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GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 441 AIRFOIL (goe441-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.91 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe441-il-1000000-n5.txt
Download as CSV file: xf-goe441-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4256   0.05377   0.05035  -0.1219   0.7701   0.0242
 -12.250  -0.4665   0.04025   0.03659  -0.1403   0.7615   0.0242
 -12.000  -0.4557   0.02775   0.02372  -0.1636   0.7546   0.0243
 -11.750  -0.4192   0.02228   0.01794  -0.1769   0.7480   0.0244
 -11.500  -0.3894   0.02040   0.01589  -0.1810   0.7411   0.0246
 -11.250  -0.3599   0.01915   0.01452  -0.1834   0.7349   0.0248
 -11.000  -0.3305   0.01819   0.01345  -0.1852   0.7280   0.0250
 -10.750  -0.3013   0.01742   0.01257  -0.1866   0.7204   0.0251
 -10.500  -0.2717   0.01674   0.01180  -0.1878   0.7147   0.0253
 -10.250  -0.2421   0.01613   0.01112  -0.1889   0.7087   0.0255
 -10.000  -0.2126   0.01561   0.01049  -0.1897   0.7017   0.0257
  -9.750  -0.1829   0.01511   0.00991  -0.1906   0.6948   0.0259
  -9.500  -0.1533   0.01467   0.00938  -0.1913   0.6852   0.0261
  -9.250  -0.1238   0.01426   0.00887  -0.1919   0.6756   0.0263
  -9.000  -0.0945   0.01390   0.00840  -0.1925   0.6618   0.0265
  -8.750  -0.0653   0.01359   0.00796  -0.1930   0.6425   0.0267
  -8.500  -0.0388   0.01354   0.00761  -0.1929   0.5798   0.0270
  -8.000   0.0170   0.01333   0.00702  -0.1933   0.5213   0.0275
  -7.750   0.0465   0.01310   0.00670  -0.1938   0.5117   0.0277
  -7.500   0.0761   0.01290   0.00641  -0.1942   0.5041   0.0278
  -7.250   0.1058   0.01267   0.00609  -0.1946   0.4979   0.0281
  -7.000   0.1361   0.01236   0.00573  -0.1952   0.4937   0.0285
  -6.750   0.1661   0.01212   0.00545  -0.1957   0.4891   0.0288
  -6.500   0.1959   0.01195   0.00522  -0.1961   0.4842   0.0292
  -6.000   0.2556   0.01164   0.00481  -0.1968   0.4757   0.0300
  -5.750   0.2856   0.01149   0.00463  -0.1972   0.4723   0.0305
  -5.500   0.3155   0.01136   0.00445  -0.1975   0.4689   0.0309
  -5.250   0.3453   0.01125   0.00430  -0.1978   0.4654   0.0314
  -5.000   0.3749   0.01117   0.00416  -0.1981   0.4618   0.0318
  -4.750   0.4047   0.01105   0.00400  -0.1984   0.4584   0.0326
  -4.500   0.4348   0.01092   0.00387  -0.1988   0.4560   0.0334
  -4.250   0.4646   0.01083   0.00376  -0.1991   0.4531   0.0344
  -4.000   0.4943   0.01076   0.00366  -0.1994   0.4498   0.0355
  -3.750   0.5239   0.01070   0.00357  -0.1996   0.4467   0.0367
  -3.500   0.5534   0.01064   0.00349  -0.1999   0.4437   0.0385
  -3.250   0.5827   0.01061   0.00343  -0.2001   0.4404   0.0403
  -3.000   0.6124   0.01055   0.00337  -0.2004   0.4383   0.0430
  -2.750   0.6420   0.01050   0.00331  -0.2007   0.4361   0.0462
  -2.500   0.6716   0.01045   0.00327  -0.2009   0.4334   0.0506
  -2.250   0.7010   0.01041   0.00323  -0.2012   0.4304   0.0559
  -2.000   0.7302   0.01039   0.00322  -0.2014   0.4275   0.0630
  -1.750   0.7592   0.01038   0.00323  -0.2016   0.4247   0.0727
  -1.500   0.7879   0.01042   0.00327  -0.2017   0.4217   0.0812
  -1.250   0.8169   0.01044   0.00330  -0.2018   0.4197   0.0870
  -1.000   0.8460   0.01045   0.00331  -0.2020   0.4174   0.0907
  -0.750   0.8749   0.01047   0.00334  -0.2021   0.4148   0.0944
  -0.500   0.9035   0.01052   0.00337  -0.2022   0.4122   0.0973
  -0.250   0.9320   0.01057   0.00341  -0.2023   0.4096   0.1003
   0.000   0.9603   0.01061   0.00345  -0.2023   0.4068   0.1050
   0.250   0.9882   0.01070   0.00351  -0.2023   0.4034   0.1084
   0.500   1.0168   0.01074   0.00355  -0.2024   0.4015   0.1108
