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GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il)
Reynolds number: 200,000
Max Cl/Cd: 60.81 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe235-il-200000.txt
Download as CSV file: xf-goe235-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 235 (SCHTTE-LANZ) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4676   0.11464   0.11088   0.0058   1.0000   0.0368
  -9.000  -0.4680   0.11246   0.10873   0.0009   1.0000   0.0371
  -8.750  -0.4679   0.10993   0.10624  -0.0042   1.0000   0.0372
  -8.500  -0.4590   0.10542   0.10175  -0.0042   1.0000   0.0374
  -8.250  -0.4454   0.10108   0.09740  -0.0019   1.0000   0.0378
  -8.000  -0.4358   0.09772   0.09407  -0.0019   1.0000   0.0383
  -7.750  -0.4278   0.09467   0.09104  -0.0029   1.0000   0.0389
  -7.500  -0.4206   0.09167   0.08807  -0.0045   1.0000   0.0396
  -7.250  -0.4125   0.08855   0.08497  -0.0070   1.0000   0.0403
  -7.000  -0.4013   0.08517   0.08161  -0.0105   1.0000   0.0412
  -6.750  -0.3874   0.08163   0.07808  -0.0155   1.0000   0.0423
  -6.500  -0.3566   0.07739   0.07370  -0.0319   1.0000   0.0435
  -6.250  -0.3398   0.07291   0.06919  -0.0357   1.0000   0.0438
  -6.000  -0.3311   0.06940   0.06576  -0.0338   1.0000   0.0441
  -5.750  -0.3193   0.06641   0.06280  -0.0333   1.0000   0.0446
  -5.500  -0.3059   0.06363   0.06004  -0.0337   1.0000   0.0454
  -5.250  -0.2924   0.06098   0.05740  -0.0347   1.0000   0.0465
  -5.000  -0.2810   0.05850   0.05491  -0.0354   1.0000   0.0477
  -4.750  -0.2733   0.05633   0.05271  -0.0354   1.0000   0.0490
  -4.500  -0.2335   0.05334   0.04918  -0.0433   0.9985   0.0513
  -4.250  -0.2079   0.04865   0.04464  -0.0459   0.9946   0.0520
  -4.000  -0.1762   0.04551   0.04151  -0.0492   0.9896   0.0531
  -3.750  -0.1372   0.04249   0.03840  -0.0538   0.9851   0.0552
  -3.500  -0.0804   0.03930   0.03457  -0.0610   0.9794   0.0606
  -3.250  -0.0449   0.03561   0.03104  -0.0649   0.9739   0.0623
  -3.000  -0.0047   0.03323   0.02858  -0.0686   0.9657   0.0658
  -2.750   0.0419   0.03063   0.02551  -0.0726   0.9571   0.0724
  -2.500   0.0709   0.02848   0.02340  -0.0738   0.9438   0.0748
  -2.000   0.1190   0.01010   0.00500  -0.0691   0.8828   0.0880
  -1.750   0.1442   0.00927   0.00383  -0.0683   0.8678   0.0997
  -1.500   0.1658   0.00818   0.00278  -0.0677   0.8539   0.1046
  -1.250   0.1900   0.00738   0.00183  -0.0672   0.8415   0.1189
  -1.000   0.2138   0.00673   0.00108  -0.0667   0.8301   0.1376
  -0.750   0.2378   0.00610   0.00039  -0.0664   0.8165   0.1662
  -0.500   0.2738   0.01907   0.01305  -0.0699   0.8254   0.1892
   0.250   0.3685   0.01585   0.00860  -0.0666   0.7856   0.0945
   0.500   0.3972   0.01511   0.00763  -0.0656   0.7709   0.0815
   0.750   0.4245   0.01433   0.00677  -0.0648   0.7545   0.0794
   1.000   0.4520   0.01366   0.00600  -0.0640   0.7373   0.0754
   1.250   0.4793   0.01318   0.00544  -0.0633   0.7198   0.0736
   1.500   0.5062   0.01273   0.00497  -0.0625   0.7007   0.0736
   1.750   0.5326   0.01236   0.00457  -0.0617   0.6741   0.0750
