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GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 431 AIRFOIL (goe431-il)
Reynolds number: 200,000
Max Cl/Cd: 72.45 at α=1.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe431-il-200000-n5.txt
Download as CSV file: xf-goe431-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.0612   0.09137   0.08748  -0.1123   0.9293   0.0181
 -10.250  -0.0567   0.08513   0.08123  -0.1171   0.9248   0.0185
  -9.750  -0.1377   0.05511   0.05093  -0.1405   0.9038   0.0174
  -9.500  -0.1541   0.04979   0.04548  -0.1444   0.8928   0.0172
  -9.250  -0.1603   0.04459   0.04012  -0.1504   0.8840   0.0174
  -9.000  -0.1534   0.03959   0.03491  -0.1580   0.8775   0.0177
  -8.750  -0.1374   0.03495   0.03004  -0.1659   0.8724   0.0182
  -8.500  -0.1161   0.03137   0.02626  -0.1721   0.8675   0.0186
  -8.250  -0.0870   0.02813   0.02273  -0.1785   0.8641   0.0194
  -8.000  -0.0546   0.02553   0.01994  -0.1840   0.8617   0.0202
  -7.750  -0.0208   0.02334   0.01758  -0.1891   0.8597   0.0217
  -7.500   0.0059   0.02203   0.01612  -0.1912   0.8564   0.0235
  -7.250   0.0345   0.02094   0.01485  -0.1930   0.8534   0.0255
  -7.000   0.0647   0.01972   0.01349  -0.1952   0.8508   0.0280
  -6.750   0.0953   0.01879   0.01235  -0.1969   0.8486   0.0316
  -6.500   0.1265   0.01774   0.01115  -0.1987   0.8468   0.0378
  -6.250   0.1585   0.01676   0.00997  -0.2005   0.8449   0.0470
  -6.000   0.1844   0.01599   0.00906  -0.2008   0.8411   0.0588
  -5.750   0.2122   0.01519   0.00828  -0.2015   0.8373   0.0825
  -5.500   0.2416   0.01538   0.00853  -0.2017   0.8337   0.1256
  -5.250   0.2724   0.01568   0.00866  -0.2019   0.8307   0.1412
  -5.000   0.3004   0.01586   0.00863  -0.2018   0.8273   0.1504
  -4.750   0.3257   0.01594   0.00870  -0.2012   0.8230   0.1549
  -4.500   0.3538   0.01595   0.00861  -0.2012   0.8194   0.1603
  -4.250   0.3837   0.01585   0.00827  -0.2015   0.8162   0.1642
  -4.000   0.4132   0.01563   0.00798  -0.2018   0.8131   0.1678
  -3.750   0.4372   0.01561   0.00798  -0.2010   0.8082   0.1712
  -3.500   0.4646   0.01548   0.00777  -0.2008   0.8039   0.1743
  -3.250   0.4942   0.01529   0.00745  -0.2010   0.8002   0.1769
  -3.000   0.5228   0.01509   0.00713  -0.2011   0.7968   0.1782
  -2.750   0.5477   0.01496   0.00693  -0.2005   0.7924   0.1790
  -2.500   0.5748   0.01479   0.00669  -0.2002   0.7885   0.1797
  -2.250   0.6037   0.01461   0.00642  -0.2003   0.7849   0.1805
  -2.000   0.6324   0.01445   0.00618  -0.2003   0.7812   0.1813
  -1.750   0.6564   0.01432   0.00607  -0.1995   0.7759   0.1823
  -1.500   0.6834   0.01415   0.00590  -0.1993   0.7712   0.1834
  -1.250   0.7133   0.01396   0.00567  -0.1995   0.7668   0.1847
  -1.000   0.7364   0.01391   0.00566  -0.1985   0.7604   0.1862
  -0.750   0.7629   0.01381   0.00556  -0.1981   0.7548   0.1882
  -0.500   0.7907   0.01369   0.00543  -0.1979   0.7493   0.1903
  -0.250   0.8144   0.01365   0.00541  -0.1970   0.7413   0.1923
   0.000   0.8418   0.01353   0.00527  -0.1967   0.7341   0.1943
   0.250   0.8652   0.01350   0.00527  -0.1957   0.7250   0.1962
   0.500   0.8899   0.01343   0.00521  -0.1949   0.7148   0.1984
   0.750   0.9140   0.01335   0.00516  -0.1940   0.7013   0.2012
   1.000   0.9370   0.01331   0.00513  -0.1929   0.6824   0.2044
   1.250   0.9599   0.01325   0.00498  -0.1916   0.6439   0.2084
   1.500   0.9665   0.01383   0.00478  -0.1869   0.5278   0.2117
   1.750   0.9762   0.01447   0.00516  -0.1834   0.4882   0.2158
   2.000   0.9915   0.01492   0.00550  -0.1810   0.4644   0.2217
