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GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 431 AIRFOIL (goe431-il)
Reynolds number: 500,000
Max Cl/Cd: 104.68 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe431-il-500000.txt
Download as CSV file: xf-goe431-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 431 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.0642   0.06152   0.05906  -0.1256   0.9422   0.0194
 -11.000  -0.1125   0.04608   0.04346  -0.1349   0.9323   0.0187
 -10.750  -0.1908   0.05943   0.05676  -0.1354   0.9457   0.0180
 -10.500  -0.2131   0.04606   0.04303  -0.1541   0.9279   0.0175
 -10.250  -0.2295   0.03956   0.03627  -0.1616   0.9094   0.0172
 -10.000  -0.2232   0.03482   0.03132  -0.1690   0.8989   0.0175
  -9.750  -0.2150   0.02992   0.02619  -0.1765   0.8890   0.0175
  -9.250  -0.1649   0.02270   0.01845  -0.1902   0.8782   0.0183
  -9.000  -0.1385   0.02086   0.01638  -0.1931   0.8741   0.0189
  -8.750  -0.1107   0.01956   0.01487  -0.1951   0.8708   0.0194
  -8.500  -0.0843   0.01782   0.01297  -0.1972   0.8677   0.0204
  -8.250  -0.0581   0.01696   0.01206  -0.1981   0.8645   0.0214
  -8.000  -0.0309   0.01616   0.01115  -0.1989   0.8612   0.0225
  -7.750  -0.0029   0.01540   0.01025  -0.1996   0.8577   0.0235
  -7.500   0.0256   0.01446   0.00915  -0.2006   0.8543   0.0247
  -7.250   0.0534   0.01372   0.00833  -0.2013   0.8508   0.0265
  -7.000   0.0807   0.01322   0.00774  -0.2015   0.8472   0.0287
  -6.750   0.1089   0.01253   0.00695  -0.2021   0.8436   0.0320
  -6.500   0.1376   0.01213   0.00646  -0.2024   0.8406   0.0361
  -6.250   0.1670   0.01154   0.00577  -0.2030   0.8379   0.0443
  -6.000   0.1948   0.01088   0.00506  -0.2034   0.8351   0.0589
  -5.750   0.2222   0.01026   0.00467  -0.2038   0.8318   0.1141
  -5.500   0.2510   0.01057   0.00494  -0.2036   0.8284   0.1344
  -5.250   0.2800   0.01075   0.00503  -0.2036   0.8252   0.1418
  -5.000   0.3095   0.01105   0.00527  -0.2036   0.8222   0.1481
  -4.750   0.3374   0.01135   0.00549  -0.2034   0.8192   0.1528
  -4.500   0.3646   0.01125   0.00542  -0.2033   0.8160   0.1586
  -4.250   0.3928   0.01139   0.00555  -0.2031   0.8129   0.1633
  -4.000   0.4214   0.01137   0.00544  -0.2031   0.8100   0.1660
  -3.750   0.4505   0.01146   0.00543  -0.2032   0.8071   0.1683
  -3.500   0.4780   0.01123   0.00514  -0.2031   0.8038   0.1698
  -3.250   0.5050   0.01090   0.00481  -0.2029   0.8002   0.1722
  -3.000   0.5328   0.01077   0.00467  -0.2028   0.7965   0.1746
  -2.750   0.5613   0.01071   0.00458  -0.2028   0.7932   0.1773
  -2.500   0.5903   0.01063   0.00444  -0.2029   0.7903   0.1788
  -2.250   0.6170   0.01048   0.00428  -0.2026   0.7867   0.1797
  -2.000   0.6443   0.01033   0.00411  -0.2024   0.7827   0.1804
  -1.750   0.6724   0.01020   0.00394  -0.2023   0.7788   0.1811
  -1.500   0.7013   0.01010   0.00378  -0.2023   0.7753   0.1819
  -1.250   0.7277   0.00998   0.00368  -0.2019   0.7709   0.1827
  -1.000   0.7546   0.00987   0.00356  -0.2016   0.7658   0.1835
  -0.750   0.7826   0.00978   0.00342  -0.2014   0.7607   0.1842
  -0.500   0.8089   0.00968   0.00333  -0.2009   0.7548   0.1851
  -0.250   0.8354   0.00949   0.00316  -0.2005   0.7480   0.1870
   0.000   0.8620   0.00938   0.00306  -0.2001   0.7407   0.1890
   0.250   0.8878   0.00929   0.00298  -0.1995   0.7313   0.1911
   0.500   0.9132   0.00922   0.00293  -0.1988   0.7204   0.1932
   0.750   0.9380   0.00918   0.00287  -0.1980   0.7062   0.1957
   1.000   0.9610   0.00918   0.00280  -0.1968   0.6829   0.1981
   1.250   0.9694   0.00964   0.00281  -0.1925   0.5817   0.1999
   1.500   0.9679   0.01081   0.00338  -0.1867   0.4868   0.2018
