrit 5
% Mach 0
% Max Cl/Cd 70.796
% Max Cl/Cd alpha 2.25
B = [-9.5 -0.8157 0.01598 0.01068 -0.0444 0.894 0.0104
-9.25 -0.7935 0.01554 0.01016 -0.0437 0.8849 0.0107
-9 -0.7709 0.01515 0.00969 -0.0431 0.8757 0.011
-8.75 -0.7482 0.01468 0.00913 -0.0426 0.867 0.0113
-8.25 -0.7009 0.01394 0.00824 -0.0417 0.851 0.012
-8 -0.6774 0.01354 0.00774 -0.0412 0.8435 0.0122
-6.25 -0.5049 0.01097 0.00478 -0.039 0.7947 0.0149
-6 -0.479 0.0107 0.00445 -0.0389 0.788 0.0153
-5.75 -0.4529 0.01044 0.00414 -0.0387 0.7822 0.0159
-5.5 -0.4264 0.01021 0.00386 -0.0387 0.7761 0.0162
-5 -0.3736 0.00969 0.00327 -0.0385 0.7644 0.0182
-4.75 -0.3468 0.00949 0.00305 -0.0385 0.7582 0.0192
-4.25 -0.2924 0.00916 0.00265 -0.0386 0.747 0.0214
-4 -0.2652 0.00899 0.00245 -0.0386 0.7417 0.023
-3.75 -0.2378 0.00881 0.00227 -0.0387 0.7368 0.0256
-3.5 -0.2102 0.00867 0.00212 -0.0388 0.7313 0.0279
-3 -0.155 0.0084 0.00183 -0.039 0.7211 0.0374
-2.75 -0.1276 0.00819 0.0017 -0.0391 0.7162 0.0572
-2.5 -0.1007 0.0079 0.00154 -0.0392 0.7113 0.1037
-2.25 -0.0748 0.00739 0.00135 -0.0393 0.7068 0.2001
-1.75 -0.025 0.00589 0.00093 -0.0395 0.6971 0.515
-1.5 0.0024 0.00567 0.00091 -0.0396 0.6929 0.5813
-1.25 0.0305 0.00557 0.00091 -0.0397 0.6882 0.6158
-0.75 0.0873 0.00553 0.00091 -0.0401 0.6792 0.6504
-0.5 0.1161 0.00552 0.00091 -0.0404 0.6749 0.6569
-0.25 0.1449 0.00552 0.00091 -0.0406 0.6703 0.6616
0 0.1736 0.00555 0.00091 -0.0409 0.666 0.6661
0.25 0.2024 0.00555 0.00092 -0.0411 0.6619 0.6704
0.5 0.2312 0.00555 0.00094 -0.0414 0.6575 0.6751
0.75 0.2599 0.00558 0.00095 -0.0416 0.653 0.6798
1 0.2885 0.0056 0.00098 -0.0419 0.6489 0.6842
1.25 0.3171 0.00561 0.00102 -0.0421 0.642 0.6888
1.5 0.3452 0.00567 0.00104 -0.0422 0.6276 0.6938
1.75 0.3733 0.00573 0.00108 -0.0423 0.6137 0.6983
2 0.4006 0.00583 0.00112 -0.0423 0.5912 0.703
2.25 0.4269 0.00603 0.00118 -0.0421 0.5476 0.7082
2.5 0.4517 0.0064 0.00131 -0.0418 0.4799 0.7131
2.75 0.4715 0.00729 0.00165 -0.0407 0.343 0.7182
3.25 0.5145 0.00879 0.00232 -0.0393 0.1363 0.7285
3.5 0.5377 0.00933 0.00262 -0.0388 0.0721 0.7341
3.75 0.5626 0.00969 0.00286 -0.0385 0.0411 0.74
4 0.5888 0.00992 0.00306 -0.0383 0.0321 0.7453
4.25 0.615 0.01012 0.00326 -0.0382 0.028 0.7511
4.5 0.6413 0.01033 0.00348 -0.038 0.0246 0.7569
4.75 0.6675 0.01051 0.00369 -0.0379 0.0227 0.7628
5 0.6933 0.01074 0.00393 -0.0377 0.0205 0.7695
5.25 0.7187 0.01099 0.00421 -0.0374 0.0184 0.7757
5.5 0.7444 0.01121 0.00447 -0.0372 0.0175 0.7824
6 0.7946 0.01172 0.00502 -0.0366 0.0152 0.7953
6.25 0.8186 0.01208 0.00541 -0.0361 0.014 0.8025
6.5 0.843 0.01235 0.00574 -0.0357 0.0137 0.8097
7 0.8907 0.01298 0.00648 -0.0347 0.0129 0.8247
7.25 0.914 0.01333 0.00689 -0.0341 0.0125 0.8324
7.5 0.9367 0.01369 0.0073 -0.0334 0.0122 0.8403
8 0.9808 0.01444 0.00817 -0.0318 0.0116 0.8582
8.25 1.0019 0.01486 0.00865 -0.0309 0.0114 0.8675
8.5 1.0221 0.01532 0.00917 -0.0298 0.011 0.8776
8.75 1.0407 0.01583 0.00976 -0.0285 0.0108 0.889];
s = 'AB';
for ns = 1:length(s)
Dan = eval(s(ns));
subplot(3,2,1)
plot(Dan(:,1),Dan(:,2)); % Cl vs Alpha
hold on
title('Cl vs Alpha');
xlabel('Angle of Attack'); % x-axis label
ylabel('Cl') % y-axis label
DivA = bsxfun(@rdivide,Dan(:,2),(Dan(:,3))); % dividing colum 2 by 3 (cl/cd)
subplot(3,2,2)
plot(Dan(:,1),DivA) % Cl / Cd vs Alpha
title('Cl / Cd vs Alpha')
subplot(3,2,3)
plot(Dan(:,1),Dan(:,3)) % Cd vs Alpha
title('Cd vs Alpha')
subplot(3,2,4)
plot(Dan(:,1),Dan(:,5)) % Cm vs Alpha
title('Cm vs Alpha')
subplot(3,2,5)
%subplot(Dan(:,3),Dan(:,2)) % Cl vs Cd
%title('Cl vs Cd')
end
  1 个评论
Aletta Wilbrink
Aletta Wilbrink 2018-4-9
When I run your code, I do get to see multiple plots. What is it exactly you want?
Do you want multiple figures? Or do you want all the plots in the same window?

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回答（2 个）

Daniel Jones
Daniel Jones 2018-4-9
I changed it so that there should only be two lines per plot. Currently I only get the two lines for the first plot the remaining plots have just the one line.
Aletta Wilbrink
Aletta Wilbrink 2018-4-10
Every time you want a new line in the same plot use hold on and if you want a new plot use hold off.
You only use hold on for the first plot now

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