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GOE 501 AIRFOIL (goe501-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 501 AIRFOIL (goe501-il)
Reynolds number: 100,000
Max Cl/Cd: 60.47 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe501-il-100000-n5.txt
Download as CSV file: xf-goe501-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 501 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1500   0.09403   0.08869  -0.0861   0.9487   0.0593
  -9.000  -0.1431   0.08869   0.08332  -0.0919   0.9446   0.0601
  -8.750  -0.1533   0.08340   0.07805  -0.0957   0.9345   0.0608
  -8.500  -0.1295   0.08226   0.07690  -0.0963   0.9316   0.0621
  -8.250  -0.1271   0.07833   0.07296  -0.0991   0.9248   0.0621
  -8.000  -0.1273   0.07481   0.06945  -0.1011   0.9165   0.0624
  -7.750  -0.1106   0.07177   0.06639  -0.1047   0.9128   0.0638
  -7.500  -0.1186   0.06884   0.06348  -0.1050   0.9014   0.0644
  -7.000  -0.1304   0.03979   0.03341  -0.1432   0.8819   0.0663
  -6.750  -0.1200   0.03610   0.02916  -0.1456   0.8733   0.0681
  -6.500  -0.0888   0.03272   0.02496  -0.1500   0.8697   0.0704
  -6.250  -0.0554   0.03094   0.02308  -0.1522   0.8673   0.0720
  -6.000  -0.0293   0.02966   0.02162  -0.1527   0.8619   0.0735
  -5.750  -0.0029   0.02849   0.02025  -0.1531   0.8556   0.0755
  -5.500   0.0332   0.02710   0.01855  -0.1551   0.8521   0.0786
  -5.250   0.0717   0.02575   0.01681  -0.1573   0.8496   0.0812
  -5.000   0.0890   0.02505   0.01612  -0.1557   0.8410   0.0828
  -4.750   0.1208   0.02425   0.01529  -0.1566   0.8373   0.0856
  -4.500   0.1556   0.02346   0.01438  -0.1580   0.8347   0.0894
  -4.250   0.1800   0.02298   0.01375  -0.1574   0.8289   0.0924
  -4.000   0.2064   0.02245   0.01324  -0.1573   0.8236   0.0953
  -3.750   0.2396   0.02189   0.01266  -0.1582   0.8201   0.1000
  -3.500   0.2757   0.02127   0.01196  -0.1596   0.8174   0.1059
  -3.250   0.2952   0.02116   0.01189  -0.1582   0.8097   0.1106
  -3.000   0.3265   0.02075   0.01143  -0.1587   0.8051   0.1183
  -2.750   0.3619   0.02027   0.01093  -0.1599   0.8017   0.1307
  -2.500   0.3863   0.02009   0.01077  -0.1593   0.7950   0.1451
  -2.250   0.4153   0.01978   0.01047  -0.1594   0.7892   0.1657
  -2.000   0.4501   0.01933   0.01008  -0.1605   0.7852   0.1931
  -1.750   0.4756   0.01924   0.01002  -0.1600   0.7783   0.2163
  -1.500   0.5040   0.01908   0.00991  -0.1599   0.7718   0.2389
  -1.250   0.5393   0.01880   0.00962  -0.1610   0.7674   0.2668
  -1.000   0.5614   0.01887   0.00974  -0.1598   0.7589   0.2882
  -0.750   0.5926   0.01872   0.00959  -0.1601   0.7527   0.3130
  -0.500   0.6224   0.01862   0.00947  -0.1602   0.7461   0.3375
  -0.250   0.6473   0.01860   0.00950  -0.1595   0.7375   0.3601
   0.000   0.6822   0.01835   0.00922  -0.1604   0.7320   0.3857
   0.250   0.7024   0.01845   0.00937  -0.1589   0.7215   0.4049
   0.500   0.7361   0.01822   0.00912  -0.1596   0.7151   0.4268
   0.750   0.7574   0.01830   0.00926  -0.1583   0.7042   0.4455
   1.000   0.7897   0.01810   0.00906  -0.1587   0.6968   0.4685
   1.250   0.8113   0.01818   0.00921  -0.1574   0.6850   0.4906
   1.500   0.8366   0.01815   0.00924  -0.1567   0.6743   0.5181
   1.750   0.8650   0.01801   0.00915  -0.1564   0.6640   0.5550
   2.000   0.8864   0.01803   0.00928  -0.1551   0.6508   0.6019
   2.250   0.9087   0.01789   0.00936  -0.1537   0.6386   0.6710
   2.500   0.9305   0.01736   0.00921  -0.1520   0.6277   1.0000
   2.750   0.9570   0.01749   0.00921  -0.1516   0.6162   1.0000
