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GOE 620 AIRFOIL (goe620-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 620 AIRFOIL (goe620-il)
Reynolds number: 200,000
Max Cl/Cd: 71.05 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe620-il-200000.txt
Download as CSV file: xf-goe620-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 620 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.1033   0.08996   0.08612  -0.1249   0.9306   0.1017
 -10.500   0.1256   0.08708   0.08323  -0.1266   0.9264   0.1038
 -10.250  -0.2121   0.04793   0.04339  -0.1620   0.9201   0.0722
 -10.000  -0.2348   0.04491   0.04020  -0.1601   0.9070   0.0718
  -9.750  -0.2481   0.04092   0.03588  -0.1602   0.8989   0.0715
  -9.500  -0.2587   0.03827   0.03293  -0.1577   0.8891   0.0714
  -9.250  -0.2505   0.03504   0.02926  -0.1581   0.8849   0.0715
  -9.000  -0.2582   0.03369   0.02766  -0.1535   0.8747   0.0716
  -8.750  -0.2440   0.03159   0.02518  -0.1528   0.8699   0.0720
  -8.500  -0.2218   0.02977   0.02295  -0.1530   0.8668   0.0726
  -8.250  -0.2183   0.02871   0.02182  -0.1494   0.8584   0.0733
  -8.000  -0.1946   0.02760   0.02068  -0.1491   0.8539   0.0746
  -7.750  -0.1659   0.02654   0.01952  -0.1496   0.8507   0.0761
  -7.500  -0.1350   0.02538   0.01817  -0.1505   0.8481   0.0774
  -7.250  -0.1300   0.02500   0.01768  -0.1466   0.8399   0.0782
  -7.000  -0.1063   0.02413   0.01663  -0.1459   0.8354   0.0795
  -6.750  -0.0769   0.02324   0.01551  -0.1462   0.8322   0.0810
  -6.500  -0.0434   0.02221   0.01452  -0.1474   0.8297   0.0833
  -6.250  -0.0349   0.02209   0.01442  -0.1440   0.8223   0.0849
  -6.000  -0.0102   0.02155   0.01380  -0.1433   0.8175   0.0871
  -5.750   0.0206   0.02092   0.01301  -0.1437   0.8141   0.0895
  -5.500   0.0536   0.02006   0.01220  -0.1446   0.8114   0.0925
  -5.250   0.0645   0.01999   0.01217  -0.1415   0.8043   0.0951
  -5.000   0.0886   0.01965   0.01175  -0.1407   0.7993   0.0990
  -4.750   0.1180   0.01900   0.01114  -0.1409   0.7957   0.1037
  -4.500   0.1524   0.01849   0.01055  -0.1419   0.7927   0.1104
  -4.250   0.1620   0.01835   0.01053  -0.1386   0.7855   0.1164
  -4.000   0.1856   0.01794   0.01017  -0.1376   0.7803   0.1280
  -3.750   0.2156   0.01738   0.00969  -0.1379   0.7766   0.1528
  -3.500   0.2505   0.01699   0.00939  -0.1391   0.7735   0.1899
  -3.250   0.2594   0.01715   0.00963  -0.1355   0.7655   0.2088
  -3.000   0.2873   0.01701   0.00948  -0.1353   0.7606   0.2310
  -2.750   0.3216   0.01680   0.00922  -0.1363   0.7568   0.2515
  -2.500   0.3445   0.01680   0.00925  -0.1353   0.7513   0.2675
  -2.250   0.3641   0.01680   0.00930  -0.1336   0.7446   0.2822
  -2.000   0.3950   0.01663   0.00911  -0.1339   0.7400   0.2999
  -1.750   0.4317   0.01645   0.00888  -0.1353   0.7364   0.3199
  -1.500   0.4437   0.01660   0.00908  -0.1322   0.7284   0.3338
  -1.250   0.4709   0.01651   0.00898  -0.1319   0.7229   0.3524
  -1.000   0.5058   0.01629   0.00876  -0.1330   0.7188   0.3740
  -0.750   0.5233   0.01634   0.00888  -0.1309   0.7117   0.3911
  -0.500   0.5468   0.01623   0.00883  -0.1298   0.7053   0.4105
  -0.250   0.5804   0.01602   0.00860  -0.1307   0.7007   0.4339
   0.000   0.6009   0.01599   0.00867  -0.1291   0.6942   0.4559
   0.250   0.6214   0.01589   0.00869  -0.1275   0.6871   0.4809
   0.500   0.6535   0.01568   0.00851  -0.1281   0.6823   0.5153
   0.750   0.6730   0.01564   0.00860  -0.1263   0.6756   0.5473
   1.000   0.6929   0.01551   0.00860  -0.1245   0.6684   0.5849
   1.250   0.7247   0.01516   0.00835  -0.1249   0.6631   0.6377
   1.500   0.7368   0.01498   0.00846  -0.1215   0.6546   0.7017
   1.750   0.8695   0.01424   0.00809  -0.1425   0.6451   1.0000
   2.000   0.8837   0.01436   0.00815  -0.1398   0.6364   1.0000
   2.250   0.9071   0.01438   0.00804  -0.1388   0.6293   1.0000
   2.500   0.9283   0.01446   0.00803  -0.1374   0.6219   1.0000
   2.750   0.9459   0.01456   0.00807  -0.1353   0.6139   1.0000
   3.000   0.9744   0.01458   0.00794  -0.1353   0.6073   1.0000
   3.250   0.9855   0.01476   0.00813  -0.1320   0.5983   1.0000
   3.500   1.0122   0.01479   0.00802  -0.1316   0.5912   1.0000
