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GOE 462 AIRFOIL (goe462-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 462 AIRFOIL (goe462-il)
Reynolds number: 500,000
Max Cl/Cd: 175.68 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe462-il-500000.txt
Download as CSV file: xf-goe462-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 462 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.1933   0.09992   0.09678  -0.0881   0.7301   0.0161
  -9.250   0.1995   0.09824   0.09501  -0.0890   0.7066   0.0163
  -9.000   0.2066   0.09649   0.09315  -0.0895   0.6826   0.0163
  -8.750   0.2165   0.09346   0.09002  -0.0890   0.6600   0.0165
  -8.500   0.2264   0.09158   0.08803  -0.0890   0.6393   0.0167
  -8.250   0.2372   0.09008   0.08644  -0.0890   0.6208   0.0173
  -8.000   0.2466   0.08829   0.08457  -0.0893   0.6044   0.0177
  -7.750   0.2564   0.08652   0.08274  -0.0896   0.5923   0.0182
  -7.250   0.2745   0.08272   0.07886  -0.0903   0.5711   0.0197
  -7.000   0.2805   0.08111   0.07722  -0.0906   0.5628   0.0203
  -6.750   0.2865   0.07974   0.07585  -0.0915   0.5552   0.0204
  -6.250   0.3088   0.07502   0.07110  -0.0935   0.5405   0.0207
  -6.000   0.3214   0.07310   0.06912  -0.0933   0.5327   0.0210
  -5.750   0.3356   0.07146   0.06747  -0.0939   0.5251   0.0216
  -5.500   0.3502   0.06977   0.06574  -0.0950   0.5176   0.0223
  -5.250   0.3660   0.06788   0.06382  -0.0966   0.5110   0.0235
  -5.000   0.3870   0.06563   0.06155  -0.1007   0.5045   0.0253
  -4.750   0.4127   0.06349   0.05934  -0.1065   0.4984   0.0256
  -4.500   0.4235   0.06072   0.05659  -0.1053   0.4921   0.0263
  -4.250   0.4418   0.05914   0.05497  -0.1063   0.4849   0.0268
  -4.000   0.4626   0.05744   0.05323  -0.1081   0.4782   0.0278
  -3.750   0.4863   0.05546   0.05122  -0.1108   0.4707   0.0294
  -3.500   0.5312   0.05257   0.04822  -0.1207   0.4638   0.0319
  -3.250   0.5505   0.04961   0.04524  -0.1221   0.4562   0.0327
  -3.000   0.5699   0.04859   0.04415  -0.1221   0.4483   0.0339
  -2.750   0.5985   0.04695   0.04247  -0.1250   0.4402   0.0371
  -2.500   0.6494   0.04315   0.03852  -0.1352   0.4324   0.0405
  -2.250   0.6708   0.04208   0.03743  -0.1353   0.4242   0.0417
  -2.000   0.6994   0.04086   0.03611  -0.1374   0.4160   0.0447
  -1.750   0.7523   0.03770   0.03282  -0.1465   0.4075   0.0501
  -1.500   0.7771   0.03681   0.03184  -0.1471   0.3997   0.0517
  -1.250   0.9463   0.02069   0.01472  -0.1887   0.3904   0.0516
  -1.000   0.9738   0.02064   0.01460  -0.1888   0.3832   0.0549
  -0.750   1.0064   0.02002   0.01388  -0.1902   0.3767   0.0610
  -0.500   1.0260   0.02090   0.01478  -0.1880   0.3706   0.0628
  -0.250   1.0549   0.02072   0.01453  -0.1884   0.3653   0.0707
   0.000   1.0759   0.02140   0.01523  -0.1867   0.3601   0.0720
   0.250   1.0976   0.02197   0.01576  -0.1854   0.3550   0.0750
   0.500   1.1247   0.02203   0.01575  -0.1854   0.3504   0.0830
   0.750   1.1470   0.02243   0.01617  -0.1843   0.3461   0.0862
