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GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 431 AIRFOIL (goe431-il)
Reynolds number: 50,000
Max Cl/Cd: 20.19 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe431-il-50000.txt
Download as CSV file: xf-goe431-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3577   0.12844   0.12260  -0.0130   1.0000   0.1818
  -7.250  -0.3752   0.12852   0.12277  -0.0120   1.0000   0.1837
  -7.000  -0.3981   0.12904   0.12339  -0.0105   1.0000   0.1844
  -6.750  -0.3859   0.12358   0.11795  -0.0095   1.0000   0.1865
  -6.500  -0.3767   0.11973   0.11409  -0.0080   1.0000   0.1899
  -6.250  -0.3809   0.11765   0.11206  -0.0063   1.0000   0.1930
  -6.000  -0.3915   0.11622   0.11069  -0.0046   1.0000   0.1960
  -5.750  -0.4061   0.11535   0.10989  -0.0045   1.0000   0.1990
  -5.500  -0.4187   0.11467   0.10928  -0.0087   1.0000   0.2006
  -5.250  -0.4078   0.10931   0.10394  -0.0038   1.0000   0.2039
  -5.000  -0.4037   0.10656   0.10121  -0.0024   1.0000   0.2103
  -4.750  -0.4060   0.10533   0.10000  -0.0112   1.0000   0.2166
  -4.500  -0.4012   0.10084   0.09555  -0.0051   1.0000   0.2203
  -4.250  -0.3950   0.09798   0.09269  -0.0049   1.0000   0.2275
  -4.000  -0.3842   0.09457   0.08928  -0.0116   1.0000   0.2343
  -3.750  -0.3775   0.09174   0.08645  -0.0089   1.0000   0.2450
  -3.500  -0.3671   0.08833   0.08305  -0.0101   1.0000   0.2551
  -3.250  -0.3504   0.08486   0.07955  -0.0142   1.0000   0.2688
  -3.000  -0.3364   0.08175   0.07642  -0.0152   1.0000   0.2859
  -2.750  -0.3220   0.07879   0.07344  -0.0159   1.0000   0.3062
  -2.500  -0.3026   0.07568   0.07028  -0.0185   1.0000   0.3331
  -2.000  -0.2662   0.07091   0.06539  -0.0205   1.0000   0.4097
  -1.250  -0.1153   0.05784   0.05139  -0.0526   1.0000   0.4262
  -1.000  -0.0956   0.05597   0.04945  -0.0529   1.0000   0.4364
  -0.750  -0.0520   0.05435   0.04755  -0.0606   1.0000   0.4368
  -0.500   0.0005   0.05299   0.04580  -0.0712   1.0000   0.4230
  -0.250   0.0333   0.05236   0.04499  -0.0760   1.0000   0.4187
   0.000   0.1453   0.05275   0.04471  -0.0964   0.9732   0.4051
   0.250   0.2344   0.05277   0.04429  -0.1099   0.9398   0.4023
   0.500   0.3076   0.05249   0.04362  -0.1200   0.9152   0.3985
   0.750   0.3623   0.05222   0.04312  -0.1261   0.8899   0.3992
   1.000   0.4236   0.05207   0.04275  -0.1324   0.8693   0.4050
   1.250   0.4713   0.05178   0.04223  -0.1367   0.8443   0.4095
   1.500   0.5255   0.05133   0.04168  -0.1410   0.8243   0.4144
   1.750   0.5821   0.05074   0.04094  -0.1455   0.8060   0.4225
   2.000   0.6165   0.05051   0.04062  -0.1468   0.7806   0.4301
   2.250   0.6627   0.04996   0.03999  -0.1491   0.7626   0.4451
   2.500   0.7058   0.04936   0.03937  -0.1508   0.7459   0.4635
   2.750   0.7466   0.04872   0.03872  -0.1522   0.7299   0.4859
   3.000   0.7835   0.04816   0.03817  -0.1530   0.7145   0.5145
   3.250   0.8163   0.04771   0.03778  -0.1533   0.6997   0.5589
   3.500   0.8436   0.04732   0.03764  -0.1530   0.6856   0.6334
   3.750   0.8592   0.04663   0.03762  -0.1513   0.6721   1.0000
   4.000   0.8884   0.04759   0.03818  -0.1525   0.6595   1.0000
   4.250   0.9382   0.04646   0.03685  -0.1543   0.6540   1.0000
   4.500   0.9492   0.04828   0.03859  -0.1531   0.6410   1.0000
   4.750   0.9579   0.05051   0.04076  -0.1520   0.6295   1.0000
   5.000   0.9989   0.04993   0.04011  -0.1528   0.6248   1.0000
   5.250   0.9876   0.05440   0.04458  -0.1511   0.6134   1.0000
   5.500   1.0283   0.05384   0.04402  -0.1517   0.6094   1.0000
   5.750   1.0013   0.06007   0.05027  -0.1496   0.5983   1.0000
   6.000   1.0399   0.05979   0.04999  -0.1501   0.5944   1.0000
   6.250   0.9902   0.06878   0.05902  -0.1481   0.5864   1.0000
   6.500   0.9933   0.07243   0.06270  -0.1478   0.5824   1.0000
   6.750   1.0269   0.07300   0.06330  -0.1482   0.5788   1.0000
   7.000   0.9901   0.08073   0.07108  -0.1472   0.5756   1.0000
   7.250   0.9761   0.08628   0.07668  -0.1470   0.5749   1.0000
   7.500   0.9667   0.09124   0.08170  -0.1470   0.5740   1.0000
   7.750   0.9606   0.09586   0.08638  -0.1470   0.5735   1.0000
   8.000   0.9576   0.09995   0.09055  -0.1469   0.5711   1.0000
   8.250   0.9864   0.10106   0.09172  -0.1467   0.5610   1.0000
   8.500   0.9754   0.10574   0.09646  -0.1466   0.5580   1.0000
   8.750   0.9740   0.10973   0.10054  -0.1466   0.5550   1.0000
   9.000   0.9954   0.11168   0.10257  -0.1464   0.5447   1.0000
   9.250   0.9879   0.11640   0.10738  -0.1468   0.5435   1.0000
   9.500   0.9843   0.12109   0.11217  -0.1474   0.5440   1.0000
   9.750   0.9874   0.12585   0.11706  -0.1485   0.5461   1.0000
  10.000   1.0231   0.12564   0.11696  -0.1470   0.5179   1.0000
  10.250   1.0231   0.13067   0.12209  -0.1480   0.5172   1.0000
  10.500   0.9552   0.14513   0.13664  -0.1548   0.5937   1.0000
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