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GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 441 AIRFOIL (goe441-il)
Reynolds number: 500,000
Max Cl/Cd: 101.67 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe441-il-500000-n5.txt
Download as CSV file: xf-goe441-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 441 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2803   0.02798   0.02346  -0.1674   0.7726   0.0286
 -10.250  -0.2476   0.02482   0.02004  -0.1752   0.7642   0.0288
 -10.000  -0.2184   0.02318   0.01820  -0.1787   0.7568   0.0290
  -9.750  -0.1890   0.02187   0.01675  -0.1813   0.7497   0.0292
  -9.500  -0.1599   0.02078   0.01550  -0.1833   0.7424   0.0295
  -9.250  -0.1306   0.01984   0.01440  -0.1849   0.7356   0.0298
  -9.000  -0.1012   0.01901   0.01343  -0.1863   0.7272   0.0301
  -8.500  -0.0425   0.01760   0.01172  -0.1886   0.7107   0.0309
  -8.250  -0.0132   0.01699   0.01095  -0.1894   0.7014   0.0312
  -8.000   0.0163   0.01641   0.01025  -0.1903   0.6913   0.0315
  -7.750   0.0454   0.01593   0.00960  -0.1909   0.6794   0.0317
  -7.500   0.0748   0.01543   0.00898  -0.1916   0.6650   0.0320
  -7.250   0.1036   0.01498   0.00841  -0.1921   0.6448   0.0324
  -7.000   0.1306   0.01473   0.00796  -0.1922   0.6025   0.0328
  -6.750   0.1559   0.01470   0.00762  -0.1920   0.5560   0.0332
  -6.500   0.1836   0.01455   0.00730  -0.1922   0.5362   0.0336
  -6.250   0.2124   0.01435   0.00699  -0.1925   0.5250   0.0341
  -6.000   0.2412   0.01416   0.00669  -0.1928   0.5166   0.0347
  -5.750   0.2707   0.01395   0.00640  -0.1932   0.5102   0.0353
  -5.500   0.2999   0.01379   0.00613  -0.1935   0.5040   0.0359
  -5.250   0.3290   0.01361   0.00588  -0.1939   0.4982   0.0365
  -5.000   0.3588   0.01341   0.00565  -0.1943   0.4938   0.0375
  -4.750   0.3882   0.01327   0.00546  -0.1946   0.4891   0.0385
  -4.500   0.4175   0.01316   0.00529  -0.1949   0.4849   0.0397
  -4.250   0.4465   0.01308   0.00513  -0.1951   0.4809   0.0408
  -4.000   0.4760   0.01294   0.00497  -0.1954   0.4775   0.0423
  -3.750   0.5056   0.01282   0.00483  -0.1958   0.4745   0.0441
  -3.500   0.5351   0.01273   0.00470  -0.1960   0.4710   0.0461
  -3.250   0.5644   0.01264   0.00459  -0.1963   0.4673   0.0489
  -3.000   0.5933   0.01259   0.00451  -0.1965   0.4637   0.0524
  -2.750   0.6221   0.01257   0.00445  -0.1967   0.4603   0.0575
  -2.500   0.6512   0.01252   0.00441  -0.1969   0.4576   0.0643
  -2.250   0.6804   0.01248   0.00441  -0.1971   0.4552   0.0726
  -2.000   0.7093   0.01248   0.00442  -0.1972   0.4524   0.0804
  -1.750   0.7378   0.01251   0.00444  -0.1973   0.4493   0.0870
  -1.500   0.7662   0.01255   0.00446  -0.1974   0.4461   0.0921
  -1.250   0.7942   0.01262   0.00449  -0.1973   0.4430   0.0971
  -1.000   0.8222   0.01268   0.00452  -0.1973   0.4400   0.1013
  -0.750   0.8508   0.01270   0.00454  -0.1975   0.4379   0.1061
  -0.500   0.8793   0.01273   0.00457  -0.1975   0.4356   0.1106
  -0.250   0.9079   0.01273   0.00459  -0.1977   0.4328   0.1163
   0.000   0.9361   0.01277   0.00462  -0.1977   0.4298   0.1207
   0.250   0.9639   0.01283   0.00466  -0.1977   0.4269   0.1257
   0.500   0.9916   0.01289   0.00473  -0.1977   0.4242   0.1338
   0.750   1.0190   0.01297   0.00482  -0.1977   0.4216   0.1457
   1.000   1.0471   0.01299   0.00493  -0.1978   0.4194   0.1736
   1.250   1.0751   0.01304   0.00502  -0.1978   0.4168   0.1967
   1.500   1.1027   0.01310   0.00512  -0.1978   0.4141   0.2128
   1.750   1.1300   0.01318   0.00523  -0.1977   0.4114   0.2279
   2.000   1.1570   0.01327   0.00534  -0.1976   0.4086   0.2470
