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GOE 462 AIRFOIL (goe462-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 462 AIRFOIL (goe462-il)
Reynolds number: 100,000
Max Cl/Cd: 52.26 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe462-il-100000.txt
Download as CSV file: xf-goe462-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500   0.1961   0.10232   0.09848  -0.0845   0.8929   0.0496
  -8.250   0.2207   0.09829   0.09435  -0.0874   0.8715   0.0514
  -8.000   0.2405   0.09563   0.09159  -0.0899   0.8482   0.0538
  -7.750   0.2565   0.09352   0.08936  -0.0916   0.8271   0.0562
  -7.500   0.2647   0.09303   0.08881  -0.0924   0.8044   0.0580
  -7.250   0.2685   0.09388   0.08960  -0.0929   0.7838   0.0585
  -6.750   0.2896   0.08764   0.08323  -0.0925   0.7519   0.0598
  -6.500   0.3009   0.08501   0.08052  -0.0920   0.7368   0.0613
  -6.250   0.3122   0.08321   0.07864  -0.0921   0.7228   0.0628
  -6.000   0.3243   0.08149   0.07683  -0.0927   0.7101   0.0651
  -5.750   0.3369   0.08014   0.07540  -0.0939   0.6968   0.0676
  -5.500   0.3542   0.08069   0.07589  -0.0979   0.6834   0.0691
  -5.250   0.3684   0.07848   0.07364  -0.0995   0.6717   0.0700
  -5.000   0.3791   0.07478   0.06982  -0.0976   0.6615   0.0716
  -4.750   0.3932   0.07289   0.06789  -0.0979   0.6496   0.0743
  -4.500   0.4100   0.07130   0.06625  -0.0995   0.6384   0.0773
  -4.250   0.4414   0.07131   0.06608  -0.1061   0.6279   0.0802
  -4.000   0.4640   0.06949   0.06420  -0.1095   0.6167   0.0810
  -3.750   0.4718   0.06611   0.06080  -0.1071   0.6068   0.0823
  -3.500   0.4912   0.06400   0.05853  -0.1080   0.5976   0.0853
  -3.250   0.5178   0.06289   0.05738  -0.1116   0.5861   0.0905
  -3.000   0.5581   0.06196   0.05628  -0.1191   0.5759   0.0922
  -2.750   0.5694   0.05893   0.05320  -0.1176   0.5673   0.0938
  -2.500   0.5913   0.05715   0.05136  -0.1189   0.5577   0.0968
  -2.250   0.6566   0.05742   0.05124  -0.1313   0.5476   0.1030
  -2.000   0.6623   0.05411   0.04805  -0.1286   0.5384   0.1041
  -1.750   0.6879   0.05200   0.04572  -0.1301   0.5312   0.1070
  -1.500   0.7575   0.05319   0.04669  -0.1423   0.5195   0.1139
  -1.250   0.7677   0.04937   0.04277  -0.1404   0.5140   0.1151
  -1.000   0.7899   0.04769   0.04114  -0.1411   0.5052   0.1177
  -0.500   0.8734   0.04553   0.03862  -0.1508   0.4893   0.1263
  -0.250   0.9032   0.04380   0.03672  -0.1527   0.4832   0.1296
   0.000   0.9658   0.04524   0.03789  -0.1609   0.4746   0.1366
   0.250   0.9810   0.04202   0.03468  -0.1602   0.4694   0.1389
   0.500   1.0182   0.04105   0.03347  -0.1631   0.4642   0.1453
   0.750   1.0575   0.04057   0.03294  -0.1668   0.4567   0.1502
   1.000   1.0539   0.02495   0.01756  -0.1591   0.4457   0.1616
   1.250   1.0778   0.02402   0.01666  -0.1600   0.4402   0.1689
   1.500   1.1163   0.02365   0.01606  -0.1631   0.4356   0.1768
   1.750   1.1561   0.02487   0.01695  -0.1654   0.4312   0.1861
   2.000   1.1774   0.02411   0.01635  -0.1663   0.4262   0.1890
   2.250   1.2070   0.02419   0.01632  -0.1675   0.4215   0.1948
   2.500   1.2428   0.02427   0.01611  -0.1693   0.4176   0.1991
   2.750   1.2658   0.02464   0.01655  -0.1698   0.4130   0.2036
   3.000   1.2923   0.02634   0.01821  -0.1700   0.4081   0.2100
   3.250   1.3197   0.02576   0.01759  -0.1712   0.4045   0.2130
   3.500   1.3504   0.02584   0.01748  -0.1721   0.4015   0.2197
   3.750   1.3723   0.02719   0.01889  -0.1722   0.3977   0.2232
   4.000   1.3908   0.02834   0.02018  -0.1719   0.3933   0.2280
   4.250   1.4165   0.02901   0.02079  -0.1722   0.3895   0.2360
   4.500   1.4459   0.02949   0.02110  -0.1725   0.3864   0.2458
   4.750   1.4714   0.02963   0.02121  -0.1732   0.3834   0.2513
   5.000   1.4779   0.03291   0.02476  -0.1712   0.3792   0.2582
   5.250   1.4934   0.03414   0.02612  -0.1708   0.3758   0.2638
   5.500   1.5161   0.03503   0.02701  -0.1707   0.3729   0.2740
   5.750   1.5441   0.03527   0.02716  -0.1713   0.3704   0.2902
   6.000   1.5716   0.03576   0.02755  -0.1718   0.3680   0.3145
   6.250   1.5351   0.04294   0.03532  -0.1660   0.3636   0.3105
   6.750   1.6632   0.05000   0.04179  -0.1778   0.3599   0.3814
   7.000   1.6872   0.05049   0.04227  -0.1780   0.3571   0.4146
   7.250   1.7152   0.05082   0.04250  -0.1783   0.3548   0.4427
   7.500   1.7491   0.05084   0.04233  -0.1791   0.3527   0.4671
   8.250   1.8030   0.05007   0.04149  -0.1749   0.3348   0.5155
   8.500   1.7682   0.05516   0.04705  -0.1695   0.3326   0.5136
   8.750   1.8670   0.04657   0.03760  -0.1744   0.3196   0.5283
   9.000   1.8521   0.04917   0.04058  -0.1701   0.3158   0.5281
   9.250   1.8541   0.05040   0.04195  -0.1673   0.3116   0.5275
   9.500   1.7088   0.06684   0.05926  -0.1569   0.3180   0.5197
   9.750   1.8810   0.04910   0.04047  -0.1629   0.2979   0.5226
  10.000   1.9238   0.04628   0.03718  -0.1633   0.2888   0.5015
  10.250   1.9016   0.04900   0.04025  -0.1584   0.2863   0.4972
  10.500   1.8815   0.05207   0.04359  -0.1548   0.2833   0.4919
  10.750   1.8731   0.05438   0.04604  -0.1525   0.2795   0.4831
  11.000   1.9013   0.05296   0.04433  -0.1515   0.2729   0.4604
  11.250   1.8736   0.05767   0.04939  -0.1492   0.2705   0.4590
  11.500   1.8442   0.06328   0.05531  -0.1478   0.2682   0.4584
  11.750   1.7983   0.07197   0.06437  -0.1477   0.2672   0.4644
  12.000   1.8367   0.06816   0.06023  -0.1464   0.2567   0.4409
  12.250   1.8010   0.07615   0.06856  -0.1469   0.2559   0.4423
  12.500   1.7498   0.08765   0.08043  -0.1489   0.2569   0.4502
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