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GOE 502 AIRFOIL (goe502-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 502 AIRFOIL (goe502-il)
Reynolds number: 200,000
Max Cl/Cd: 75.12 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe502-il-200000-n5.txt
Download as CSV file: xf-goe502-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3967   0.04537   0.04008  -0.1397   0.9356   0.0444
 -10.750  -0.4027   0.03812   0.03243  -0.1527   0.9249   0.0446
 -10.500  -0.3975   0.03509   0.02909  -0.1560   0.9156   0.0449
 -10.250  -0.3801   0.03260   0.02628  -0.1592   0.9095   0.0454
 -10.000  -0.3541   0.03044   0.02377  -0.1626   0.9057   0.0458
  -9.750  -0.3416   0.02925   0.02245  -0.1615   0.8961   0.0462
  -9.500  -0.3144   0.02806   0.02123  -0.1627   0.8911   0.0468
  -9.250  -0.2825   0.02686   0.01995  -0.1648   0.8873   0.0475
  -9.000  -0.2673   0.02603   0.01904  -0.1634   0.8764   0.0481
  -8.750  -0.2376   0.02494   0.01780  -0.1647   0.8698   0.0488
  -8.500  -0.2183   0.02410   0.01685  -0.1638   0.8595   0.0494
  -8.250  -0.1913   0.02319   0.01578  -0.1643   0.8522   0.0501
  -8.000  -0.1683   0.02245   0.01490  -0.1639   0.8441   0.0507
  -7.750  -0.1436   0.02176   0.01406  -0.1638   0.8360   0.0512
  -7.500  -0.1171   0.02092   0.01325  -0.1639   0.8293   0.0519
  -7.250  -0.0950   0.02031   0.01263  -0.1632   0.8203   0.0527
  -7.000  -0.0667   0.01966   0.01194  -0.1636   0.8137   0.0537
  -6.750  -0.0436   0.01915   0.01137  -0.1630   0.8050   0.0548
  -6.500  -0.0160   0.01861   0.01072  -0.1631   0.7976   0.0559
  -6.250   0.0100   0.01817   0.01018  -0.1629   0.7900   0.0568
  -6.000   0.0358   0.01758   0.00959  -0.1628   0.7826   0.0578
  -5.750   0.0638   0.01708   0.00904  -0.1630   0.7762   0.0589
  -5.500   0.0891   0.01669   0.00860  -0.1626   0.7684   0.0602
  -5.250   0.1173   0.01632   0.00812  -0.1628   0.7616   0.0618
  -5.000   0.1442   0.01597   0.00770  -0.1627   0.7551   0.0635
  -4.750   0.1704   0.01560   0.00730  -0.1625   0.7483   0.0655
  -4.500   0.1988   0.01531   0.00690  -0.1626   0.7421   0.0678
  -4.250   0.2255   0.01505   0.00658  -0.1624   0.7356   0.0704
  -4.000   0.2518   0.01477   0.00629  -0.1621   0.7286   0.0743
  -3.750   0.2799   0.01449   0.00600  -0.1622   0.7226   0.0831
  -3.500   0.3064   0.01423   0.00582  -0.1619   0.7166   0.1050
  -3.250   0.3323   0.01405   0.00569  -0.1615   0.7097   0.1274
  -3.000   0.3601   0.01394   0.00556  -0.1614   0.7033   0.1467
  -2.750   0.3871   0.01387   0.00548  -0.1612   0.6971   0.1633
  -2.500   0.4126   0.01381   0.00544  -0.1606   0.6901   0.1764
  -2.250   0.4398   0.01378   0.00539  -0.1603   0.6837   0.1899
  -2.000   0.4668   0.01377   0.00534  -0.1600   0.6773   0.2004
  -1.750   0.4918   0.01375   0.00534  -0.1593   0.6697   0.2115
  -1.500   0.5185   0.01374   0.00531  -0.1589   0.6629   0.2225
  -1.250   0.5445   0.01376   0.00530  -0.1584   0.6561   0.2337
  -1.000   0.5694   0.01375   0.00532  -0.1576   0.6482   0.2442
  -0.750   0.5960   0.01377   0.00529  -0.1572   0.6412   0.2550
  -0.500   0.6205   0.01379   0.00533  -0.1564   0.6334   0.2668
  -0.250   0.6457   0.01381   0.00535  -0.1557   0.6256   0.2782
   0.000   0.6712   0.01386   0.00535  -0.1551   0.6183   0.2902
   0.250   0.6954   0.01388   0.00541  -0.1542   0.6098   0.3010
   0.750   0.7449   0.01397   0.00548  -0.1527   0.5946   0.3220
   1.000   0.7696   0.01404   0.00549  -0.1519   0.5869   0.3325
   1.250   0.7938   0.01409   0.00557  -0.1511   0.5796   0.3427
   1.500   0.8181   0.01417   0.00563  -0.1502   0.5722   0.3543
   1.750   0.8428   0.01425   0.00570  -0.1495   0.5658   0.3659
   2.000   0.8665   0.01435   0.00583  -0.1486   0.5587   0.3782
   2.250   0.8905   0.01445   0.00593  -0.1478   0.5520   0.3913
   2.500   0.9151   0.01457   0.00605  -0.1470   0.5462   0.4049
   2.750   0.9386   0.01468   0.00621  -0.1461   0.5400   0.4200
   3.000   0.9623   0.01481   0.00635  -0.1452   0.5340   0.4363
