Attempting to make multiple plots on multiple graphs using several arrays

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

[Aletta Wilbrink]

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?

Answer 1

[Daniel Jones]

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.

Answer 2

[Aletta Wilbrink]

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