   1.000   1.1765   0.02224   0.01587  -0.1849   0.3418   0.0940
   1.250   1.1983   0.02258   0.01616  -0.1839   0.3378   0.0972
   1.500   1.2219   0.02284   0.01643  -0.1832   0.3346   0.1065
   2.750   1.3690   0.02175   0.01495  -0.1863   0.3184   0.1266
   3.000   1.3957   0.02146   0.01467  -0.1865   0.3156   0.1277
   3.250   1.4225   0.02130   0.01448  -0.1866   0.3127   0.1293
   3.500   1.4495   0.02125   0.01437  -0.1867   0.3100   0.1327
   4.000   1.4732   0.00985   0.00304  -0.1805   0.3031   0.1381
   4.250   1.4986   0.00974   0.00296  -0.1805   0.3010   0.1392
   4.500   1.5239   0.00972   0.00295  -0.1804   0.2987   0.1408
   4.750   1.5491   0.00977   0.00298  -0.1803   0.2963   0.1439
   5.000   1.6135   0.02162   0.01443  -0.1868   0.2955   0.1483
   5.250   1.6393   0.02110   0.01384  -0.1872   0.2910   0.1494
   5.500   1.6639   0.02091   0.01367  -0.1871   0.2866   0.1502
   5.750   1.6889   0.02080   0.01359  -0.1869   0.2833   0.1514
   6.000   1.7130   0.02081   0.01358  -0.1866   0.2790   0.1531
   6.250   1.7350   0.02105   0.01375  -0.1859   0.2743   0.1559
   6.500   1.7187   0.01016   0.00313  -0.1779   0.2670   0.1615
   6.750   1.7384   0.01011   0.00302  -0.1772   0.2594   0.1625
   7.000   1.7603   0.01002   0.00295  -0.1767   0.2502   0.1637
   7.250   1.7779   0.01023   0.00309  -0.1755   0.2396   0.1653
   7.500   1.7897   0.01064   0.00340  -0.1733   0.2240   0.1672
   7.750   1.7914   0.01140   0.00402  -0.1696   0.2037   0.1695
   8.000   1.8563   0.02401   0.01599  -0.1759   0.1774   0.1728
   8.250   1.8351   0.02680   0.01842  -0.1694   0.1330   0.1732
   8.500   1.8080   0.03024   0.02166  -0.1635   0.0920   0.1732
   8.750   1.7818   0.03418   0.02553  -0.1590   0.0543   0.1733
   9.000   1.7679   0.03761   0.02895  -0.1563   0.0223   0.1734
   9.250   1.7732   0.03949   0.03089  -0.1550   0.0190   0.1736
   9.500   1.7807   0.04112   0.03264  -0.1547   0.0180   0.1745
   9.750   1.7837   0.04337   0.03502  -0.1539   0.0172   0.1752
  10.000   1.7837   0.04609   0.03787  -0.1532   0.0164   0.1760
  10.250   1.7815   0.04926   0.04119  -0.1527   0.0156   0.1770
  10.500   1.7779   0.05278   0.04485  -0.1524   0.0151   0.1780
  10.750   1.7744   0.05646   0.04866  -0.1523   0.0149   0.1792
  11.000   1.7686   0.06061   0.05294  -0.1525   0.0147   0.1806
  11.250   1.7609   0.06519   0.05766  -0.1528   0.0145   0.1826
  11.500   1.7497   0.07041   0.06299  -0.1527   0.0144   0.1858
  11.750   1.7386   0.07582   0.06854  -0.1534   0.0142   0.1859
  12.000   1.7270   0.08144   0.07432  -0.1545   0.0141   0.1862
  12.250   1.7141   0.08748   0.08051  -0.1559   0.0139   0.1865
  12.500   1.7000   0.09381   0.08700  -0.1574   0.0138   0.1868
  12.750   1.6854   0.10033   0.09368  -0.1590   0.0137   0.1870
  13.000   1.6705   0.10707   0.10057  -0.1608   0.0136   0.1873
  13.250   1.6561   0.11382   0.10747  -0.1627   0.0136   0.1875
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