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GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il)
Reynolds number: 200,000
Max Cl/Cd: 66.71 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe228-il-200000-n5.txt
Download as CSV file: xf-goe228-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 228 (MVA H.38) 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3018   0.05845   0.05398  -0.1329   0.9197   0.0341
 -12.000  -0.3363   0.04964   0.04485  -0.1414   0.9084   0.0341
 -11.750  -0.3517   0.04428   0.03927  -0.1467   0.8969   0.0343
 -11.500  -0.3486   0.04150   0.03640  -0.1491   0.8895   0.0347
 -11.250  -0.3436   0.03902   0.03384  -0.1518   0.8802   0.0351
 -11.000  -0.3300   0.03632   0.03097  -0.1564   0.8736   0.0357
 -10.750  -0.3142   0.03381   0.02829  -0.1610   0.8650   0.0363
 -10.500  -0.2940   0.03159   0.02581  -0.1647   0.8591   0.0371
 -10.250  -0.2737   0.02971   0.02368  -0.1671   0.8530   0.0379
 -10.000  -0.2517   0.02805   0.02176  -0.1690   0.8468   0.0387
  -9.750  -0.2267   0.02658   0.02000  -0.1706   0.8420   0.0395
  -9.500  -0.2019   0.02563   0.01904  -0.1714   0.8367   0.0403
  -9.250  -0.1767   0.02481   0.01816  -0.1721   0.8307   0.0412
  -9.000  -0.1498   0.02391   0.01714  -0.1731   0.8256   0.0421
  -8.750  -0.1225   0.02301   0.01610  -0.1739   0.8208   0.0431
  -8.500  -0.0965   0.02221   0.01517  -0.1744   0.8144   0.0440
  -8.250  -0.0687   0.02144   0.01422  -0.1751   0.8088   0.0452
  -8.000  -0.0401   0.02073   0.01348  -0.1759   0.8041   0.0464
  -7.750  -0.0134   0.02020   0.01293  -0.1764   0.7972   0.0476
  -7.500   0.0150   0.01962   0.01226  -0.1770   0.7911   0.0490
  -7.250   0.0445   0.01903   0.01156  -0.1777   0.7859   0.0505
  -7.000   0.0719   0.01852   0.01099  -0.1781   0.7786   0.0520
  -6.750   0.1010   0.01803   0.01046  -0.1787   0.7721   0.0538
  -6.500   0.1303   0.01762   0.00999  -0.1793   0.7657   0.0564
  -6.250   0.1588   0.01722   0.00952  -0.1798   0.7579   0.0593
  -6.000   0.1889   0.01678   0.00902  -0.1805   0.7513   0.0624
  -5.750   0.2173   0.01645   0.00863  -0.1809   0.7427   0.0666
  -5.500   0.2472   0.01603   0.00815  -0.1816   0.7348   0.0715
  -5.250   0.2760   0.01574   0.00778  -0.1820   0.7257   0.0779
  -5.000   0.3059   0.01536   0.00734  -0.1827   0.7169   0.0857
  -4.750   0.3348   0.01504   0.00700  -0.1832   0.7065   0.0944
  -4.500   0.3643   0.01475   0.00666  -0.1837   0.6964   0.1057
  -4.250   0.3934   0.01446   0.00637  -0.1842   0.6850   0.1250
  -4.000   0.4225   0.01416   0.00610  -0.1847   0.6735   0.1576
  -3.750   0.4517   0.01387   0.00593  -0.1853   0.6618   0.2063
  -3.500   0.4800   0.01381   0.00590  -0.1855   0.6495   0.2537
  -3.250   0.5079   0.01386   0.00588  -0.1855   0.6370   0.2798
  -3.000   0.5356   0.01394   0.00584  -0.1855   0.6251   0.2956
  -2.750   0.5630   0.01403   0.00580  -0.1853   0.6136   0.3067
  -2.500   0.5904   0.01411   0.00580  -0.1852   0.6019   0.3179
  -2.250   0.6176   0.01423   0.00579  -0.1851   0.5914   0.3292
  -2.000   0.6445   0.01434   0.00581  -0.1849   0.5809   0.3375
  -1.750   0.6715   0.01445   0.00583  -0.1848   0.5708   0.3453
  -1.250   0.7250   0.01469   0.00592  -0.1845   0.5525   0.3628
  -1.000   0.7515   0.01484   0.00598  -0.1843   0.5444   0.3725
  -0.750   0.7783   0.01496   0.00607  -0.1842   0.5364   0.3827
  -0.500   0.8045   0.01510   0.00614  -0.1839   0.5285   0.3911
  -0.250   0.8308   0.01523   0.00624  -0.1838   0.5212   0.3992
   0.250   0.8828   0.01553   0.00644  -0.1833   0.5071   0.4131
   0.500   0.9091   0.01565   0.00656  -0.1831   0.5004   0.4206
   0.750   0.9349   0.01582   0.00669  -0.1828   0.4942   0.4286
   1.000   0.9606   0.01600   0.00685  -0.1826   0.4887   0.4383
   1.250   0.9865   0.01614   0.00703  -0.1824   0.4828   0.4490