   2.000   0.5584   0.01217   0.00428  -0.0608   0.6406   0.0794
   2.250   0.5844   0.01212   0.00406  -0.0600   0.6037   0.0821
   2.500   0.6111   0.01203   0.00387  -0.0595   0.5582   0.0856
   2.750   0.6352   0.01234   0.00368  -0.0586   0.4421   0.0935
   3.000   0.6588   0.01303   0.00385  -0.0580   0.3392   0.1157
   3.250   0.6802   0.01174   0.00405  -0.0569   0.2881   1.0000
   3.500   0.7062   0.01224   0.00427  -0.0565   0.2664   1.0000
   3.750   0.7325   0.01266   0.00453  -0.0562   0.2529   1.0000
   4.000   0.7589   0.01304   0.00480  -0.0560   0.2400   1.0000
   4.250   0.7852   0.01340   0.00509  -0.0557   0.2298   1.0000
   4.500   0.8113   0.01379   0.00540  -0.0554   0.2174   1.0000
   4.750   0.8375   0.01413   0.00567  -0.0551   0.2020   1.0000
   5.000   0.8642   0.01437   0.00588  -0.0549   0.1832   1.0000
   5.250   0.8908   0.01465   0.00607  -0.0546   0.1567   1.0000
   5.500   0.9134   0.01571   0.00658  -0.0541   0.0750   1.0000
   5.750   0.9380   0.01644   0.00729  -0.0535   0.0671   1.0000
   6.000   0.9626   0.01711   0.00801  -0.0529   0.0628   1.0000
   6.250   0.9860   0.01797   0.00888  -0.0522   0.0594   1.0000
   6.500   1.0103   0.01861   0.00960  -0.0516   0.0579   1.0000
   6.750   1.0337   0.01935   0.01040  -0.0509   0.0566   1.0000
   7.000   1.0564   0.02018   0.01128  -0.0502   0.0554   1.0000
   7.250   1.0784   0.02110   0.01222  -0.0493   0.0544   1.0000
   7.500   1.1000   0.02210   0.01322  -0.0484   0.0534   1.0000
   7.750   1.1211   0.02323   0.01432  -0.0475   0.0522   1.0000
   8.000   1.1419   0.02467   0.01572  -0.0466   0.0510   1.0000
   8.250   1.1639   0.02644   0.01745  -0.0458   0.0502   1.0000
   8.500   1.1873   0.02782   0.01888  -0.0451   0.0499   1.0000
   8.750   1.2107   0.02917   0.02033  -0.0444   0.0496   1.0000
   9.000   1.2337   0.03059   0.02188  -0.0436   0.0493   1.0000
   9.250   1.2558   0.03200   0.02346  -0.0428   0.0487   1.0000
   9.500   1.2771   0.03355   0.02520  -0.0419   0.0481   1.0000
   9.750   1.2977   0.03548   0.02733  -0.0410   0.0479   1.0000
  10.000   1.3169   0.03768   0.02978  -0.0400   0.0479   1.0000
  10.250   1.3341   0.04014   0.03251  -0.0388   0.0481   1.0000
  10.500   1.3486   0.04270   0.03538  -0.0374   0.0481   1.0000
  10.750   1.3602   0.04540   0.03838  -0.0359   0.0479   1.0000
  11.000   1.3688   0.04850   0.04181  -0.0342   0.0481   1.0000
  11.250   1.3745   0.05256   0.04618  -0.0326   0.0489   1.0000
  11.500   1.3917   0.05716   0.05088  -0.0322   0.0506   1.0000
  11.750   1.3402   0.06180   0.05666  -0.0258   0.0562   1.0000
  12.000   1.2472   0.05462   0.04958  -0.0137   0.0529   1.0000
  12.250   1.2018   0.06012   0.05544  -0.0115   0.0541   1.0000
  12.500   1.1631   0.06635   0.06193  -0.0113   0.0548   1.0000
  12.750   1.1243   0.07342   0.06921  -0.0127   0.0552   1.0000
  13.000   1.0824   0.08166   0.07765  -0.0157   0.0555   1.0000
  13.250   1.0330   0.09186   0.08803  -0.0210   0.0556   1.0000
  13.500   0.9651   0.10690   0.10325  -0.0299   0.0575   1.0000
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