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GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il)
Reynolds number: 200,000
Max Cl/Cd: 79.33 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe144-il-200000.txt
Download as CSV file: xf-goe144-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 144 (MVA H.21) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3483   0.10017   0.09678  -0.0280   1.0000   0.0445
  -8.000  -0.3577   0.09858   0.09528  -0.0278   1.0000   0.0446
  -7.750  -0.3639   0.09645   0.09322  -0.0284   1.0000   0.0447
  -7.500  -0.3508   0.09069   0.08746  -0.0242   1.0000   0.0460
  -7.250  -0.3485   0.08844   0.08525  -0.0220   1.0000   0.0469
  -7.000  -0.3509   0.08658   0.08343  -0.0201   1.0000   0.0481
  -6.750  -0.3536   0.08455   0.08145  -0.0191   1.0000   0.0496
  -6.500  -0.3564   0.08240   0.07934  -0.0187   1.0000   0.0512
  -6.250  -0.3577   0.08005   0.07704  -0.0228   1.0000   0.0543
  -6.000  -0.3434   0.07659   0.07351  -0.0339   1.0000   0.0554
  -5.750  -0.3502   0.07249   0.06950  -0.0278   1.0000   0.0567
  -5.500  -0.3464   0.07060   0.06764  -0.0243   1.0000   0.0581
  -5.250  -0.3391   0.06819   0.06525  -0.0240   1.0000   0.0600
  -5.000  -0.2699   0.06159   0.05828  -0.0455   0.9953   0.0673
  -4.750  -0.2461   0.05493   0.05163  -0.0492   0.9906   0.0687
  -4.500  -0.2158   0.05197   0.04866  -0.0515   0.9857   0.0710
  -4.250  -0.1563   0.03752   0.03353  -0.0671   0.9810   0.0569
  -4.000  -0.1154   0.02610   0.02120  -0.0740   0.9769   0.0508
  -3.750  -0.0740   0.02082   0.01481  -0.0777   0.9732   0.0546
  -3.500  -0.0358   0.01844   0.01196  -0.0800   0.9678   0.0575
  -3.250   0.0048   0.01784   0.01127  -0.0825   0.9609   0.0632
  -3.000   0.0462   0.01670   0.00973  -0.0848   0.9550   0.0675
  -2.750   0.0849   0.01553   0.00853  -0.0869   0.9478   0.0752
  -2.500   0.1276   0.01449   0.00740  -0.0896   0.9424   0.0875
  -2.250   0.1674   0.01391   0.00677  -0.0916   0.9340   0.1082
  -2.000   0.2123   0.01388   0.00674  -0.0947   0.9277   0.1241
  -1.750   0.2531   0.01366   0.00642  -0.0968   0.9185   0.1355
  -1.500   0.2914   0.01332   0.00608  -0.0986   0.9071   0.1436
  -1.250   0.3291   0.01289   0.00559  -0.1001   0.8937   0.1516
  -1.000   0.3638   0.01263   0.00526  -0.1010   0.8766   0.1609
  -0.750   0.3953   0.01220   0.00485  -0.1013   0.8557   0.1693
  -0.500   0.4240   0.01183   0.00442  -0.1010   0.8301   0.1792
  -0.250   0.4520   0.01151   0.00404  -0.1006   0.8020   0.1925
   0.000   0.4802   0.01129   0.00375  -0.1002   0.7743   0.2076
   0.250   0.5076   0.01124   0.00356  -0.0997   0.7476   0.2216
   0.500   0.5338   0.01132   0.00348  -0.0990   0.7223   0.2344
   0.750   0.5594   0.01141   0.00346  -0.0982   0.7000   0.2462
   1.000   0.5845   0.01148   0.00348  -0.0975   0.6807   0.2580
   1.250   0.6099   0.01155   0.00353  -0.0969   0.6647   0.2727
   1.500   0.6353   0.01159   0.00357  -0.0962   0.6502   0.2911
   1.750   0.6604   0.01155   0.00361  -0.0956   0.6367   0.3204
   2.000   0.7000   0.01024   0.00365  -0.0980   0.6225   1.0000
   2.250   0.7254   0.01045   0.00374  -0.0973   0.6099   1.0000
   2.500   0.7506   0.01066   0.00383  -0.0966   0.5968   1.0000
