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GOE 482 AIRFOIL (goe482-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 482 AIRFOIL (goe482-il)
Reynolds number: 100,000
Max Cl/Cd: 50.96 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe482-il-100000-n5.txt
Download as CSV file: xf-goe482-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 482 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.1831   0.10671   0.10097  -0.1229   0.8362   0.0776
 -10.750   0.1720   0.10630   0.10056  -0.1260   0.8280   0.0805
 -10.500   0.1693   0.10455   0.09878  -0.1289   0.8215   0.0808
 -10.250   0.2010   0.09951   0.09368  -0.1273   0.8153   0.0823
 -10.000   0.2180   0.09716   0.09129  -0.1272   0.8083   0.0854
  -9.750   0.2268   0.09513   0.08920  -0.1284   0.8021   0.0891
  -9.500   0.2115   0.09492   0.08903  -0.1307   0.7934   0.0922
  -9.250   0.2078   0.09324   0.08732  -0.1328   0.7868   0.0925
  -9.000   0.2326   0.08916   0.08321  -0.1313   0.7806   0.0938
  -8.750   0.2526   0.08676   0.08077  -0.1304   0.7737   0.0966
  -8.500   0.2633   0.08479   0.07874  -0.1309   0.7680   0.0995
  -8.250   0.2651   0.08325   0.07723  -0.1311   0.7596   0.1024
  -8.000   0.2468   0.08264   0.07665  -0.1334   0.7520   0.1052
  -7.750   0.2388   0.08112   0.07517  -0.1339   0.7439   0.1055
  -7.500   0.2542   0.07790   0.07193  -0.1333   0.7373   0.1064
  -7.250   0.2829   0.07528   0.06921  -0.1321   0.7321   0.1087
  -6.750   0.2544   0.06741   0.06132  -0.1358   0.7172   0.0803
  -6.500   0.2636   0.06562   0.05954  -0.1351   0.7099   0.0796
  -6.250   0.2685   0.06306   0.05696  -0.1367   0.7026   0.0795
  -6.000   0.2773   0.06025   0.05408  -0.1390   0.6967   0.0793
  -5.750   0.2845   0.05771   0.05155  -0.1407   0.6884   0.0788
  -5.500   0.2982   0.05448   0.04823  -0.1442   0.6826   0.0780
  -5.250   0.3114   0.05067   0.04435  -0.1489   0.6753   0.0771
  -5.000   0.3354   0.04331   0.03671  -0.1606   0.6689   0.0761
  -4.750   0.3727   0.03642   0.02917  -0.1724   0.6643   0.0773
  -4.500   0.4018   0.03313   0.02543  -0.1770   0.6564   0.0776
  -4.250   0.4346   0.03066   0.02247  -0.1803   0.6504   0.0780
  -4.000   0.4662   0.02890   0.02027  -0.1825   0.6447   0.0786
  -3.750   0.4947   0.02769   0.01871  -0.1837   0.6376   0.0795
  -3.500   0.5262   0.02663   0.01724  -0.1849   0.6323   0.0810
  -3.250   0.5530   0.02591   0.01644  -0.1853   0.6261   0.0824
  -3.000   0.5800   0.02533   0.01574  -0.1855   0.6196   0.0835
  -2.750   0.6100   0.02468   0.01489  -0.1860   0.6147   0.0847
  -2.500   0.6364   0.02427   0.01435  -0.1860   0.6086   0.0859
  -2.250   0.6634   0.02388   0.01384  -0.1860   0.6025   0.0873
  -2.000   0.6929   0.02346   0.01324  -0.1863   0.5977   0.0893
  -1.750   0.7192   0.02327   0.01293  -0.1862   0.5920   0.0919
  -1.500   0.7452   0.02304   0.01269  -0.1860   0.5862   0.0945
  -1.250   0.7738   0.02280   0.01240  -0.1862   0.5814   0.0972
  -1.000   0.8010   0.02268   0.01221  -0.1862   0.5764   0.1001
  -0.750   0.8259   0.02266   0.01216  -0.1858   0.5706   0.1035
