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GOE 482 AIRFOIL (goe482-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 482 AIRFOIL (goe482-il)
Reynolds number: 200,000
Max Cl/Cd: 73.86 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe482-il-200000-n5.txt
Download as CSV file: xf-goe482-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.1909   0.09732   0.09242  -0.1282   0.7785   0.0433
 -10.750   0.1969   0.09474   0.08981  -0.1292   0.7730   0.0440
 -10.500   0.1977   0.09182   0.08686  -0.1308   0.7684   0.0469
 -10.250   0.2127   0.09054   0.08559  -0.1308   0.7626   0.0485
 -10.000   0.2203   0.08849   0.08353  -0.1315   0.7566   0.0506
  -9.750   0.2261   0.08592   0.08092  -0.1323   0.7515   0.0503
  -9.500   0.2265   0.08317   0.07816  -0.1337   0.7456   0.0519
  -9.250   0.2423   0.08229   0.07728  -0.1334   0.7388   0.0561
  -9.000   0.2490   0.08022   0.07516  -0.1340   0.7331   0.0578
  -8.750   0.2533   0.07763   0.07259  -0.1347   0.7267   0.0567
  -8.500   0.2570   0.07509   0.07004  -0.1355   0.7204   0.0563
  -8.250   0.2627   0.07294   0.06784  -0.1361   0.7147   0.0571
  -8.000   0.2661   0.07054   0.06547  -0.1367   0.7076   0.0572
  -7.750   0.2682   0.06795   0.06286  -0.1373   0.7009   0.0566
  -7.500   0.2680   0.06520   0.06009  -0.1379   0.6940   0.0558
  -7.250   0.2702   0.06305   0.05795  -0.1380   0.6864   0.0564
  -7.000   0.2687   0.06087   0.05574  -0.1380   0.6797   0.0567
  -6.750   0.2693   0.05835   0.05324  -0.1390   0.6720   0.0569
  -6.500   0.2714   0.05505   0.04989  -0.1416   0.6654   0.0565
  -6.250   0.2756   0.05107   0.04589  -0.1458   0.6582   0.0564
  -6.000   0.2855   0.03012   0.02410  -0.1791   0.6528   0.0573
  -5.750   0.3143   0.02655   0.01997  -0.1840   0.6460   0.0578
  -5.500   0.3427   0.02453   0.01757  -0.1863   0.6377   0.0584
  -5.000   0.3996   0.02206   0.01440  -0.1888   0.6225   0.0599
  -4.750   0.4281   0.02127   0.01327  -0.1895   0.6153   0.0606
  -4.500   0.4560   0.02051   0.01229  -0.1900   0.6081   0.0611
  -4.250   0.4834   0.01976   0.01140  -0.1903   0.6008   0.0617
  -4.000   0.5108   0.01923   0.01073  -0.1905   0.5944   0.0623
  -3.750   0.5382   0.01879   0.01020  -0.1907   0.5876   0.0629
  -3.500   0.5657   0.01843   0.00971  -0.1907   0.5814   0.0636
  -3.250   0.5931   0.01811   0.00929  -0.1908   0.5754   0.0644
  -3.000   0.6205   0.01783   0.00892  -0.1908   0.5692   0.0654
  -2.750   0.6479   0.01763   0.00859  -0.1908   0.5638   0.0668
  -2.500   0.6753   0.01743   0.00830  -0.1908   0.5585   0.0681
  -2.250   0.7025   0.01725   0.00804  -0.1908   0.5528   0.0691
  -2.000   0.7297   0.01712   0.00780  -0.1907   0.5477   0.0700
  -1.750   0.7571   0.01691   0.00754  -0.1908   0.5432   0.0711
  -1.500   0.7842   0.01675   0.00740  -0.1908   0.5380   0.0725
  -1.250   0.8113   0.01667   0.00729  -0.1907   0.5331   0.0741
  -1.000   0.8384   0.01665   0.00720  -0.1907   0.5288   0.0763
  -0.750   0.8656   0.01665   0.00715  -0.1907   0.5247   0.0789
  -0.500   0.8925   0.01663   0.00712  -0.1906   0.5202   0.0814
  -0.250   0.9195   0.01661   0.00709  -0.1906   0.5158   0.0848
   0.000   0.9463   0.01665   0.00708  -0.1905   0.5117   0.0889
   0.250   0.9733   0.01671   0.00709  -0.1904   0.5079   0.0950
   0.500   0.9997   0.01671   0.00720  -0.1903   0.5037   0.1105
   0.750   1.0261   0.01672   0.00732  -0.1903   0.4996   0.1506
   1.000   1.0525   0.01674   0.00742  -0.1902   0.4958   0.1935
   1.250   1.0791   0.01678   0.00758  -0.1903   0.4922   0.2580
   1.500   1.1044   0.01687   0.00785  -0.1900   0.4882   0.3349
   1.750   1.1289   0.01702   0.00807  -0.1895   0.4839   0.3729
   2.000   1.1535   0.01718   0.00825  -0.1891   0.4799   0.4004
   2.250   1.1784   0.01735   0.00842  -0.1887   0.4764   0.4254
   2.500   1.2034   0.01750   0.00862  -0.1883   0.4731   0.4557