   2.250   1.1838   0.01335   0.00548  -0.1975   0.4058   0.2805
   2.500   1.2105   0.01341   0.00570  -0.1975   0.4030   0.3608
   2.750   1.2377   0.01348   0.00587  -0.1974   0.4007   0.4020
   3.000   1.2644   0.01358   0.00603  -0.1973   0.3981   0.4302
   3.250   1.2905   0.01371   0.00619  -0.1970   0.3950   0.4531
   3.500   1.3161   0.01385   0.00637  -0.1966   0.3919   0.4752
   3.750   1.3410   0.01403   0.00656  -0.1962   0.3889   0.4949
   4.000   1.3651   0.01423   0.00677  -0.1956   0.3858   0.5133
   4.500   1.4162   0.01449   0.00716  -0.1949   0.3807   0.5547
   4.750   1.4410   0.01463   0.00739  -0.1945   0.3780   0.5879
   5.000   1.4650   0.01476   0.00765  -0.1939   0.3753   0.6372
   5.250   1.4869   0.01488   0.00794  -0.1929   0.3724   0.7195
   5.500   1.5060   0.01492   0.00820  -0.1913   0.3696   0.8332
   5.750   1.5240   0.01499   0.00838  -0.1894   0.3672   1.0000
   6.000   1.5471   0.01523   0.00863  -0.1887   0.3645   1.0000
   6.250   1.5694   0.01549   0.00890  -0.1878   0.3618   1.0000
   6.500   1.5911   0.01579   0.00920  -0.1869   0.3590   1.0000
   6.750   1.6119   0.01612   0.00952  -0.1859   0.3562   1.0000
   7.000   1.6318   0.01650   0.00988  -0.1847   0.3535   1.0000
   7.250   1.6531   0.01682   0.01023  -0.1838   0.3511   1.0000
   7.500   1.6747   0.01713   0.01057  -0.1830   0.3484   1.0000
   7.750   1.6953   0.01749   0.01095  -0.1820   0.3452   1.0000
   8.000   1.7147   0.01790   0.01137  -0.1808   0.3418   1.0000
   8.250   1.7328   0.01838   0.01184  -0.1795   0.3386   1.0000
   8.500   1.7514   0.01885   0.01233  -0.1783   0.3351   1.0000
   8.750   1.7710   0.01927   0.01279  -0.1773   0.3308   1.0000
   9.000   1.7885   0.01980   0.01334  -0.1760   0.3262   1.0000
   9.250   1.8037   0.02046   0.01398  -0.1745   0.3216   1.0000
   9.500   1.8215   0.02101   0.01456  -0.1733   0.3167   1.0000
   9.750   1.8376   0.02165   0.01522  -0.1720   0.3110   1.0000
  10.000   1.8504   0.02251   0.01607  -0.1703   0.3056   1.0000
  10.250   1.8665   0.02319   0.01678  -0.1690   0.2995   1.0000
  10.500   1.8782   0.02416   0.01774  -0.1673   0.2923   1.0000
  10.750   1.8907   0.02510   0.01869  -0.1658   0.2859   1.0000
  11.000   1.9025   0.02612   0.01973  -0.1642   0.2793   1.0000
  11.250   1.9115   0.02735   0.02096  -0.1624   0.2730   1.0000
  11.500   1.9230   0.02844   0.02208  -0.1609   0.2664   1.0000
  12.000   1.9360   0.03144   0.02509  -0.1573   0.2507   1.0000
  12.250   1.9388   0.03330   0.02695  -0.1553   0.2432   1.0000
  12.500   1.9456   0.03490   0.02858  -0.1537   0.2361   1.0000
  12.750   1.9466   0.03704   0.03073  -0.1518   0.2292   1.0000
  13.000   1.9504   0.03900   0.03272  -0.1503   0.2220   1.0000
  13.250   1.9474   0.04166   0.03539  -0.1484   0.2141   1.0000
  13.500   1.9461   0.04424   0.03799  -0.1468   0.2049   1.0000
  13.750   1.9379   0.04757   0.04133  -0.1449   0.1951   1.0000
  14.000   1.9253   0.05150   0.04526  -0.1432   0.1838   1.0000
  14.250   1.9096   0.05594   0.04971  -0.1415   0.1715   1.0000
  14.500   1.8904   0.06094   0.05472  -0.1401   0.1589   1.0000
  14.750   1.8643   0.06705   0.06085  -0.1389   0.1452   1.0000
  15.000   1.8327   0.07415   0.06797  -0.1381   0.1316   1.0000
  15.250   1.8055   0.08086   0.07473  -0.1377   0.1219   1.0000
  15.500   1.7801   0.08743   0.08135  -0.1375   0.1131   1.0000
  15.750   1.7572   0.09367   0.08765  -0.1375   0.1054   1.0000
  16.000   1.7348   0.09990   0.09392  -0.1376   0.0973   1.0000
  16.250   1.7046   0.10735   0.10137  -0.1381   0.0811   1.0000
  16.500   1.6733   0.11507   0.10907  -0.1389   0.0620   1.0000
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