  -0.500   0.8538   0.02256   0.01201  -0.1859   0.5657   0.1083
  -0.250   0.8841   0.02246   0.01180  -0.1864   0.5617   0.1166
   0.000   0.9069   0.02257   0.01201  -0.1858   0.5559   0.1263
   0.250   0.9334   0.02257   0.01202  -0.1857   0.5508   0.1435
   0.500   0.9626   0.02246   0.01193  -0.1861   0.5466   0.1812
   0.750   0.9907   0.02241   0.01210  -0.1865   0.5422   0.2548
   1.000   1.0137   0.02266   0.01254  -0.1860   0.5370   0.3359
   1.250   1.0395   0.02288   0.01273  -0.1857   0.5323   0.3871
   1.500   1.0679   0.02297   0.01283  -0.1859   0.5283   0.4362
   1.750   1.0915   0.02318   0.01319  -0.1853   0.5239   0.4862
   2.250   1.1371   0.02369   0.01387  -0.1838   0.5146   0.5764
   2.500   1.1643   0.02380   0.01397  -0.1837   0.5109   0.6211
   2.750   1.1858   0.02392   0.01427  -0.1826   0.5068   0.6924
   3.000   1.1967   0.02389   0.01461  -0.1796   0.5019   1.0000
   3.250   1.2207   0.02429   0.01488  -0.1792   0.4974   1.0000
   3.500   1.2483   0.02459   0.01501  -0.1793   0.4937   1.0000
   3.750   1.2736   0.02499   0.01530  -0.1792   0.4900   1.0000
   4.000   1.2887   0.02566   0.01599  -0.1775   0.4852   1.0000
   4.250   1.3089   0.02616   0.01644  -0.1766   0.4808   1.0000
   4.500   1.3340   0.02651   0.01669  -0.1764   0.4771   1.0000
   4.750   1.3629   0.02679   0.01681  -0.1767   0.4738   1.0000
   5.000   1.3695   0.02765   0.01778  -0.1739   0.4686   1.0000
   5.250   1.3835   0.02828   0.01842  -0.1720   0.4642   1.0000
   5.500   1.4050   0.02872   0.01880  -0.1713   0.4606   1.0000
   5.750   1.4330   0.02902   0.01899  -0.1715   0.4576   1.0000
   6.000   1.4396   0.02993   0.01999  -0.1688   0.4535   1.0000
   6.250   1.4445   0.03095   0.02108  -0.1659   0.4489   1.0000
   6.500   1.4601   0.03161   0.02173  -0.1646   0.4450   1.0000
   6.750   1.4845   0.03196   0.02201  -0.1643   0.4418   1.0000
   7.000   1.5013   0.03263   0.02268  -0.1631   0.4384   1.0000
   7.250   1.4926   0.03439   0.02460  -0.1591   0.4333   1.0000
   7.500   1.5016   0.03549   0.02574  -0.1573   0.4294   1.0000
   7.750   1.5213   0.03608   0.02631  -0.1566   0.4263   1.0000
   8.000   1.5491   0.03630   0.02648  -0.1568   0.4239   1.0000
   8.250   1.5341   0.03882   0.02918  -0.1529   0.4191   1.0000
   8.500   1.5247   0.04124   0.03173  -0.1499   0.4141   1.0000
   8.750   1.5393   0.04218   0.03269  -0.1489   0.4107   1.0000
   9.000   1.5665   0.04230   0.03276  -0.1489   0.4082   1.0000
   9.250   1.5567   0.04506   0.03566  -0.1463   0.4039   1.0000
   9.500   1.5138   0.05083   0.04167  -0.1423   0.3970   1.0000
   9.750   1.5284   0.05195   0.04282  -0.1416   0.3941   1.0000
  10.000   1.5565   0.05187   0.04272  -0.1416   0.3922   1.0000
  10.250   1.5921   0.05118   0.04199  -0.1419   0.3906   1.0000
  10.750   1.4984   0.06570   0.05693  -0.1364   0.3757   1.0000
  11.000   1.5316   0.06485   0.05608  -0.1363   0.3747   1.0000
  11.500   1.4471   0.08163   0.07317  -0.1346   0.3582   1.0000
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