   2.750   1.2267   0.01763   0.00891  -0.1877   0.4692   0.4919
   3.000   1.2497   0.01777   0.00919  -0.1870   0.4651   0.5391
   3.250   1.2730   0.01793   0.00942  -0.1864   0.4611   0.5924
   3.500   1.2963   0.01806   0.00963  -0.1857   0.4576   0.6530
   3.750   1.3148   0.01796   0.00988  -0.1839   0.4539   0.8084
   4.000   1.3353   0.01808   0.01007  -0.1827   0.4498   1.0000
   4.250   1.3571   0.01838   0.01033  -0.1819   0.4460   1.0000
   4.500   1.3782   0.01868   0.01056  -0.1809   0.4426   1.0000
   4.750   1.3996   0.01901   0.01080  -0.1800   0.4394   1.0000
   5.000   1.4177   0.01935   0.01118  -0.1786   0.4354   1.0000
   5.250   1.4358   0.01970   0.01154  -0.1772   0.4314   1.0000
   5.500   1.4541   0.02008   0.01187  -0.1759   0.4275   1.0000
   5.750   1.4731   0.02046   0.01220  -0.1747   0.4240   1.0000
   6.000   1.4904   0.02089   0.01264  -0.1733   0.4203   1.0000
   6.250   1.5071   0.02135   0.01314  -0.1718   0.4164   1.0000
   6.500   1.5239   0.02182   0.01361  -0.1705   0.4127   1.0000
   6.750   1.5412   0.02230   0.01407  -0.1692   0.4094   1.0000
   7.000   1.5595   0.02279   0.01451  -0.1681   0.4064   1.0000
   7.250   1.5742   0.02339   0.01518  -0.1666   0.4027   1.0000
   7.500   1.5890   0.02400   0.01584  -0.1651   0.3989   1.0000
   7.750   1.6040   0.02463   0.01647  -0.1637   0.3953   1.0000
   8.000   1.6198   0.02524   0.01706  -0.1624   0.3919   1.0000
   8.250   1.6348   0.02593   0.01777  -0.1612   0.3886   1.0000
   8.500   1.6477   0.02674   0.01866  -0.1597   0.3851   1.0000
   8.750   1.6611   0.02753   0.01950  -0.1584   0.3817   1.0000
   9.000   1.6753   0.02832   0.02031  -0.1571   0.3786   1.0000
   9.250   1.6909   0.02906   0.02103  -0.1561   0.3758   1.0000
   9.500   1.7058   0.02987   0.02188  -0.1550   0.3730   1.0000
   9.750   1.7158   0.03096   0.02307  -0.1535   0.3697   1.0000
  10.000   1.7262   0.03204   0.02423  -0.1521   0.3661   1.0000
  10.250   1.7376   0.03308   0.02529  -0.1509   0.3626   1.0000
  10.500   1.7512   0.03398   0.02618  -0.1498   0.3593   1.0000
  10.750   1.7601   0.03524   0.02752  -0.1484   0.3556   1.0000
  11.000   1.7639   0.03685   0.02925  -0.1468   0.3510   1.0000
  11.250   1.7701   0.03830   0.03072  -0.1453   0.3461   1.0000
  11.500   1.7781   0.03964   0.03202  -0.1441   0.3410   1.0000
  11.750   1.7767   0.04183   0.03438  -0.1424   0.3354   1.0000
  12.000   1.7797   0.04371   0.03629  -0.1410   0.3299   1.0000
  12.250   1.7875   0.04522   0.03777  -0.1400   0.3253   1.0000
  12.500   1.7861   0.04772   0.04043  -0.1387   0.3203   1.0000
  12.750   1.7881   0.04994   0.04273  -0.1376   0.3155   1.0000
  13.000   1.7930   0.05187   0.04466  -0.1367   0.3107   1.0000
  13.250   1.7916   0.05463   0.04755  -0.1357   0.3057   1.0000
  13.500   1.7896   0.05751   0.05053  -0.1349   0.3001   1.0000
  13.750   1.7916   0.05995   0.05298  -0.1341   0.2952   1.0000
  14.000   1.7892   0.06308   0.05624  -0.1335   0.2903   1.0000
  14.250   1.7855   0.06645   0.05973  -0.1330   0.2851   1.0000
  14.500   1.7853   0.06936   0.06268  -0.1326   0.2796   1.0000
  14.750   1.7786   0.07327   0.06673  -0.1323   0.2740   1.0000
  15.000   1.7709   0.07740   0.07095  -0.1322   0.2675   1.0000
  15.250   1.7641   0.08144   0.07506  -0.1321   0.2607   1.0000
  15.500   1.7533   0.08619   0.07992  -0.1323   0.2532   1.0000
  15.750   1.7444   0.09069   0.08448  -0.1325   0.2458   1.0000
  16.000   1.7322   0.09579   0.08967  -0.1329   0.2373   1.0000
  16.250   1.7219   0.10067   0.09463  -0.1334   0.2290   1.0000
  16.500   1.7107   0.10569   0.09967  -0.1341   0.2196   1.0000
  16.750   1.6979   0.11105   0.10511  -0.1350   0.2094   1.0000
  17.000   1.6848   0.11649   0.11057  -0.1360   0.1981   1.0000
  17.250   1.6705   0.12215   0.11622  -0.1372   0.1862   1.0000
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