   0.750   1.0453   0.01076   0.00359  -0.2025   0.3995   0.1161
   1.000   1.0736   0.01080   0.00364  -0.2026   0.3970   0.1203
   1.500   1.1295   0.01093   0.00379  -0.2026   0.3912   0.1370
   1.750   1.1573   0.01097   0.00391  -0.2027   0.3881   0.1782
   2.000   1.1847   0.01106   0.00401  -0.2026   0.3853   0.1952
   2.250   1.2125   0.01111   0.00410  -0.2027   0.3830   0.2075
   2.500   1.2400   0.01119   0.00420  -0.2026   0.3800   0.2192
   2.750   1.2672   0.01128   0.00431  -0.2025   0.3767   0.2325
   3.250   1.3211   0.01143   0.00460  -0.2024   0.3702   0.3195
   3.500   1.3483   0.01148   0.00477  -0.2024   0.3681   0.3773
   3.750   1.3753   0.01156   0.00493  -0.2023   0.3659   0.4153
   4.000   1.4018   0.01166   0.00509  -0.2022   0.3632   0.4405
   4.250   1.4277   0.01180   0.00524  -0.2019   0.3601   0.4577
   4.500   1.4530   0.01196   0.00541  -0.2015   0.3571   0.4718
   4.750   1.4779   0.01213   0.00560  -0.2010   0.3542   0.4864
   5.000   1.5029   0.01228   0.00579  -0.2006   0.3519   0.5027
   5.250   1.5284   0.01241   0.00597  -0.2002   0.3499   0.5228
   5.500   1.5534   0.01254   0.00616  -0.1998   0.3475   0.5491
   5.750   1.5777   0.01269   0.00637  -0.1993   0.3447   0.5736
   6.000   1.6002   0.01285   0.00661  -0.1984   0.3417   0.6130
   6.250   1.6216   0.01300   0.00691  -0.1974   0.3384   0.6899
   6.500   1.6448   0.01311   0.00719  -0.1968   0.3355   0.7871
   7.000   1.6853   0.01328   0.00765  -0.1941   0.3301   1.0000
   7.250   1.7068   0.01356   0.00793  -0.1931   0.3269   1.0000
   7.500   1.7263   0.01394   0.00827  -0.1918   0.3217   1.0000
   7.750   1.7474   0.01424   0.00857  -0.1909   0.3169   1.0000
   8.000   1.7675   0.01459   0.00892  -0.1897   0.3116   1.0000
   8.250   1.7855   0.01506   0.00935  -0.1883   0.3057   1.0000
   8.500   1.8053   0.01544   0.00973  -0.1872   0.3003   1.0000
   8.750   1.8234   0.01591   0.01018  -0.1859   0.2939   1.0000
   9.000   1.8403   0.01645   0.01070  -0.1844   0.2877   1.0000
   9.250   1.8580   0.01696   0.01120  -0.1831   0.2811   1.0000
   9.500   1.8724   0.01766   0.01186  -0.1813   0.2734   1.0000
   9.750   1.8878   0.01832   0.01250  -0.1798   0.2650   1.0000
  10.000   1.9009   0.01912   0.01327  -0.1779   0.2572   1.0000
  10.250   1.9151   0.01988   0.01402  -0.1763   0.2494   1.0000
  10.500   1.9263   0.02084   0.01495  -0.1744   0.2413   1.0000
  10.750   1.9367   0.02187   0.01595  -0.1724   0.2318   1.0000
  11.000   1.9468   0.02295   0.01701  -0.1705   0.2236   1.0000
  11.250   1.9530   0.02432   0.01834  -0.1682   0.2137   1.0000
  11.500   1.9620   0.02553   0.01954  -0.1663   0.2052   1.0000
  11.750   1.9669   0.02708   0.02106  -0.1641   0.1963   1.0000
  12.000   1.9685   0.02893   0.02287  -0.1617   0.1855   1.0000
  12.250   1.9687   0.03094   0.02485  -0.1593   0.1735   1.0000
  12.500   1.9614   0.03367   0.02752  -0.1565   0.1577   1.0000
  12.750   1.9333   0.03841   0.03212  -0.1525   0.1302   1.0000
  13.000   1.9151   0.04256   0.03622  -0.1496   0.1142   1.0000
  13.250   1.9031   0.04630   0.03997  -0.1475   0.1040   1.0000
  13.500   1.8900   0.05031   0.04399  -0.1456   0.0942   1.0000
  13.750   1.8609   0.05629   0.04996  -0.1435   0.0755   1.0000
  14.000   1.8288   0.06300   0.05667  -0.1418   0.0582   1.0000
  14.250   1.7993   0.06980   0.06354  -0.1408   0.0469   1.0000
  14.500   1.7799   0.07555   0.06937  -0.1403   0.0410   1.0000
  14.750   1.7658   0.08063   0.07454  -0.1400   0.0376   1.0000
  15.000   1.7536   0.08550   0.07947  -0.1397   0.0350   1.0000
  15.250   1.7417   0.09033   0.08439  -0.1396   0.0330   1.0000
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