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GOE 482 AIRFOIL (goe482-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 482 AIRFOIL (goe482-il)
Reynolds number: 500,000
Max Cl/Cd: 100.28 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe482-il-500000-n5.txt
Download as CSV file: xf-goe482-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500   0.1498   0.09163   0.08776  -0.1304   0.7356   0.0283
 -11.250   0.1418   0.08644   0.08253  -0.1328   0.7317   0.0313
 -11.000   0.1539   0.08497   0.08107  -0.1334   0.7260   0.0315
 -10.750   0.1666   0.08366   0.07974  -0.1339   0.7202   0.0318
 -10.500   0.1780   0.08219   0.07824  -0.1344   0.7150   0.0323
 -10.000   0.1722   0.07435   0.07039  -0.1381   0.7046   0.0358
  -9.750   0.1826   0.07286   0.06887  -0.1384   0.6985   0.0360
  -8.750   0.0169   0.02784   0.02346  -0.1799   0.6782   0.0424
  -8.500   0.0387   0.02488   0.02017  -0.1846   0.6706   0.0429
  -8.250   0.0628   0.02292   0.01792  -0.1871   0.6631   0.0434
  -8.000   0.0886   0.02137   0.01613  -0.1888   0.6545   0.0439
  -7.750   0.1148   0.02017   0.01467  -0.1900   0.6461   0.0444
  -7.500   0.1420   0.01919   0.01347  -0.1910   0.6375   0.0449
  -7.250   0.1690   0.01833   0.01238  -0.1917   0.6290   0.0453
  -7.000   0.1966   0.01759   0.01145  -0.1923   0.6195   0.0456
  -6.750   0.2239   0.01701   0.01067  -0.1926   0.6103   0.0459
  -6.500   0.2515   0.01651   0.01000  -0.1929   0.6004   0.0461
  -6.250   0.2789   0.01588   0.00922  -0.1933   0.5922   0.0465
  -6.000   0.3063   0.01537   0.00860  -0.1935   0.5835   0.0469
  -5.750   0.3338   0.01502   0.00816  -0.1937   0.5757   0.0473
  -5.500   0.3616   0.01473   0.00779  -0.1938   0.5677   0.0476
  -5.250   0.3890   0.01450   0.00745  -0.1938   0.5608   0.0480
  -5.000   0.4171   0.01425   0.00715  -0.1940   0.5544   0.0484
  -4.750   0.4448   0.01408   0.00689  -0.1940   0.5479   0.0490
  -4.500   0.4725   0.01391   0.00663  -0.1941   0.5423   0.0496
  -4.250   0.5007   0.01370   0.00636  -0.1942   0.5367   0.0501
  -4.000   0.5284   0.01352   0.00610  -0.1942   0.5312   0.0506
  -3.750   0.5559   0.01338   0.00587  -0.1942   0.5261   0.0511
  -3.500   0.5842   0.01321   0.00565  -0.1943   0.5215   0.0516
  -3.250   0.6121   0.01308   0.00546  -0.1943   0.5167   0.0521
  -3.000   0.6396   0.01300   0.00531  -0.1943   0.5119   0.0526
  -2.750   0.6672   0.01294   0.00518  -0.1942   0.5079   0.0530
  -2.500   0.6956   0.01271   0.00495  -0.1944   0.5040   0.0538
  -2.250   0.7236   0.01260   0.00482  -0.1945   0.5001   0.0546
  -2.000   0.7511   0.01255   0.00475  -0.1945   0.4963   0.0555
  -1.750   0.7782   0.01256   0.00470  -0.1944   0.4923   0.0566
  -1.500   0.8061   0.01252   0.00465  -0.1944   0.4890   0.0577
  -1.250   0.8340   0.01248   0.00460  -0.1944   0.4854   0.0587
  -1.000   0.8615   0.01247   0.00456  -0.1944   0.4820   0.0596
  -0.750   0.8885   0.01249   0.00454  -0.1943   0.4784   0.0605
  -0.500   0.9152   0.01251   0.00452  -0.1941   0.4749   0.0617
  -0.250   0.9427   0.01249   0.00451  -0.1941   0.4717   0.0635
   0.000   0.9700   0.01250   0.00452  -0.1940   0.4680   0.0654
   0.250   0.9968   0.01254   0.00455  -0.1939   0.4644   0.0678
   0.500   1.0230   0.01261   0.00459  -0.1936   0.4609   0.0702
   0.750   1.0489   0.01268   0.00464  -0.1933   0.4576   0.0746
   1.000   1.0755   0.01272   0.00470  -0.1932   0.4546   0.0805
   1.250   1.1022   0.01271   0.00478  -0.1931   0.4511   0.1035
   1.500   1.1282   0.01272   0.00489  -0.1929   0.4472   0.1511
   1.750   1.1533   0.01278   0.00501  -0.1926   0.4433   0.1835
   2.000   1.1778   0.01284   0.00516  -0.1922   0.4397   0.2360