   1.500   1.0117   0.01633   0.00721  -0.1820   0.4771   0.4612
   1.750   1.0365   0.01655   0.00742  -0.1816   0.4720   0.4744
   2.000   1.0616   0.01672   0.00765  -0.1813   0.4663   0.4899
   2.250   1.0858   0.01695   0.00789  -0.1807   0.4604   0.5079
   2.500   1.1094   0.01722   0.00814  -0.1801   0.4550   0.5276
   2.750   1.1335   0.01743   0.00840  -0.1796   0.4492   0.5471
   3.000   1.1568   0.01768   0.00866  -0.1789   0.4437   0.5648
   3.250   1.1796   0.01798   0.00892  -0.1782   0.4390   0.5808
   3.500   1.2030   0.01823   0.00920  -0.1776   0.4344   0.5958
   3.750   1.2259   0.01849   0.00950  -0.1769   0.4297   0.6105
   4.000   1.2470   0.01877   0.00979  -0.1759   0.4251   0.6247
   4.250   1.2673   0.01908   0.01008  -0.1747   0.4211   0.6380
   4.500   1.2887   0.01934   0.01041  -0.1737   0.4169   0.6510
   4.750   1.3101   0.01964   0.01075  -0.1729   0.4128   0.6639
   5.000   1.3312   0.01996   0.01111  -0.1720   0.4089   0.6772
   5.250   1.3517   0.02032   0.01147  -0.1709   0.4052   0.6913
   5.500   1.3726   0.02065   0.01186  -0.1700   0.4014   0.7070
   5.750   1.3930   0.02098   0.01227  -0.1691   0.3973   0.7249
   6.000   1.4127   0.02132   0.01269  -0.1680   0.3935   0.7474
   6.250   1.4313   0.02162   0.01311  -0.1666   0.3903   0.7873
   6.500   1.4440   0.02177   0.01340  -0.1641   0.3877   1.0000
   6.750   1.4648   0.02222   0.01387  -0.1634   0.3849   1.0000
   7.000   1.4851   0.02268   0.01439  -0.1626   0.3819   1.0000
   7.250   1.5049   0.02318   0.01491  -0.1617   0.3789   1.0000
   7.500   1.5240   0.02370   0.01545  -0.1608   0.3761   1.0000
   7.750   1.5430   0.02424   0.01600  -0.1598   0.3735   1.0000
   8.000   1.5619   0.02479   0.01655  -0.1589   0.3711   1.0000
   8.250   1.5808   0.02536   0.01714  -0.1580   0.3688   1.0000
   8.500   1.5984   0.02596   0.01783  -0.1569   0.3658   1.0000
   8.750   1.6152   0.02661   0.01855  -0.1558   0.3627   1.0000
   9.000   1.6319   0.02727   0.01926  -0.1547   0.3598   1.0000
   9.250   1.6487   0.02794   0.01997  -0.1536   0.3574   1.0000
   9.500   1.6653   0.02863   0.02068  -0.1525   0.3550   1.0000
   9.750   1.6820   0.02933   0.02141  -0.1515   0.3527   1.0000
  10.000   1.6967   0.03015   0.02235  -0.1503   0.3499   1.0000
  10.250   1.7110   0.03099   0.02330  -0.1491   0.3471   1.0000
  10.500   1.7248   0.03187   0.02427  -0.1478   0.3443   1.0000
  10.750   1.7383   0.03277   0.02524  -0.1466   0.3416   1.0000
  11.000   1.7517   0.03369   0.02619  -0.1453   0.3389   1.0000
  11.250   1.7656   0.03458   0.02710  -0.1442   0.3363   1.0000
  11.500   1.7753   0.03578   0.02847  -0.1427   0.3331   1.0000
  11.750   1.7837   0.03708   0.02991  -0.1412   0.3290   1.0000
  12.000   1.7902   0.03849   0.03138  -0.1396   0.3241   1.0000
  12.250   1.7975   0.03985   0.03274  -0.1380   0.3196   1.0000
  12.500   1.8018   0.04160   0.03467  -0.1365   0.3144   1.0000
  12.750   1.8052   0.04344   0.03661  -0.1350   0.3087   1.0000
  13.000   1.8088   0.04528   0.03846  -0.1335   0.3034   1.0000
  13.250   1.8106   0.04749   0.04084  -0.1321   0.2971   1.0000
  13.500   1.8114   0.04979   0.04323  -0.1308   0.2907   1.0000
  13.750   1.8111   0.05228   0.04582  -0.1295   0.2842   1.0000
  14.000   1.8073   0.05525   0.04887  -0.1283   0.2754   1.0000
  14.250   1.8025   0.05844   0.05217  -0.1272   0.2659   1.0000
  14.500   1.7943   0.06211   0.05591  -0.1261   0.2546   1.0000
  14.750   1.7822   0.06633   0.06018  -0.1252   0.2402   1.0000
  15.000   1.7634   0.07149   0.06534  -0.1243   0.2216   1.0000
  15.250   1.7355   0.07794   0.07175  -0.1236   0.2030   1.0000
  15.500   1.7067   0.08469   0.07848  -0.1232   0.1908   1.0000
  15.750   1.6816   0.09112   0.08493  -0.1231   0.1832   1.0000
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