   3.000   0.9814   0.01768   0.00931  -0.1509   0.6041   1.0000
   3.250   1.0072   0.01785   0.00936  -0.1503   0.5924   1.0000
   3.500   1.0341   0.01799   0.00936  -0.1500   0.5814   1.0000
   3.750   1.0590   0.01823   0.00951  -0.1494   0.5704   1.0000
   4.000   1.0845   0.01848   0.00967  -0.1489   0.5609   1.0000
   4.250   1.1108   0.01874   0.00983  -0.1485   0.5521   1.0000
   4.500   1.1352   0.01907   0.01012  -0.1479   0.5436   1.0000
   4.750   1.1612   0.01938   0.01036  -0.1475   0.5360   1.0000
   5.000   1.1861   0.01973   0.01068  -0.1470   0.5288   1.0000
   5.250   1.2103   0.02010   0.01104  -0.1464   0.5212   1.0000
   5.500   1.2360   0.02046   0.01134  -0.1460   0.5140   1.0000
   5.750   1.2578   0.02087   0.01179  -0.1450   0.5060   1.0000
   6.000   1.2843   0.02124   0.01211  -0.1448   0.4997   1.0000
   6.250   1.3055   0.02169   0.01263  -0.1438   0.4929   1.0000
   6.500   1.3279   0.02211   0.01309  -0.1429   0.4859   1.0000
   6.750   1.3509   0.02253   0.01352  -0.1421   0.4786   1.0000
   7.000   1.3690   0.02300   0.01407  -0.1405   0.4703   1.0000
   7.250   1.3922   0.02341   0.01446  -0.1398   0.4632   1.0000
   7.500   1.4063   0.02392   0.01509  -0.1376   0.4543   1.0000
   7.750   1.4270   0.02433   0.01550  -0.1364   0.4465   1.0000
   8.000   1.4384   0.02489   0.01620  -0.1338   0.4379   1.0000
   8.250   1.4555   0.02535   0.01666  -0.1320   0.4293   1.0000
   8.500   1.4642   0.02598   0.01742  -0.1291   0.4188   1.0000
   8.750   1.4749   0.02660   0.01810  -0.1265   0.4079   1.0000
   9.000   1.4849   0.02724   0.01875  -0.1239   0.3963   1.0000
   9.250   1.4912   0.02806   0.01969  -0.1210   0.3835   1.0000
   9.500   1.4983   0.02893   0.02064  -0.1182   0.3707   1.0000
   9.750   1.5050   0.02988   0.02165  -0.1156   0.3573   1.0000
  10.000   1.5103   0.03096   0.02279  -0.1129   0.3424   1.0000
  10.250   1.5140   0.03220   0.02407  -0.1102   0.3254   1.0000
  10.500   1.5160   0.03364   0.02551  -0.1075   0.3060   1.0000
  10.750   1.5164   0.03528   0.02711  -0.1048   0.2856   1.0000
  11.000   1.5158   0.03713   0.02892  -0.1023   0.2656   1.0000
  11.250   1.5145   0.03918   0.03092  -0.1000   0.2473   1.0000
  11.500   1.5121   0.04143   0.03314  -0.0978   0.2318   1.0000
  11.750   1.5103   0.04378   0.03546  -0.0959   0.2197   1.0000
  12.000   1.5084   0.04624   0.03790  -0.0941   0.2100   1.0000
  12.250   1.5086   0.04863   0.04033  -0.0926   0.2013   1.0000
  12.500   1.5074   0.05122   0.04292  -0.0912   0.1939   1.0000
  12.750   1.5080   0.05374   0.04551  -0.0900   0.1864   1.0000
  13.000   1.5068   0.05648   0.04822  -0.0888   0.1799   1.0000
  13.250   1.5092   0.05899   0.05089  -0.0880   0.1729   1.0000
  13.500   1.5091   0.06176   0.05367  -0.0871   0.1663   1.0000
  13.750   1.5113   0.06440   0.05643  -0.0864   0.1597   1.0000
  14.000   1.5115   0.06733   0.05947  -0.0858   0.1526   1.0000
  14.250   1.5118   0.07029   0.06249  -0.0854   0.1458   1.0000
  14.500   1.5111   0.07359   0.06597  -0.0852   0.1377   1.0000
  14.750   1.5094   0.07702   0.06951  -0.0852   0.1303   1.0000
  15.000   1.5068   0.08073   0.07336  -0.0854   0.1222   1.0000
  15.250   1.5045   0.08448   0.07723  -0.0858   0.1142   1.0000
  15.500   1.4996   0.08869   0.08148  -0.0865   0.1073   1.0000
  15.750   1.4959   0.09279   0.08567  -0.0872   0.1002   1.0000
  16.000   1.4906   0.09718   0.09006  -0.0882   0.0946   1.0000
  16.250   1.4866   0.10139   0.09431  -0.0892   0.0893   1.0000
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