   2.250   1.0086   0.01531   0.00580  -0.1790   0.4474   0.2296
   2.500   1.0260   0.01563   0.00610  -0.1771   0.4343   0.2410
   2.750   1.0438   0.01595   0.00641  -0.1752   0.4236   0.2576
   3.000   1.0634   0.01622   0.00673  -0.1737   0.4145   0.2796
   3.500   1.1039   0.01679   0.00740  -0.1711   0.4002   0.3393
   3.750   1.1242   0.01709   0.00779  -0.1698   0.3945   0.3779
   4.000   1.1462   0.01735   0.00818  -0.1689   0.3895   0.4256
   4.250   1.1680   0.01763   0.00856  -0.1679   0.3847   0.4718
   4.500   1.1892   0.01796   0.00895  -0.1667   0.3805   0.5089
   4.750   1.2104   0.01833   0.00933  -0.1656   0.3768   0.5395
   5.000   1.2331   0.01859   0.00968  -0.1648   0.3731   0.5681
   5.250   1.2553   0.01886   0.01005  -0.1639   0.3694   0.5989
   5.750   1.2946   0.01907   0.01074  -0.1610   0.3620   1.0000
   6.000   1.3166   0.01944   0.01113  -0.1601   0.3582   1.0000
   6.250   1.3382   0.01980   0.01154  -0.1592   0.3542   1.0000
   6.500   1.3594   0.02020   0.01196  -0.1582   0.3504   1.0000
   6.750   1.3803   0.02065   0.01240  -0.1571   0.3468   1.0000
   7.000   1.4022   0.02109   0.01284  -0.1563   0.3438   1.0000
   7.250   1.4244   0.02146   0.01332  -0.1554   0.3411   1.0000
   7.500   1.4461   0.02186   0.01380  -0.1546   0.3383   1.0000
   7.750   1.4666   0.02229   0.01430  -0.1535   0.3348   1.0000
   8.000   1.4865   0.02277   0.01481  -0.1524   0.3310   1.0000
   8.250   1.5069   0.02327   0.01535  -0.1514   0.3274   1.0000
   8.500   1.5248   0.02372   0.01595  -0.1499   0.3227   1.0000
   8.750   1.5405   0.02426   0.01656  -0.1482   0.3167   1.0000
   9.000   1.5545   0.02488   0.01722  -0.1463   0.3095   1.0000
   9.250   1.5669   0.02551   0.01795  -0.1442   0.3006   1.0000
   9.500   1.5794   0.02620   0.01872  -0.1423   0.2916   1.0000
   9.750   1.5894   0.02703   0.01959  -0.1400   0.2803   1.0000
  10.000   1.6001   0.02786   0.02050  -0.1379   0.2659   1.0000
  10.250   1.6114   0.02874   0.02145  -0.1360   0.2452   1.0000
  10.500   1.6133   0.03027   0.02280  -0.1332   0.2029   1.0000
  10.750   1.6068   0.03269   0.02489  -0.1299   0.1638   1.0000
  11.000   1.6055   0.03494   0.02700  -0.1271   0.1400   1.0000
  11.250   1.6049   0.03720   0.02916  -0.1247   0.1132   1.0000
  11.500   1.5956   0.04030   0.03201  -0.1217   0.0705   1.0000
  11.750   1.5799   0.04415   0.03561  -0.1186   0.0392   1.0000
  12.000   1.5750   0.04712   0.03860  -0.1164   0.0295   1.0000
  12.250   1.5742   0.04979   0.04136  -0.1147   0.0251   1.0000
  12.500   1.5723   0.05268   0.04433  -0.1131   0.0221   1.0000
  12.750   1.5722   0.05546   0.04724  -0.1117   0.0203   1.0000
  13.000   1.5716   0.05840   0.05032  -0.1106   0.0189   1.0000
  13.250   1.5688   0.06171   0.05377  -0.1095   0.0178   1.0000
  13.500   1.5636   0.06547   0.05766  -0.1087   0.0170   1.0000
  13.750   1.5552   0.06983   0.06218  -0.1082   0.0163   1.0000
  14.000   1.5508   0.07383   0.06635  -0.1080   0.0158   1.0000
  14.250   1.5448   0.07822   0.07092  -0.1081   0.0153   1.0000
  14.500   1.5379   0.08296   0.07583  -0.1086   0.0148   1.0000
  14.750   1.5302   0.08802   0.08105  -0.1094   0.0143   1.0000
  15.000   1.5221   0.09330   0.08650  -0.1105   0.0139   1.0000
  15.250   1.5138   0.09873   0.09208  -0.1119   0.0135   1.0000
  15.500   1.5052   0.10429   0.09777  -0.1135   0.0132   1.0000
  15.750   1.4965   0.10992   0.10353  -0.1153   0.0129   1.0000
  16.000   1.4876   0.11556   0.10928  -0.1172   0.0126   1.0000
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