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GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il)
Reynolds number: 200,000
Max Cl/Cd: 74.01 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe140-il-200000-n5.txt
Download as CSV file: xf-goe140-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 140 (MVA H.17) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2938   0.10092   0.09766  -0.0245   1.0000   0.0260
  -8.000  -0.2942   0.09859   0.09539  -0.0263   1.0000   0.0262
  -7.750  -0.2921   0.09587   0.09273  -0.0285   1.0000   0.0262
  -7.500  -0.2882   0.09285   0.08977  -0.0303   1.0000   0.0263
  -7.250  -0.2717   0.08859   0.08551  -0.0353   0.9941   0.0263
  -7.000  -0.2461   0.08354   0.08042  -0.0425   0.9818   0.0264
  -6.750  -0.2353   0.07814   0.07504  -0.0421   0.9721   0.0272
  -6.500  -0.2163   0.07535   0.07224  -0.0428   0.9588   0.0289
  -6.250  -0.1911   0.07191   0.06876  -0.0480   0.9412   0.0320
  -6.000  -0.1434   0.06731   0.06395  -0.0637   0.9195   0.0356
  -5.750  -0.1120   0.06296   0.05943  -0.0704   0.8996   0.0358
  -5.500  -0.0823   0.05912   0.05540  -0.0751   0.8794   0.0360
  -5.250  -0.0671   0.05368   0.04988  -0.0770   0.8608   0.0368
  -5.000  -0.0500   0.05091   0.04704  -0.0772   0.8413   0.0376
  -4.750  -0.0287   0.04839   0.04439  -0.0783   0.8224   0.0388
  -4.500  -0.0038   0.04581   0.04163  -0.0802   0.8040   0.0404
  -4.250   0.0434   0.04375   0.03898  -0.0859   0.7864   0.0472
  -4.000   0.0720   0.04098   0.03591  -0.0875   0.7692   0.0473
  -3.750   0.0996   0.03834   0.03299  -0.0887   0.7515   0.0473
  -3.500   0.1272   0.03576   0.03015  -0.0898   0.7332   0.0473
  -3.250   0.1516   0.03273   0.02697  -0.0907   0.7147   0.0468
  -3.000   0.1757   0.03022   0.02435  -0.0916   0.6956   0.0452
  -2.500   0.2360   0.02558   0.01900  -0.0933   0.6586   0.0401
  -2.250   0.2678   0.02327   0.01621  -0.0940   0.6407   0.0387
  -2.000   0.2980   0.02157   0.01412  -0.0943   0.6224   0.0384
  -1.750   0.3273   0.02025   0.01244  -0.0945   0.6046   0.0384
  -1.500   0.3552   0.01963   0.01160  -0.0947   0.5866   0.0398
  -1.250   0.3837   0.01889   0.01061  -0.0948   0.5688   0.0411
  -1.000   0.4128   0.01785   0.00925  -0.0949   0.5518   0.0407
  -0.750   0.4417   0.01693   0.00804  -0.0948   0.5352   0.0404
  -0.500   0.4700   0.01619   0.00705  -0.0948   0.5190   0.0405
  -0.250   0.4981   0.01562   0.00629  -0.0947   0.5037   0.0408
   0.000   0.5259   0.01517   0.00567  -0.0946   0.4895   0.0415
   0.250   0.5537   0.01482   0.00519  -0.0946   0.4762   0.0425
   0.500   0.5813   0.01454   0.00480  -0.0945   0.4643   0.0437
   0.750   0.6091   0.01432   0.00451  -0.0945   0.4527   0.0451
   1.000   0.6368   0.01422   0.00432  -0.0945   0.4420   0.0472
   1.250   0.6643   0.01421   0.00430  -0.0945   0.4318   0.0509
   1.500   0.6921   0.01418   0.00423  -0.0945   0.4220   0.0540
   1.750   0.7199   0.01416   0.00414  -0.0945   0.4132   0.0578
   2.000   0.7475   0.01420   0.00414  -0.0945   0.4050   0.0662
   2.250   0.7752   0.01425   0.00415  -0.0945   0.3973   0.0803
   2.500   0.8026   0.01433   0.00421  -0.0945   0.3901   0.0955
   3.000   0.8505   0.01285   0.00449  -0.0931   0.3770   1.0000
   3.250   0.8777   0.01308   0.00462  -0.0931   0.3710   1.0000
   3.500   0.9050   0.01329   0.00477  -0.0930   0.3646   1.0000
   3.750   0.9318   0.01356   0.00494  -0.0929   0.3588   1.0000
   4.000   0.9590   0.01377   0.00515  -0.0928   0.3518   1.0000
   4.250   0.9855   0.01403   0.00534  -0.0927   0.3452   1.0000
   4.500   1.0124   0.01427   0.00557  -0.0926   0.3388   1.0000
   4.750   1.0390   0.01452   0.00582  -0.0925   0.3327   1.0000
   5.000   1.0652   0.01481   0.00607  -0.0923   0.3278   1.0000
