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GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il)
Reynolds number: 500,000
Max Cl/Cd: 114.84 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe124-il-500000.txt
Download as CSV file: xf-goe124-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 124 (MVA H.4) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3177   0.10283   0.10063  -0.0224   1.0000   0.0205
  -8.500  -0.3157   0.09994   0.09777  -0.0264   1.0000   0.0206
  -8.250  -0.3114   0.09626   0.09413  -0.0285   1.0000   0.0206
  -8.000  -0.2982   0.09246   0.09034  -0.0268   1.0000   0.0209
  -7.750  -0.2902   0.08973   0.08764  -0.0272   1.0000   0.0211
  -7.500  -0.2730   0.08637   0.08429  -0.0308   0.9845   0.0214
  -7.250  -0.2530   0.08280   0.08070  -0.0356   0.9655   0.0219
  -7.000  -0.2367   0.07947   0.07734  -0.0395   0.9440   0.0226
  -6.750  -0.2232   0.07632   0.07413  -0.0426   0.9233   0.0234
  -6.500  -0.1920   0.07155   0.06923  -0.0561   0.9021   0.0247
  -6.250  -0.1635   0.06676   0.06431  -0.0647   0.8864   0.0249
  -6.000  -0.1508   0.06242   0.05991  -0.0661   0.8732   0.0251
  -5.750  -0.1364   0.05984   0.05727  -0.0661   0.8603   0.0254
  -5.500  -0.1175   0.05725   0.05459  -0.0676   0.8474   0.0257
  -5.250  -0.0944   0.05444   0.05171  -0.0705   0.8348   0.0263
  -5.000  -0.0679   0.05140   0.04857  -0.0742   0.8229   0.0271
  -4.750  -0.0207   0.04689   0.04380  -0.0833   0.8116   0.0298
  -4.500   0.0211   0.04238   0.03897  -0.0896   0.8004   0.0301
  -4.250   0.0439   0.03782   0.03431  -0.0923   0.7888   0.0307
  -4.000   0.0678   0.03583   0.03223  -0.0934   0.7771   0.0311
  -3.750   0.0944   0.03388   0.03016  -0.0949   0.7663   0.0317
  -3.500   0.1235   0.03185   0.02799  -0.0966   0.7554   0.0328
  -3.250   0.1568   0.02938   0.02530  -0.0987   0.7452   0.0349
  -3.000   0.1991   0.02537   0.02060  -0.1018   0.7361   0.0373
  -2.750   0.2260   0.02342   0.01862  -0.1029   0.7255   0.0380
  -2.500   0.2543   0.02213   0.01724  -0.1037   0.7163   0.0389
  -2.250   0.2839   0.02090   0.01585  -0.1046   0.7083   0.0403
  -2.000   0.3152   0.01984   0.01456  -0.1052   0.7003   0.0433
  -1.750   0.3483   0.01818   0.01245  -0.1061   0.6927   0.0464
  -1.500   0.3773   0.01700   0.01124  -0.1068   0.6847   0.0477
  -1.250   0.4066   0.01621   0.01032  -0.1073   0.6768   0.0499
  -1.000   0.4365   0.01637   0.01031  -0.1072   0.6690   0.0548
  -0.750   0.4670   0.01459   0.00834  -0.1082   0.6619   0.0589
  -0.500   0.4963   0.01404   0.00773  -0.1085   0.6545   0.0628
   0.500   0.6168   0.01155   0.00454  -0.1086   0.6247   0.0458
   0.750   0.6459   0.01107   0.00404  -0.1087   0.6166   0.0444
   1.000   0.6750   0.01068   0.00363  -0.1088   0.6090   0.0443
   1.250   0.7039   0.01044   0.00337  -0.1089   0.6008   0.0446
   1.500   0.7329   0.01027   0.00319  -0.1091   0.5926   0.0450
   1.750   0.7620   0.00998   0.00288  -0.1094   0.5832   0.0471
   2.000   0.7910   0.00983   0.00275  -0.1096   0.5723   0.0485
   2.250   0.8198   0.00977   0.00268  -0.1097   0.5619   0.0504
   2.500   0.8483   0.00977   0.00263  -0.1098   0.5508   0.0535
   2.750   0.8767   0.00978   0.00259  -0.1098   0.5370   0.0585
   3.000   0.8987   0.00807   0.00279  -0.1090   0.5235   1.0000
   3.250   0.9267   0.00822   0.00283  -0.1090   0.5090   1.0000
   3.500   0.9546   0.00839   0.00291  -0.1090   0.4940   1.0000
   3.750   0.9822   0.00858   0.00302  -0.1089   0.4772   1.0000
   4.000   1.0096   0.00880   0.00315  -0.1089   0.4590   1.0000
   4.250   1.0370   0.00903   0.00330  -0.1089   0.4414   1.0000
   4.500   1.0641   0.00928   0.00348  -0.1088   0.4237   1.0000
   4.750   1.0910   0.00955   0.00367  -0.1087   0.4072   1.0000
