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GOE 502 AIRFOIL (goe502-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 502 AIRFOIL (goe502-il)
Reynolds number: 200,000
Max Cl/Cd: 75.95 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe502-il-200000.txt
Download as CSV file: xf-goe502-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 502 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0506   0.10185   0.09795  -0.0916   0.9558   0.0995
  -9.250  -0.2968   0.04707   0.04251  -0.1442   0.9239   0.0701
  -9.000  -0.2991   0.04181   0.03694  -0.1481   0.9119   0.0696
  -8.750  -0.2784   0.03639   0.03103  -0.1547   0.9076   0.0693
  -8.500  -0.2473   0.03252   0.02665  -0.1600   0.9053   0.0694
  -8.250  -0.2397   0.03085   0.02468  -0.1582   0.8938   0.0697
  -8.000  -0.2077   0.02866   0.02205  -0.1609   0.8904   0.0705
  -7.750  -0.1716   0.02659   0.01987  -0.1635   0.8881   0.0714
  -7.500  -0.1523   0.02557   0.01877  -0.1624   0.8802   0.0721
  -7.250  -0.1242   0.02444   0.01752  -0.1629   0.8746   0.0730
  -7.000  -0.0889   0.02323   0.01617  -0.1646   0.8712   0.0741
  -6.750  -0.0513   0.02209   0.01489  -0.1666   0.8685   0.0754
  -6.500  -0.0358   0.02158   0.01428  -0.1644   0.8592   0.0765
  -6.250  -0.0049   0.02073   0.01329  -0.1651   0.8543   0.0781
  -6.000   0.0302   0.01977   0.01239  -0.1665   0.8509   0.0803
  -5.750   0.0538   0.01928   0.01188  -0.1657   0.8440   0.0821
  -5.500   0.0795   0.01872   0.01128  -0.1652   0.8373   0.0841
  -5.250   0.1133   0.01802   0.01051  -0.1662   0.8330   0.0865
  -5.000   0.1420   0.01751   0.01003  -0.1664   0.8277   0.0898
  -4.750   0.1645   0.01719   0.00968  -0.1652   0.8198   0.0937
  -4.500   0.1973   0.01660   0.00911  -0.1660   0.8149   0.0990
  -4.250   0.2263   0.01618   0.00866  -0.1661   0.8090   0.1061
  -4.000   0.2503   0.01581   0.00834  -0.1653   0.8013   0.1173
  -3.750   0.2830   0.01526   0.00789  -0.1661   0.7961   0.1464
  -3.500   0.3102   0.01510   0.00779  -0.1659   0.7892   0.1785
  -3.250   0.3380   0.01506   0.00770  -0.1656   0.7817   0.1986
  -3.000   0.3724   0.01497   0.00753  -0.1665   0.7761   0.2144
  -2.750   0.3961   0.01504   0.00760  -0.1656   0.7678   0.2264
  -2.500   0.4265   0.01502   0.00745  -0.1657   0.7607   0.2386
  -2.250   0.4565   0.01499   0.00742  -0.1659   0.7537   0.2489
  -2.000   0.4818   0.01498   0.00736  -0.1652   0.7450   0.2591
  -1.750   0.5144   0.01499   0.00730  -0.1658   0.7385   0.2713
  -1.500   0.5376   0.01502   0.00735  -0.1647   0.7295   0.2816
  -1.250   0.5670   0.01503   0.00728  -0.1647   0.7218   0.2931
  -1.000   0.5941   0.01504   0.00729  -0.1644   0.7140   0.3041
  -0.750   0.6197   0.01513   0.00730  -0.1637   0.7054   0.3165
  -0.500   0.6514   0.01512   0.00728  -0.1642   0.6987   0.3299
  -0.250   0.6722   0.01517   0.00737  -0.1627   0.6894   0.3419
   0.000   0.7007   0.01521   0.00736  -0.1626   0.6820   0.3553
   0.250   0.7262   0.01524   0.00742  -0.1620   0.6745   0.3667
   0.500   0.7510   0.01529   0.00743  -0.1612   0.6662   0.3788
   0.750   0.7811   0.01527   0.00739  -0.1614   0.6599   0.3910
   1.000   0.8023   0.01534   0.00751  -0.1600   0.6515   0.4032
   1.250   0.8289   0.01535   0.00752  -0.1595   0.6445   0.4169
   1.500   0.8566   0.01539   0.00756  -0.1593   0.6382   0.4309
   1.750   0.8786   0.01544   0.00766  -0.1581   0.6302   0.4453
   2.000   0.9062   0.01546   0.00765  -0.1578   0.6240   0.4623
   2.250   0.9312   0.01551   0.00776  -0.1572   0.6176   0.4796
   2.500   0.9543   0.01553   0.00786  -0.1561   0.6103   0.4989
   2.750   0.9820   0.01549   0.00785  -0.1560   0.6045   0.5225
   3.000   1.0049   0.01552   0.00803  -0.1549   0.5981   0.5500
   3.250   1.0281   0.01549   0.00818  -0.1539   0.5915   0.5903