   3.250   0.9868   0.01496   0.00649  -0.1445   0.5286   0.4535
   3.500   1.0097   0.01507   0.00669  -0.1435   0.5229   0.4721
   3.750   1.0332   0.01520   0.00688  -0.1426   0.5175   0.4933
   4.000   1.0569   0.01534   0.00705  -0.1418   0.5125   0.5178
   4.250   1.0795   0.01545   0.00727  -0.1408   0.5075   0.5495
   4.500   1.1005   0.01550   0.00754  -0.1394   0.5021   0.6076
   4.750   1.1221   0.01531   0.00779  -0.1380   0.4970   0.7891
   5.250   1.1745   0.01564   0.00819  -0.1374   0.4853   1.0000
   5.500   1.1937   0.01589   0.00842  -0.1358   0.4787   1.0000
   5.750   1.2149   0.01618   0.00862  -0.1345   0.4728   1.0000
   6.000   1.2330   0.01645   0.00891  -0.1327   0.4666   1.0000
   6.250   1.2517   0.01673   0.00919  -0.1310   0.4605   1.0000
   6.500   1.2714   0.01703   0.00945  -0.1296   0.4549   1.0000
   6.750   1.2895   0.01734   0.00977  -0.1278   0.4490   1.0000
   7.000   1.3067   0.01765   0.01010  -0.1260   0.4425   1.0000
   7.250   1.3246   0.01800   0.01041  -0.1243   0.4365   1.0000
   7.500   1.3411   0.01835   0.01079  -0.1224   0.4300   1.0000
   7.750   1.3565   0.01872   0.01118  -0.1204   0.4228   1.0000
   8.000   1.3727   0.01913   0.01155  -0.1185   0.4165   1.0000
   8.250   1.3887   0.01954   0.01203  -0.1167   0.4104   1.0000
   8.500   1.4042   0.01998   0.01249  -0.1148   0.4042   1.0000
   8.750   1.4192   0.02046   0.01294  -0.1129   0.3981   1.0000
   9.000   1.4334   0.02097   0.01353  -0.1109   0.3911   1.0000
   9.250   1.4464   0.02153   0.01410  -0.1088   0.3840   1.0000
   9.500   1.4593   0.02213   0.01472  -0.1068   0.3768   1.0000
   9.750   1.4708   0.02279   0.01541  -0.1046   0.3685   1.0000
  10.000   1.4811   0.02353   0.01616  -0.1024   0.3599   1.0000
  10.250   1.4895   0.02438   0.01702  -0.0999   0.3496   1.0000
  10.500   1.4978   0.02528   0.01794  -0.0977   0.3392   1.0000
  10.750   1.5032   0.02637   0.01899  -0.0951   0.3281   1.0000
  11.000   1.5095   0.02749   0.02013  -0.0928   0.3160   1.0000
  11.250   1.5146   0.02874   0.02139  -0.0906   0.3039   1.0000
  11.500   1.5176   0.03017   0.02280  -0.0882   0.2915   1.0000
  11.750   1.5182   0.03185   0.02445  -0.0859   0.2774   1.0000
  12.000   1.5171   0.03376   0.02632  -0.0836   0.2617   1.0000
  12.250   1.5153   0.03584   0.02836  -0.0814   0.2461   1.0000
  12.500   1.5119   0.03817   0.03065  -0.0794   0.2304   1.0000
  12.750   1.5090   0.04060   0.03305  -0.0776   0.2162   1.0000
  13.000   1.5065   0.04308   0.03551  -0.0761   0.2041   1.0000
  13.250   1.5042   0.04566   0.03808  -0.0747   0.1944   1.0000
  13.500   1.5008   0.04843   0.04083  -0.0734   0.1856   1.0000
  13.750   1.5005   0.05098   0.04341  -0.0724   0.1785   1.0000
  14.000   1.4982   0.05379   0.04624  -0.0714   0.1719   1.0000
  14.250   1.4983   0.05645   0.04893  -0.0706   0.1663   1.0000
  14.500   1.4990   0.05911   0.05163  -0.0700   0.1610   1.0000
  14.750   1.4971   0.06209   0.05463  -0.0694   0.1562   1.0000
  15.000   1.4994   0.06467   0.05727  -0.0689   0.1518   1.0000
  15.250   1.5010   0.06739   0.06006  -0.0686   0.1470   1.0000
  15.500   1.4995   0.07051   0.06320  -0.0683   0.1425   1.0000
  15.750   1.5018   0.07324   0.06600  -0.0681   0.1384   1.0000
  16.000   1.5040   0.07603   0.06887  -0.0680   0.1338   1.0000
  16.250   1.5029   0.07924   0.07211  -0.0681   0.1294   1.0000
  16.500   1.5044   0.08219   0.07514  -0.0682   0.1251   1.0000
  16.750   1.5059   0.08517   0.07820  -0.0683   0.1203   1.0000
  17.000   1.5034   0.08872   0.08177  -0.0687   0.1160   1.0000
  17.250   1.5054   0.09170   0.08484  -0.0690   0.1111   1.0000
  17.500   1.5038   0.09520   0.08838  -0.0695   0.1063   1.0000
  17.750   1.5030   0.09861   0.09186  -0.0700   0.1018   1.0000
  18.000   1.5023   0.10205   0.09535  -0.0707   0.0970   1.0000
  18.250   1.4995   0.10580   0.09914  -0.0715   0.0928   1.0000
  18.500   1.4992   0.10919   0.10260  -0.0722   0.0883   1.0000
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