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GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 430 AIRFOIL (goe430-il)
Reynolds number: 200,000
Max Cl/Cd: 83.79 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe430-il-200000.txt
Download as CSV file: xf-goe430-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 430 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3832   0.10426   0.10077  -0.0439   0.9956   0.1047
  -9.000  -0.3520   0.10154   0.09802  -0.0426   0.9946   0.1058
  -8.750  -0.4834   0.04891   0.04485  -0.1024   0.9722   0.0800
  -8.500  -0.4636   0.03824   0.03335  -0.1171   0.9666   0.0799
  -8.250  -0.4358   0.03351   0.02802  -0.1230   0.9613   0.0807
  -8.000  -0.4013   0.03052   0.02482  -0.1271   0.9584   0.0822
  -7.750  -0.3622   0.02867   0.02277  -0.1308   0.9562   0.0835
  -7.500  -0.3288   0.02713   0.02102  -0.1332   0.9525   0.0847
  -7.250  -0.2987   0.02580   0.01949  -0.1347   0.9472   0.0861
  -7.000  -0.2601   0.02457   0.01802  -0.1376   0.9440   0.0882
  -6.750  -0.2174   0.02331   0.01650  -0.1410   0.9417   0.0904
  -6.500  -0.1723   0.02205   0.01498  -0.1448   0.9400   0.0921
  -6.250  -0.1459   0.02107   0.01399  -0.1449   0.9324   0.0941
  -6.000  -0.1039   0.02030   0.01320  -0.1478   0.9289   0.0970
  -5.750  -0.0598   0.01956   0.01237  -0.1509   0.9264   0.1011
  -5.500  -0.0167   0.01868   0.01139  -0.1538   0.9242   0.1054
  -5.250   0.0101   0.01824   0.01099  -0.1536   0.9160   0.1093
  -5.000   0.0480   0.01766   0.01034  -0.1553   0.9116   0.1158
  -4.750   0.0869   0.01699   0.00971  -0.1572   0.9084   0.1245
  -4.500   0.1144   0.01663   0.00935  -0.1571   0.9006   0.1364
  -4.250   0.1475   0.01614   0.00889  -0.1580   0.8952   0.1541
  -4.000   0.1825   0.01564   0.00838  -0.1592   0.8915   0.1714
  -3.750   0.2089   0.01541   0.00815  -0.1588   0.8831   0.1836
  -3.500   0.2405   0.01513   0.00782  -0.1593   0.8774   0.1955
  -3.250   0.2726   0.01478   0.00752  -0.1598   0.8727   0.2067
  -3.000   0.2988   0.01462   0.00737  -0.1593   0.8632   0.2165
  -2.750   0.3306   0.01434   0.00705  -0.1596   0.8578   0.2276
  -2.500   0.3574   0.01418   0.00696  -0.1592   0.8484   0.2389
  -2.250   0.3880   0.01390   0.00668  -0.1593   0.8418   0.2520
  -2.000   0.4155   0.01375   0.00657  -0.1590   0.8325   0.2674
  -1.750   0.4457   0.01349   0.00634  -0.1591   0.8253   0.2876
  -1.500   0.4735   0.01331   0.00620  -0.1589   0.8156   0.3123
  -1.250   0.5037   0.01297   0.00596  -0.1590   0.8081   0.3415
  -1.000   0.5312   0.01281   0.00589  -0.1587   0.7976   0.3705
  -0.750   0.5610   0.01262   0.00572  -0.1587   0.7895   0.3997
  -0.500   0.5885   0.01251   0.00569  -0.1583   0.7778   0.4255
  -0.250   0.6165   0.01243   0.00562  -0.1580   0.7662   0.4517
   0.000   0.6451   0.01232   0.00552  -0.1577   0.7551   0.4757
   0.250   0.6732   0.01224   0.00544  -0.1574   0.7428   0.5010
   0.500   0.7004   0.01220   0.00544  -0.1569   0.7292   0.5258
   0.750   0.7278   0.01218   0.00545  -0.1565   0.7158   0.5521
   1.000   0.7552   0.01221   0.00548  -0.1560   0.7033   0.5783
   1.250   0.7829   0.01228   0.00553  -0.1556   0.6913   0.6060
   1.500   0.8095   0.01237   0.00563  -0.1551   0.6779   0.6310
   1.750   0.8360   0.01248   0.00574  -0.1545   0.6646   0.6554
   2.000   0.8626   0.01259   0.00584  -0.1540   0.6518   0.6785
   2.250   0.8891   0.01269   0.00592  -0.1535   0.6400   0.7025
   2.500   0.9151   0.01277   0.00601  -0.1529   0.6282   0.7285
