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GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il)
Reynolds number: 500,000
Max Cl/Cd: 118.07 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe239-il-500000.txt
Download as CSV file: xf-goe239-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 239 (MVA H.31) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2127   0.09229   0.09003  -0.0577   0.9857   0.0332
  -8.750  -0.2087   0.08417   0.08191  -0.0700   0.9753   0.0359
  -8.500  -0.1992   0.07910   0.07684  -0.0734   0.9678   0.0365
  -8.250  -0.1792   0.07746   0.07518  -0.0742   0.9606   0.0371
  -8.000  -0.1623   0.07523   0.07294  -0.0759   0.9507   0.0379
  -7.750  -0.1497   0.07234   0.07002  -0.0785   0.9396   0.0390
  -7.500  -0.1509   0.02529   0.02156  -0.1426   0.9169   0.0348
  -7.250  -0.1233   0.02201   0.01769  -0.1453   0.9111   0.0356
  -7.000  -0.0970   0.01922   0.01446  -0.1470   0.9047   0.0365
  -6.750  -0.0698   0.01823   0.01338  -0.1474   0.8990   0.0376
  -6.500  -0.0421   0.01751   0.01255  -0.1477   0.8933   0.0384
  -6.250  -0.0143   0.01660   0.01149  -0.1480   0.8871   0.0393
  -6.000   0.0141   0.01573   0.01041  -0.1482   0.8813   0.0402
  -5.750   0.0422   0.01506   0.00958  -0.1484   0.8746   0.0413
  -5.500   0.0706   0.01451   0.00887  -0.1484   0.8679   0.0422
  -5.250   0.0991   0.01385   0.00804  -0.1485   0.8615   0.0428
  -5.000   0.1272   0.01266   0.00677  -0.1488   0.8544   0.0440
  -4.750   0.1556   0.01219   0.00623  -0.1488   0.8478   0.0452
  -4.500   0.1840   0.01184   0.00585  -0.1489   0.8394   0.0467
  -4.250   0.2125   0.01150   0.00542  -0.1488   0.8315   0.0482
  -4.000   0.2410   0.01113   0.00499  -0.1488   0.8213   0.0494
  -3.750   0.2695   0.01087   0.00464  -0.1487   0.8111   0.0505
  -3.500   0.2982   0.01029   0.00400  -0.1488   0.7997   0.0529
  -3.250   0.3266   0.01004   0.00371  -0.1487   0.7854   0.0555
  -3.000   0.3547   0.00988   0.00346  -0.1486   0.7679   0.0586
  -2.750   0.3829   0.00962   0.00311  -0.1485   0.7445   0.0624
  -2.500   0.4103   0.00951   0.00288  -0.1482   0.7133   0.0681
  -2.250   0.4370   0.00947   0.00265  -0.1478   0.6753   0.0766
  -2.000   0.4638   0.00948   0.00251  -0.1475   0.6431   0.0902
  -1.750   0.4911   0.00944   0.00238  -0.1473   0.6213   0.1122
  -1.500   0.5189   0.00927   0.00240  -0.1475   0.6056   0.1987
  -1.250   0.5465   0.00936   0.00245  -0.1474   0.5932   0.2282
  -1.000   0.5746   0.00943   0.00249  -0.1473   0.5832   0.2470
  -0.750   0.6023   0.00954   0.00255  -0.1472   0.5748   0.2617
  -0.500   0.6305   0.00961   0.00260  -0.1472   0.5672   0.2758
   0.000   0.6865   0.00979   0.00274  -0.1471   0.5527   0.3020
   0.250   0.7143   0.00989   0.00281  -0.1470   0.5459   0.3140
   0.500   0.7424   0.00997   0.00289  -0.1470   0.5405   0.3275
   0.750   0.7707   0.01002   0.00297  -0.1470   0.5355   0.3419
   1.000   0.7987   0.01011   0.00305  -0.1470   0.5309   0.3557
   1.250   0.8266   0.01024   0.00316  -0.1469   0.5263   0.3706
   1.500   0.8549   0.01026   0.00324  -0.1470   0.5218   0.3872
   1.750   0.8830   0.01030   0.00333  -0.1470   0.5170   0.4047
   2.000   0.9107   0.01038   0.00342  -0.1469   0.5124   0.4224
   2.250   0.9387   0.01044   0.00354  -0.1470   0.5083   0.4432
   2.500   0.9669   0.01040   0.00365  -0.1471   0.5038   0.4780
   2.750   0.9922   0.00977   0.00388  -0.1467   0.4994   0.7951
   3.000   1.0147   0.00968   0.00391  -0.1452   0.4950   1.0000
   3.250   1.0425   0.00980   0.00403  -0.1452   0.4906   1.0000