   3.500   1.0530   0.01534   0.00827  -0.1531   0.5861   0.6758
   3.750   1.0868   0.01503   0.00842  -0.1540   0.5796   1.0000
   4.000   1.1111   0.01525   0.00857  -0.1533   0.5731   1.0000
   4.250   1.1400   0.01547   0.00866  -0.1535   0.5678   1.0000
   4.500   1.1646   0.01577   0.00892  -0.1528   0.5620   1.0000
   4.750   1.1870   0.01602   0.00915  -0.1518   0.5554   1.0000
   5.000   1.2154   0.01622   0.00923  -0.1517   0.5490   1.0000
   5.250   1.2367   0.01652   0.00953  -0.1505   0.5422   1.0000
   5.500   1.2591   0.01676   0.00975  -0.1494   0.5353   1.0000
   5.750   1.2895   0.01703   0.00988  -0.1498   0.5292   1.0000
   6.000   1.3058   0.01732   0.01025  -0.1476   0.5222   1.0000
   6.250   1.3286   0.01758   0.01048  -0.1467   0.5156   1.0000
   6.500   1.3603   0.01791   0.01069  -0.1474   0.5099   1.0000
   6.750   1.3728   0.01821   0.01110  -0.1445   0.5030   1.0000
   7.000   1.3946   0.01846   0.01132  -0.1434   0.4963   1.0000
   7.250   1.4222   0.01879   0.01158  -0.1433   0.4902   1.0000
   7.500   1.4342   0.01909   0.01199  -0.1404   0.4834   1.0000
   7.750   1.4554   0.01936   0.01224  -0.1392   0.4772   1.0000
   8.000   1.4813   0.01970   0.01253  -0.1389   0.4714   1.0000
   8.250   1.4910   0.02004   0.01298  -0.1356   0.4648   1.0000
   8.500   1.5090   0.02031   0.01326  -0.1338   0.4588   1.0000
   8.750   1.5338   0.02064   0.01354  -0.1333   0.4530   1.0000
   9.000   1.5374   0.02101   0.01404  -0.1290   0.4466   1.0000
   9.250   1.5513   0.02128   0.01431  -0.1265   0.4398   1.0000
   9.500   1.5647   0.02163   0.01467  -0.1241   0.4327   1.0000
   9.750   1.5687   0.02203   0.01515  -0.1201   0.4248   1.0000
  10.000   1.5861   0.02233   0.01537  -0.1183   0.4173   1.0000
  10.250   1.5854   0.02293   0.01612  -0.1139   0.4092   1.0000
  10.500   1.5974   0.02333   0.01646  -0.1115   0.4010   1.0000
  10.750   1.5979   0.02407   0.01733  -0.1075   0.3921   1.0000
  11.000   1.6069   0.02464   0.01785  -0.1049   0.3832   1.0000
  11.250   1.6065   0.02558   0.01892  -0.1012   0.3732   1.0000
  11.500   1.6117   0.02642   0.01973  -0.0984   0.3632   1.0000
  11.750   1.6122   0.02753   0.02090  -0.0952   0.3519   1.0000
  12.000   1.6132   0.02875   0.02215  -0.0922   0.3402   1.0000
  12.250   1.6138   0.03009   0.02347  -0.0894   0.3282   1.0000
  12.500   1.6118   0.03169   0.02506  -0.0865   0.3150   1.0000
  12.750   1.6082   0.03354   0.02694  -0.0838   0.3004   1.0000
  13.000   1.6036   0.03562   0.02900  -0.0813   0.2854   1.0000
  13.250   1.5979   0.03796   0.03131  -0.0789   0.2700   1.0000
  13.500   1.5918   0.04048   0.03379  -0.0768   0.2552   1.0000
  13.750   1.5858   0.04315   0.03642  -0.0749   0.2417   1.0000
  14.000   1.5804   0.04589   0.03910  -0.0733   0.2301   1.0000
  14.250   1.5758   0.04866   0.04183  -0.0718   0.2194   1.0000
  14.500   1.5738   0.05130   0.04449  -0.0707   0.2100   1.0000
  15.000   1.5696   0.05680   0.04997  -0.0687   0.1940   1.0000
  15.250   1.5677   0.05955   0.05265  -0.0678   0.1874   1.0000
  15.500   1.5676   0.06232   0.05551  -0.0672   0.1803   1.0000
  15.750   1.5667   0.06510   0.05824  -0.0665   0.1739   1.0000
  16.000   1.5666   0.06794   0.06116  -0.0661   0.1675   1.0000
  16.250   1.5655   0.07090   0.06412  -0.0658   0.1612   1.0000
  16.500   1.5653   0.07379   0.06703  -0.0654   0.1549   1.0000
  16.750   1.5627   0.07711   0.07042  -0.0654   0.1485   1.0000
  17.000   1.5620   0.08012   0.07340  -0.0653   0.1423   1.0000
  17.250   1.5580   0.08380   0.07718  -0.0655   0.1358   1.0000
  17.500   1.5565   0.08697   0.08031  -0.0656   0.1297   1.0000
  17.750   1.5524   0.09078   0.08424  -0.0661   0.1236   1.0000
  18.000   1.5512   0.09401   0.08740  -0.0664   0.1181   1.0000
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