   2.250   1.2040   0.01284   0.00535  -0.1921   0.4367   0.3136
   2.500   1.2289   0.01294   0.00551  -0.1917   0.4331   0.3467
   2.750   1.2529   0.01308   0.00568  -0.1911   0.4294   0.3673
   3.000   1.2758   0.01325   0.00585  -0.1903   0.4258   0.3838
   3.250   1.2976   0.01342   0.00603  -0.1893   0.4224   0.4011
   3.500   1.3204   0.01353   0.00619  -0.1885   0.4187   0.4179
   3.750   1.3416   0.01366   0.00638  -0.1874   0.4146   0.4369
   4.250   1.3807   0.01406   0.00690  -0.1848   0.4066   0.4983
   4.500   1.4028   0.01419   0.00717  -0.1840   0.4032   0.5600
   4.750   1.4236   0.01435   0.00745  -0.1830   0.3995   0.6143
   5.000   1.4426   0.01451   0.00778  -0.1817   0.3956   0.6883
   5.500   1.4791   0.01475   0.00838  -0.1787   0.3886   1.0000
   5.750   1.4994   0.01506   0.00869  -0.1777   0.3850   1.0000
   6.000   1.5179   0.01542   0.00904  -0.1765   0.3811   1.0000
   6.250   1.5348   0.01586   0.00945  -0.1750   0.3771   1.0000
   6.500   1.5514   0.01633   0.00990  -0.1736   0.3734   1.0000
   6.750   1.5705   0.01672   0.01031  -0.1725   0.3700   1.0000
   7.000   1.5882   0.01717   0.01077  -0.1713   0.3663   1.0000
   7.250   1.6045   0.01770   0.01129  -0.1700   0.3628   1.0000
   7.500   1.6194   0.01832   0.01189  -0.1685   0.3595   1.0000
   7.750   1.6359   0.01887   0.01246  -0.1672   0.3567   1.0000
   8.000   1.6534   0.01941   0.01302  -0.1662   0.3537   1.0000
   8.250   1.6697   0.02001   0.01366  -0.1650   0.3504   1.0000
   8.500   1.6838   0.02075   0.01439  -0.1637   0.3467   1.0000
   8.750   1.6951   0.02166   0.01529  -0.1620   0.3424   1.0000
   9.000   1.7107   0.02237   0.01603  -0.1609   0.3384   1.0000
   9.250   1.7235   0.02325   0.01693  -0.1596   0.3329   1.0000
   9.500   1.7335   0.02433   0.01800  -0.1580   0.3281   1.0000
   9.750   1.7456   0.02532   0.01900  -0.1568   0.3238   1.0000
  10.000   1.7582   0.02629   0.02001  -0.1556   0.3187   1.0000
  10.250   1.7674   0.02751   0.02124  -0.1541   0.3136   1.0000
  10.500   1.7756   0.02883   0.02256  -0.1526   0.3087   1.0000
  10.750   1.7872   0.02995   0.02372  -0.1515   0.3036   1.0000
  11.000   1.7956   0.03133   0.02511  -0.1502   0.2984   1.0000
  11.250   1.8008   0.03299   0.02678  -0.1487   0.2936   1.0000
  11.500   1.8125   0.03418   0.02803  -0.1478   0.2891   1.0000
  11.750   1.8199   0.03576   0.02964  -0.1466   0.2839   1.0000
  12.000   1.8218   0.03785   0.03173  -0.1451   0.2779   1.0000
  12.250   1.8307   0.03939   0.03331  -0.1442   0.2721   1.0000
  12.500   1.8325   0.04161   0.03555  -0.1429   0.2656   1.0000
  12.750   1.8358   0.04377   0.03774  -0.1418   0.2589   1.0000
  13.000   1.8353   0.04637   0.04036  -0.1406   0.2506   1.0000
  13.250   1.8343   0.04911   0.04312  -0.1396   0.2417   1.0000
  13.500   1.8271   0.05261   0.04661  -0.1385   0.2309   1.0000
  13.750   1.8170   0.05656   0.05055  -0.1374   0.2186   1.0000
  14.000   1.8019   0.06124   0.05521  -0.1365   0.2037   1.0000
  14.250   1.7838   0.06646   0.06042  -0.1357   0.1893   1.0000
  14.500   1.7624   0.07230   0.06624  -0.1352   0.1747   1.0000
  14.750   1.7431   0.07806   0.07199  -0.1350   0.1626   1.0000
  15.000   1.7267   0.08358   0.07753  -0.1350   0.1525   1.0000
  15.250   1.7136   0.08877   0.08275  -0.1352   0.1429   1.0000
  15.500   1.6982   0.09438   0.08837  -0.1355   0.1328   1.0000
  15.750   1.6813   0.10034   0.09433  -0.1361   0.1213   1.0000
  16.000   1.6556   0.10774   0.10169  -0.1371   0.1030   1.0000
  16.250   1.6266   0.11580   0.10967  -0.1385   0.0809   1.0000
  16.500   1.5987   0.12386   0.11767  -0.1402   0.0581   1.0000
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