   5.250   1.0918   0.01504   0.00633  -0.0922   0.3205   1.0000
   5.500   1.1175   0.01531   0.00658  -0.0920   0.3104   1.0000
   5.750   1.1429   0.01560   0.00683  -0.0917   0.2994   1.0000
   6.000   1.1689   0.01584   0.00711  -0.0916   0.2896   1.0000
   6.250   1.1942   0.01614   0.00742  -0.0913   0.2795   1.0000
   6.500   1.2190   0.01647   0.00772  -0.0910   0.2636   1.0000
   6.750   1.2431   0.01686   0.00805  -0.0906   0.2449   1.0000
   7.000   1.2656   0.01743   0.00846  -0.0901   0.2144   1.0000
   7.250   1.2769   0.01936   0.00968  -0.0884   0.1115   1.0000
   7.500   1.2937   0.02065   0.01081  -0.0871   0.0711   1.0000
   7.750   1.3045   0.02252   0.01239  -0.0852   0.0201   1.0000
   8.000   1.3235   0.02334   0.01332  -0.0841   0.0171   1.0000
   8.250   1.3426   0.02410   0.01423  -0.0829   0.0162   1.0000
   8.500   1.3601   0.02495   0.01524  -0.0816   0.0154   1.0000
   8.750   1.3756   0.02592   0.01639  -0.0801   0.0147   1.0000
   9.000   1.3881   0.02705   0.01768  -0.0782   0.0140   1.0000
   9.250   1.3956   0.02844   0.01925  -0.0758   0.0132   1.0000
   9.500   1.3945   0.03016   0.02117  -0.0723   0.0126   1.0000
   9.750   1.3961   0.03183   0.02298  -0.0696   0.0122   1.0000
  10.000   1.3988   0.03358   0.02489  -0.0675   0.0120   1.0000
  10.250   1.3994   0.03571   0.02717  -0.0657   0.0117   1.0000
  10.500   1.3982   0.03824   0.02986  -0.0645   0.0116   1.0000
  10.750   1.3953   0.04121   0.03300  -0.0637   0.0114   1.0000
  11.000   1.3909   0.04463   0.03657  -0.0635   0.0112   1.0000
  11.250   1.3853   0.04842   0.04051  -0.0636   0.0111   1.0000
  11.500   1.3787   0.05256   0.04478  -0.0641   0.0110   1.0000
  11.750   1.3715   0.05687   0.04922  -0.0648   0.0109   1.0000
  12.000   1.3639   0.06130   0.05377  -0.0655   0.0108   1.0000
  12.250   1.3566   0.06569   0.05827  -0.0662   0.0107   1.0000
  12.500   1.3499   0.06997   0.06265  -0.0667   0.0105   1.0000
  12.750   1.3440   0.07410   0.06687  -0.0673   0.0103   1.0000
  13.000   1.3392   0.07804   0.07088  -0.0677   0.0101   1.0000
  13.250   1.3357   0.08177   0.07467  -0.0680   0.0098   1.0000
  13.500   1.3335   0.08531   0.07826  -0.0683   0.0096   1.0000
  13.750   1.3332   0.08837   0.08133  -0.0681   0.0093   1.0000
  14.000   1.3380   0.08993   0.08279  -0.0663   0.0089   1.0000
  14.250   1.3459   0.09138   0.08425  -0.0647   0.0088   1.0000
  14.500   1.3494   0.09421   0.08720  -0.0647   0.0087   1.0000
  14.750   1.3532   0.09699   0.09010  -0.0647   0.0085   1.0000
  15.000   1.3573   0.09967   0.09289  -0.0646   0.0084   1.0000
  15.250   1.3614   0.10239   0.09572  -0.0646   0.0083   1.0000
  15.500   1.3651   0.10522   0.09868  -0.0646   0.0082   1.0000
  15.750   1.3676   0.10831   0.10191  -0.0649   0.0082   1.0000
  16.000   1.3689   0.11170   0.10544  -0.0655   0.0081   1.0000
  16.250   1.3692   0.11529   0.10919  -0.0663   0.0080   1.0000
  16.500   1.3685   0.11913   0.11319  -0.0674   0.0080   1.0000
  16.750   1.3668   0.12324   0.11746  -0.0688   0.0080   1.0000
  17.000   1.3641   0.12764   0.12203  -0.0705   0.0079   1.0000
  17.250   1.3602   0.13238   0.12698  -0.0727   0.0079   1.0000
  17.500   1.3552   0.13747   0.13225  -0.0753   0.0079   1.0000
  17.750   1.3494   0.14286   0.13781  -0.0783   0.0078   1.0000
  18.000   1.3429   0.14852   0.14365  -0.0816   0.0077   1.0000
  18.250   1.3359   0.15445   0.14975  -0.0853   0.0077   1.0000
  18.500   1.3282   0.16075   0.15623  -0.0894   0.0076   1.0000
  18.750   1.3206   0.16723   0.16288  -0.0937   0.0076   1.0000
  19.000   1.3122   0.17416   0.16998  -0.0985   0.0076   1.0000
  19.250   1.3037   0.18138   0.17737  -0.1035   0.0075   1.0000
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