   3.750   1.0251   0.01499   0.00821  -0.1287   0.5824   1.0000
   4.000   1.0483   0.01508   0.00819  -0.1276   0.5746   1.0000
   4.250   1.0643   0.01529   0.00837  -0.1253   0.5664   1.0000
   4.500   1.0838   0.01544   0.00844  -0.1237   0.5583   1.0000
   4.750   1.1032   0.01565   0.00860  -0.1220   0.5505   1.0000
   5.000   1.1186   0.01587   0.00878  -0.1196   0.5422   1.0000
   5.250   1.1411   0.01608   0.00890  -0.1186   0.5345   1.0000
   5.500   1.1501   0.01634   0.00916  -0.1150   0.5262   1.0000
   5.750   1.1766   0.01656   0.00925  -0.1148   0.5186   1.0000
   6.000   1.1816   0.01687   0.00961  -0.1105   0.5103   1.0000
   6.250   1.2037   0.01711   0.00974  -0.1095   0.5023   1.0000
   6.500   1.2120   0.01746   0.01013  -0.1060   0.4940   1.0000
   6.750   1.2291   0.01775   0.01035  -0.1041   0.4859   1.0000
   7.000   1.2412   0.01812   0.01073  -0.1015   0.4775   1.0000
   7.250   1.2545   0.01847   0.01104  -0.0990   0.4688   1.0000
   7.500   1.2674   0.01888   0.01143  -0.0966   0.4604   1.0000
   7.750   1.2793   0.01930   0.01184  -0.0941   0.4518   1.0000
   8.000   1.2940   0.01974   0.01225  -0.0921   0.4437   1.0000
   8.250   1.3039   0.02024   0.01277  -0.0894   0.4350   1.0000
   8.500   1.3190   0.02072   0.01319  -0.0876   0.4270   1.0000
   8.750   1.3279   0.02132   0.01383  -0.0849   0.4184   1.0000
   9.000   1.3435   0.02183   0.01427  -0.0833   0.4104   1.0000
   9.250   1.3502   0.02255   0.01505  -0.0805   0.4015   1.0000
   9.500   1.3657   0.02311   0.01552  -0.0790   0.3936   1.0000
   9.750   1.3722   0.02393   0.01642  -0.0764   0.3850   1.0000
  10.000   1.3877   0.02453   0.01692  -0.0749   0.3777   1.0000
  10.250   1.3943   0.02545   0.01793  -0.0725   0.3696   1.0000
  10.500   1.4067   0.02618   0.01862  -0.0709   0.3623   1.0000
  10.750   1.4178   0.02703   0.01949  -0.0691   0.3555   1.0000
  11.000   1.4277   0.02793   0.02042  -0.0673   0.3486   1.0000
  11.250   1.4444   0.02858   0.02098  -0.0663   0.3425   1.0000
  11.500   1.4503   0.02971   0.02224  -0.0642   0.3360   1.0000
  11.750   1.4602   0.03067   0.02318  -0.0626   0.3294   1.0000
  12.000   1.4718   0.03160   0.02410  -0.0612   0.3233   1.0000
  12.250   1.4787   0.03279   0.02539  -0.0595   0.3172   1.0000
  12.500   1.4899   0.03375   0.02632  -0.0582   0.3112   1.0000
  12.750   1.4989   0.03490   0.02752  -0.0567   0.3055   1.0000
  13.000   1.5052   0.03623   0.02894  -0.0552   0.2996   1.0000
  13.250   1.5167   0.03724   0.02990  -0.0540   0.2939   1.0000
  13.500   1.5223   0.03870   0.03145  -0.0525   0.2881   1.0000
  13.750   1.5268   0.04025   0.03307  -0.0511   0.2819   1.0000
  14.000   1.5394   0.04121   0.03393  -0.0501   0.2758   1.0000
  14.250   1.5374   0.04336   0.03626  -0.0485   0.2693   1.0000
  14.500   1.5417   0.04502   0.03793  -0.0472   0.2624   1.0000
  14.750   1.5441   0.04690   0.03986  -0.0460   0.2555   1.0000
  15.000   1.5433   0.04911   0.04213  -0.0447   0.2477   1.0000
  15.250   1.5450   0.05114   0.04415  -0.0435   0.2401   1.0000
  15.500   1.5410   0.05379   0.04686  -0.0424   0.2315   1.0000
  15.750   1.5385   0.05635   0.04943  -0.0414   0.2229   1.0000
  16.000   1.5361   0.05897   0.05206  -0.0405   0.2149   1.0000
  16.250   1.5329   0.06176   0.05490  -0.0398   0.2071   1.0000
  16.500   1.5304   0.06455   0.05769  -0.0391   0.2000   1.0000
  16.750   1.5298   0.06717   0.06034  -0.0386   0.1939   1.0000
  17.000   1.5275   0.07011   0.06337  -0.0383   0.1879   1.0000
  17.250   1.5302   0.07235   0.06553  -0.0378   0.1831   1.0000
  17.500   1.5288   0.07526   0.06857  -0.0376   0.1784   1.0000
  17.750   1.5286   0.07806   0.07145  -0.0375   0.1741   1.0000
  18.000   1.5314   0.08039   0.07376  -0.0373   0.1704   1.0000
  18.250   1.5346   0.08272   0.07612  -0.0371   0.1669   1.0000
  18.500   1.5340   0.08560   0.07913  -0.0372   0.1637   1.0000
  18.750   1.5339   0.08845   0.08205  -0.0373   0.1602   1.0000
  19.000   1.5380   0.09063   0.08421  -0.0373   0.1571   1.0000
  19.250   1.5416   0.09290   0.08651  -0.0373   0.1540   1.0000
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