   5.000   1.1179   0.00982   0.00388  -0.1087   0.3933   1.0000
   5.250   1.1448   0.01010   0.00412  -0.1086   0.3814   1.0000
   5.500   1.1713   0.01039   0.00436  -0.1085   0.3700   1.0000
   5.750   1.1981   0.01064   0.00459  -0.1084   0.3589   1.0000
   6.000   1.2247   0.01090   0.00485  -0.1083   0.3492   1.0000
   6.250   1.2508   0.01121   0.00513  -0.1081   0.3384   1.0000
   6.750   1.3025   0.01185   0.00570  -0.1077   0.3097   1.0000
   7.000   1.3282   0.01217   0.00600  -0.1075   0.2942   1.0000
   7.250   1.3538   0.01249   0.00631  -0.1073   0.2748   1.0000
   7.500   1.3770   0.01307   0.00670  -0.1068   0.2329   1.0000
   7.750   1.3926   0.01458   0.00768  -0.1055   0.1521   1.0000
   8.000   1.4139   0.01536   0.00837  -0.1048   0.1331   1.0000
   8.250   1.4356   0.01602   0.00899  -0.1040   0.1208   1.0000
   8.500   1.4569   0.01669   0.00962  -0.1033   0.1107   1.0000
   8.750   1.4796   0.01716   0.01013  -0.1027   0.1027   1.0000
   9.000   1.5013   0.01772   0.01070  -0.1019   0.0941   1.0000
   9.250   1.5222   0.01832   0.01127  -0.1011   0.0826   1.0000
   9.500   1.5399   0.01919   0.01200  -0.0999   0.0601   1.0000
   9.750   1.5497   0.02071   0.01327  -0.0976   0.0323   1.0000
  10.000   1.5622   0.02186   0.01441  -0.0956   0.0253   1.0000
  10.250   1.5728   0.02304   0.01563  -0.0934   0.0223   1.0000
  10.500   1.5834   0.02403   0.01670  -0.0910   0.0210   1.0000
  10.750   1.5904   0.02511   0.01787  -0.0882   0.0199   1.0000
  11.000   1.5957   0.02644   0.01929  -0.0856   0.0190   1.0000
  11.250   1.5976   0.02817   0.02110  -0.0830   0.0182   1.0000
  11.500   1.5947   0.03047   0.02352  -0.0804   0.0174   1.0000
  11.750   1.6008   0.03215   0.02532  -0.0789   0.0170   1.0000
  12.000   1.6051   0.03411   0.02739  -0.0775   0.0164   1.0000
  12.250   1.6077   0.03633   0.02972  -0.0763   0.0159   1.0000
  12.500   1.6087   0.03882   0.03231  -0.0752   0.0155   1.0000
  12.750   1.6081   0.04157   0.03516  -0.0743   0.0151   1.0000
  13.000   1.6059   0.04459   0.03828  -0.0736   0.0148   1.0000
  13.250   1.6016   0.04793   0.04172  -0.0730   0.0145   1.0000
  13.500   1.5942   0.05167   0.04556  -0.0724   0.0142   1.0000
  13.750   1.5850   0.05569   0.04970  -0.0719   0.0140   1.0000
  14.000   1.5725   0.06006   0.05418  -0.0712   0.0137   1.0000
  14.250   1.5709   0.06332   0.05756  -0.0711   0.0136   1.0000
  14.500   1.5689   0.06673   0.06109  -0.0710   0.0134   1.0000
  14.750   1.5662   0.07028   0.06476  -0.0711   0.0132   1.0000
  15.000   1.5631   0.07394   0.06853  -0.0712   0.0131   1.0000
  15.250   1.5598   0.07770   0.07240  -0.0715   0.0128   1.0000
  15.500   1.5564   0.08154   0.07635  -0.0719   0.0126   1.0000
  15.750   1.5528   0.08546   0.08038  -0.0725   0.0124   1.0000
  16.000   1.5487   0.08950   0.08453  -0.0731   0.0122   1.0000
  16.250   1.5446   0.09365   0.08880  -0.0739   0.0120   1.0000
  16.500   1.5403   0.09790   0.09314  -0.0750   0.0117   1.0000
  16.750   1.5358   0.10216   0.09751  -0.0760   0.0115   1.0000
  17.000   1.5313   0.10643   0.10186  -0.0771   0.0114   1.0000
  17.250   1.5269   0.11069   0.10621  -0.0782   0.0112   1.0000
  17.500   1.5224   0.11493   0.11054  -0.0793   0.0111   1.0000
  17.750   1.5179   0.11911   0.11481  -0.0803   0.0109   1.0000
  18.000   1.5122   0.12338   0.11918  -0.0813   0.0108   1.0000
  18.250   1.5036   0.12816   0.12410  -0.0824   0.0106   1.0000
  18.500   1.4943   0.13381   0.12991  -0.0850   0.0106   1.0000
  18.750   1.4857   0.13974   0.13600  -0.0883   0.0105   1.0000
  19.000   1.4767   0.14587   0.14229  -0.0918   0.0105   1.0000
  19.250   1.4672   0.15220   0.14878  -0.0956   0.0105   1.0000
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