   3.500   1.0703   0.00990   0.00414  -0.1451   0.4856   1.0000
   3.750   1.0977   0.01005   0.00425  -0.1450   0.4805   1.0000
   4.000   1.1249   0.01022   0.00440  -0.1449   0.4753   1.0000
   4.250   1.1523   0.01030   0.00451  -0.1447   0.4690   1.0000
   4.500   1.1788   0.01047   0.00462  -0.1445   0.4616   1.0000
   4.750   1.2059   0.01054   0.00474  -0.1443   0.4532   1.0000
   5.000   1.2321   0.01072   0.00487  -0.1440   0.4452   1.0000
   5.250   1.2590   0.01081   0.00500  -0.1438   0.4359   1.0000
   5.500   1.2850   0.01097   0.00515  -0.1434   0.4255   1.0000
   5.750   1.3107   0.01115   0.00530  -0.1430   0.4146   1.0000
   6.000   1.3366   0.01132   0.00549  -0.1427   0.4034   1.0000
   6.250   1.3618   0.01155   0.00570  -0.1422   0.3914   1.0000
   6.500   1.3864   0.01182   0.00593  -0.1417   0.3781   1.0000
   6.750   1.4102   0.01213   0.00620  -0.1410   0.3637   1.0000
   7.000   1.4335   0.01249   0.00650  -0.1403   0.3489   1.0000
   7.250   1.4563   0.01287   0.00685  -0.1395   0.3347   1.0000
   7.750   1.5006   0.01371   0.00760  -0.1377   0.3073   1.0000
   8.000   1.5219   0.01417   0.00801  -0.1367   0.2925   1.0000
   8.250   1.5430   0.01462   0.00843  -0.1356   0.2781   1.0000
   8.500   1.5633   0.01511   0.00887  -0.1345   0.2635   1.0000
   8.750   1.5831   0.01561   0.00934  -0.1332   0.2490   1.0000
   9.000   1.6022   0.01613   0.00984  -0.1319   0.2348   1.0000
   9.250   1.6194   0.01674   0.01039  -0.1303   0.2184   1.0000
   9.500   1.6343   0.01743   0.01101  -0.1282   0.1981   1.0000
   9.750   1.6404   0.01849   0.01186  -0.1248   0.1598   1.0000
  10.000   1.6357   0.02026   0.01331  -0.1200   0.1152   1.0000
  10.250   1.6373   0.02173   0.01466  -0.1164   0.0922   1.0000
  10.500   1.6386   0.02328   0.01608  -0.1129   0.0700   1.0000
  10.750   1.6431   0.02470   0.01747  -0.1101   0.0609   1.0000
  11.000   1.6504   0.02598   0.01879  -0.1078   0.0562   1.0000
  11.250   1.6536   0.02763   0.02046  -0.1052   0.0514   1.0000
  11.500   1.6628   0.02887   0.02180  -0.1034   0.0479   1.0000
  11.750   1.6657   0.03068   0.02365  -0.1012   0.0438   1.0000
  12.000   1.6718   0.03229   0.02533  -0.0994   0.0397   1.0000
  12.250   1.6728   0.03440   0.02746  -0.0974   0.0356   1.0000
  12.500   1.6769   0.03632   0.02946  -0.0958   0.0319   1.0000
  12.750   1.6745   0.03892   0.03209  -0.0940   0.0290   1.0000
  13.000   1.6769   0.04118   0.03443  -0.0927   0.0268   1.0000
  13.250   1.6759   0.04387   0.03718  -0.0915   0.0250   1.0000
  13.500   1.6686   0.04736   0.04075  -0.0903   0.0236   1.0000
  13.750   1.6679   0.05030   0.04381  -0.0895   0.0226   1.0000
  14.000   1.6657   0.05353   0.04715  -0.0890   0.0217   1.0000
  14.250   1.6611   0.05719   0.05089  -0.0887   0.0208   1.0000
  14.500   1.6534   0.06139   0.05518  -0.0886   0.0202   1.0000
  14.750   1.6412   0.06633   0.06023  -0.0888   0.0196   1.0000
  15.000   1.6328   0.07080   0.06482  -0.0890   0.0192   1.0000
  15.250   1.6266   0.07499   0.06913  -0.0892   0.0187   1.0000
  15.500   1.6191   0.07938   0.07364  -0.0896   0.0183   1.0000
  15.750   1.6112   0.08388   0.07825  -0.0900   0.0179   1.0000
  16.000   1.6028   0.08848   0.08295  -0.0906   0.0176   1.0000
  16.250   1.5943   0.09311   0.08768  -0.0912   0.0172   1.0000
  16.500   1.5856   0.09784   0.09251  -0.0920   0.0169   1.0000
  16.750   1.5764   0.10271   0.09745  -0.0929   0.0166   1.0000
  17.000   1.5663   0.10771   0.10253  -0.0939   0.0163   1.0000
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