   2.750   0.7756   0.01085   0.00394  -0.0958   0.5832   1.0000
   3.000   0.8003   0.01104   0.00406  -0.0950   0.5690   1.0000
   3.250   0.8250   0.01124   0.00421  -0.0942   0.5549   1.0000
   3.500   0.8497   0.01144   0.00437  -0.0935   0.5415   1.0000
   3.750   0.8745   0.01164   0.00454  -0.0927   0.5286   1.0000
   4.000   0.8991   0.01185   0.00472  -0.0919   0.5150   1.0000
   4.250   0.9237   0.01207   0.00494  -0.0912   0.5019   1.0000
   4.500   0.9483   0.01230   0.00516  -0.0904   0.4892   1.0000
   4.750   0.9725   0.01252   0.00537  -0.0896   0.4751   1.0000
   5.000   0.9964   0.01274   0.00560  -0.0887   0.4600   1.0000
   5.250   1.0193   0.01293   0.00581  -0.0876   0.4404   1.0000
   5.500   1.0414   0.01314   0.00598  -0.0864   0.4167   1.0000
   5.750   1.0630   0.01340   0.00617  -0.0851   0.3903   1.0000
   6.000   1.0844   0.01370   0.00642  -0.0839   0.3622   1.0000
   6.250   1.1058   0.01406   0.00674  -0.0827   0.3340   1.0000
   6.500   1.1260   0.01453   0.00709  -0.0813   0.2976   1.0000
   6.750   1.1441   0.01521   0.00755  -0.0798   0.2544   1.0000
   7.000   1.1623   0.01596   0.00810  -0.0782   0.2134   1.0000
   7.250   1.1761   0.01717   0.00883  -0.0762   0.1357   1.0000
   7.500   1.1881   0.01863   0.00990  -0.0739   0.0827   1.0000
   7.750   1.1996   0.02012   0.01103  -0.0714   0.0375   1.0000
   8.000   1.2153   0.02116   0.01213  -0.0693   0.0324   1.0000
   8.250   1.2318   0.02206   0.01322  -0.0674   0.0307   1.0000
   8.500   1.2458   0.02310   0.01442  -0.0652   0.0290   1.0000
   8.750   1.2563   0.02433   0.01579  -0.0626   0.0272   1.0000
   9.000   1.2626   0.02574   0.01734  -0.0594   0.0259   1.0000
   9.250   1.2651   0.02721   0.01892  -0.0557   0.0252   1.0000
   9.500   1.2658   0.02891   0.02070  -0.0520   0.0247   1.0000
   9.750   1.2673   0.03084   0.02271  -0.0486   0.0243   1.0000
  10.000   1.2731   0.03293   0.02484  -0.0460   0.0240   1.0000
  10.250   1.2848   0.03470   0.02669  -0.0441   0.0239   1.0000
  10.500   1.3008   0.03670   0.02877  -0.0426   0.0238   1.0000
  10.750   1.3182   0.03873   0.03093  -0.0414   0.0237   1.0000
  11.000   1.3310   0.04061   0.03298  -0.0398   0.0234   1.0000
  11.250   1.3375   0.04230   0.03490  -0.0377   0.0226   1.0000
  11.500   1.3490   0.04481   0.03762  -0.0362   0.0226   1.0000
  11.750   1.3593   0.04785   0.04090  -0.0348   0.0229   1.0000
  12.000   1.3654   0.05146   0.04478  -0.0332   0.0233   1.0000
  12.250   1.3874   0.05585   0.04937  -0.0331   0.0244   1.0000
  12.500   1.3831   0.05724   0.05097  -0.0305   0.0249   1.0000
  12.750   1.3714   0.05932   0.05339  -0.0280   0.0258   1.0000
  13.000   1.3471   0.06387   0.05846  -0.0264   0.0276   1.0000
  13.250   1.3266   0.06928   0.06424  -0.0262   0.0290   1.0000
  13.500   1.3082   0.07486   0.07008  -0.0270   0.0300   1.0000
  13.750   1.2889   0.08086   0.07631  -0.0285   0.0308   1.0000
  14.000   1.2684   0.08771   0.08335  -0.0307   0.0316   1.0000
  14.750   1.0680   0.10576   0.10221  -0.0397   0.0275   1.0000
  15.000   1.0388   0.11349   0.11015  -0.0451   0.0276   1.0000
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