   1.750   0.9836   0.01127   0.00369  -0.1844   0.4539   0.2063
   2.000   1.0024   0.01161   0.00394  -0.1826   0.4332   0.2115
   2.250   1.0221   0.01190   0.00416  -0.1811   0.4184   0.2175
   2.500   1.0429   0.01212   0.00437  -0.1797   0.4073   0.2284
   2.750   1.0636   0.01230   0.00459  -0.1783   0.3989   0.2477
   3.000   1.0835   0.01247   0.00483  -0.1768   0.3918   0.2847
   3.250   1.1036   0.01264   0.00508  -0.1753   0.3861   0.3301
   3.500   1.1252   0.01276   0.00535  -0.1742   0.3809   0.3824
   3.750   1.1456   0.01296   0.00567  -0.1728   0.3761   0.4422
   4.000   1.1654   0.01323   0.00600  -0.1713   0.3714   0.4889
   4.250   1.1876   0.01340   0.00626  -0.1702   0.3672   0.5235
   4.500   1.2087   0.01363   0.00654  -0.1689   0.3630   0.5503
   4.750   1.2289   0.01390   0.00685  -0.1675   0.3592   0.5735
   5.000   1.2494   0.01420   0.00717  -0.1662   0.3556   0.5968
   5.250   1.2715   0.01432   0.00744  -0.1652   0.3525   0.6268
   5.500   1.2925   0.01401   0.00772  -0.1639   0.3496   1.0000
   5.750   1.3140   0.01431   0.00801  -0.1628   0.3468   1.0000
   6.000   1.3350   0.01464   0.00832  -0.1617   0.3440   1.0000
   6.250   1.3561   0.01505   0.00869  -0.1606   0.3408   1.0000
   6.500   1.3781   0.01532   0.00902  -0.1596   0.3387   1.0000
   6.750   1.3994   0.01558   0.00933  -0.1585   0.3358   1.0000
   7.000   1.4198   0.01586   0.00964  -0.1573   0.3317   1.0000
   7.250   1.4385   0.01626   0.01002  -0.1558   0.3266   1.0000
   7.500   1.4585   0.01661   0.01040  -0.1546   0.3224   1.0000
   7.750   1.4780   0.01688   0.01074  -0.1532   0.3173   1.0000
   8.000   1.4956   0.01729   0.01114  -0.1517   0.3115   1.0000
   8.250   1.5143   0.01768   0.01158  -0.1503   0.3064   1.0000
   8.500   1.5330   0.01801   0.01197  -0.1489   0.2994   1.0000
   8.750   1.5491   0.01855   0.01248  -0.1472   0.2930   1.0000
   9.000   1.5689   0.01885   0.01288  -0.1461   0.2851   1.0000
   9.250   1.5852   0.01937   0.01341  -0.1445   0.2753   1.0000
   9.500   1.6016   0.01990   0.01394  -0.1430   0.2608   1.0000
   9.750   1.6136   0.02073   0.01464  -0.1409   0.2267   1.0000
  10.000   1.6081   0.02294   0.01634  -0.1369   0.1612   1.0000
  10.250   1.6093   0.02481   0.01800  -0.1338   0.1266   1.0000
  10.500   1.6008   0.02755   0.02027  -0.1299   0.0650   1.0000
  10.750   1.5925   0.03031   0.02279  -0.1261   0.0319   1.0000
  11.000   1.5981   0.03198   0.02449  -0.1239   0.0262   1.0000
  11.250   1.6024   0.03379   0.02635  -0.1216   0.0232   1.0000
  11.500   1.6101   0.03532   0.02797  -0.1198   0.0216   1.0000
  11.750   1.6169   0.03696   0.02968  -0.1180   0.0203   1.0000
  12.000   1.6202   0.03896   0.03176  -0.1160   0.0190   1.0000
  12.250   1.6180   0.04156   0.03446  -0.1138   0.0181   1.0000
  12.500   1.6218   0.04364   0.03665  -0.1121   0.0175   1.0000
  12.750   1.6252   0.04584   0.03895  -0.1106   0.0170   1.0000
  13.000   1.6269   0.04828   0.04150  -0.1091   0.0164   1.0000
  13.250   1.6271   0.05096   0.04428  -0.1077   0.0159   1.0000
  13.500   1.6255   0.05394   0.04735  -0.1064   0.0154   1.0000
  13.750   1.6215   0.05734   0.05086  -0.1053   0.0150   1.0000
  14.000   1.6134   0.06140   0.05503  -0.1044   0.0146   1.0000
  14.250   1.5994   0.06647   0.06023  -0.1038   0.0142   1.0000
  14.500   1.5916   0.07095   0.06484  -0.1036   0.0140   1.0000
  14.750   1.5900   0.07475   0.06876  -0.1037   0.0137   1.0000
  15.000   1.5864   0.07896   0.07310  -0.1041   0.0134   1.0000
  15.250   1.5809   0.08362   0.07787  -0.1047   0.0132   1.0000
  15.500   1.5757   0.08838   0.08276  -0.1056   0.0130   1.0000
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