   2.750   0.9404   0.01283   0.00616  -0.1522   0.6168   0.7575
   3.000   0.9647   0.01285   0.00624  -0.1512   0.6062   0.7930
   3.250   0.9837   0.01268   0.00625  -0.1488   0.5953   0.8749
   3.500   1.0112   0.01277   0.00634  -0.1487   0.5836   1.0000
   3.750   1.0395   0.01302   0.00647  -0.1488   0.5732   1.0000
   4.000   1.0669   0.01325   0.00665  -0.1487   0.5633   1.0000
   4.250   1.0945   0.01350   0.00686  -0.1487   0.5547   1.0000
   4.500   1.1214   0.01373   0.00705  -0.1485   0.5454   1.0000
   4.750   1.1476   0.01396   0.00726  -0.1481   0.5353   1.0000
   5.000   1.1741   0.01422   0.00744  -0.1478   0.5260   1.0000
   5.250   1.1993   0.01443   0.00769  -0.1472   0.5155   1.0000
   5.500   1.2246   0.01468   0.00791  -0.1467   0.5051   1.0000
   5.750   1.2496   0.01494   0.00814  -0.1461   0.4948   1.0000
   6.000   1.2745   0.01521   0.00845  -0.1455   0.4851   1.0000
   6.250   1.2990   0.01551   0.00870  -0.1448   0.4750   1.0000
   6.500   1.3222   0.01580   0.00901  -0.1439   0.4625   1.0000
   6.750   1.3448   0.01611   0.00934  -0.1429   0.4493   1.0000
   7.000   1.3669   0.01646   0.00969  -0.1418   0.4358   1.0000
   7.250   1.3878   0.01684   0.01006  -0.1406   0.4206   1.0000
   7.500   1.4076   0.01724   0.01047  -0.1391   0.4038   1.0000
   7.750   1.4258   0.01767   0.01090  -0.1374   0.3836   1.0000
   8.000   1.4417   0.01818   0.01137  -0.1353   0.3579   1.0000
   8.250   1.4541   0.01881   0.01190  -0.1328   0.3215   1.0000
   8.500   1.4594   0.01973   0.01260  -0.1291   0.2874   1.0000
   8.750   1.4637   0.02084   0.01351  -0.1255   0.2659   1.0000
   9.000   1.4701   0.02199   0.01454  -0.1224   0.2504   1.0000
   9.250   1.4772   0.02318   0.01564  -0.1196   0.2381   1.0000
   9.500   1.4878   0.02422   0.01667  -0.1173   0.2269   1.0000
   9.750   1.4971   0.02536   0.01781  -0.1150   0.2170   1.0000
  10.000   1.5057   0.02658   0.01899  -0.1126   0.2073   1.0000
  10.250   1.5171   0.02762   0.02010  -0.1107   0.1975   1.0000
  10.500   1.5243   0.02897   0.02141  -0.1085   0.1885   1.0000
  10.750   1.5360   0.02999   0.02255  -0.1068   0.1785   1.0000
  11.000   1.5449   0.03127   0.02388  -0.1049   0.1700   1.0000
  11.250   1.5538   0.03257   0.02522  -0.1032   0.1609   1.0000
  11.500   1.5637   0.03384   0.02656  -0.1016   0.1517   1.0000
  11.750   1.5699   0.03543   0.02814  -0.0999   0.1439   1.0000
  12.000   1.5794   0.03681   0.02961  -0.0984   0.1353   1.0000
  12.250   1.5856   0.03850   0.03134  -0.0969   0.1270   1.0000
  12.500   1.5899   0.04041   0.03326  -0.0954   0.1189   1.0000
  12.750   1.5948   0.04233   0.03523  -0.0940   0.1098   1.0000
  13.000   1.5956   0.04470   0.03760  -0.0926   0.1000   1.0000
  13.250   1.5930   0.04748   0.04038  -0.0912   0.0902   1.0000
  13.500   1.5876   0.05068   0.04357  -0.0899   0.0801   1.0000
  13.750   1.5851   0.05374   0.04667  -0.0888   0.0669   1.0000
  14.250   1.5755   0.06066   0.05351  -0.0873   0.0447   1.0000
  14.500   1.5690   0.06450   0.05738  -0.0868   0.0411   1.0000
  14.750   1.5601   0.06874   0.06166  -0.0865   0.0389   1.0000
  15.000   1.5533   0.07282   0.06585  -0.0863   0.0373   1.0000
  15.250   1.5462   0.07703   0.07018  -0.0864   0.0360   1.0000
  15.500   1.5381   0.08147   0.07472  -0.0866   0.0349   1.0000
  15.750   1.5284   0.08619   0.07953  -0.0871   0.0341   1.0000
  16.000   1.5172   0.09119   0.08461  -0.0877   0.0333   1.0000
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