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FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 68-H-120 (fx68h120-il)
Reynolds number: 100,000
Max Cl/Cd: 40.97 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx68h120-il-100000-n5.txt
Download as CSV file: xf-fx68h120-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 68-H-120                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5009   0.08700   0.08252  -0.0307   1.0000   0.0215
 -10.500  -0.5285   0.07630   0.07191  -0.0373   1.0000   0.0208
 -10.250  -0.5760   0.06010   0.05559  -0.0518   1.0000   0.0198
 -10.000  -0.6069   0.05278   0.04804  -0.0580   1.0000   0.0193
  -9.750  -0.6290   0.04911   0.04418  -0.0573   1.0000   0.0192
  -9.500  -0.6490   0.04659   0.04148  -0.0540   1.0000   0.0192
  -9.250  -0.6692   0.04480   0.03951  -0.0491   1.0000   0.0192
  -9.000  -0.6769   0.04222   0.03664  -0.0463   0.9960   0.0193
  -8.750  -0.6664   0.03894   0.03294  -0.0466   0.9885   0.0198
  -8.500  -0.6494   0.03598   0.02956  -0.0472   0.9832   0.0204
  -8.250  -0.6317   0.03368   0.02689  -0.0470   0.9775   0.0213
  -8.000  -0.6084   0.03173   0.02455  -0.0475   0.9733   0.0231
  -7.750  -0.5864   0.02988   0.02235  -0.0475   0.9693   0.0245
  -7.500  -0.5677   0.02814   0.02047  -0.0469   0.9645   0.0261
  -7.250  -0.5438   0.02669   0.01883  -0.0469   0.9606   0.0279
  -7.000  -0.5198   0.02544   0.01737  -0.0467   0.9568   0.0301
  -6.750  -0.4999   0.02441   0.01610  -0.0455   0.9519   0.0327
  -6.500  -0.4771   0.02322   0.01482  -0.0451   0.9480   0.0378
  -6.250  -0.4508   0.02210   0.01365  -0.0453   0.9449   0.0491
  -6.000  -0.4328   0.02121   0.01284  -0.0438   0.9396   0.0692
  -5.750  -0.4073   0.02084   0.01255  -0.0437   0.9359   0.1056
  -5.500  -0.3776   0.02088   0.01246  -0.0442   0.9328   0.1326
  -5.250  -0.3531   0.02091   0.01236  -0.0438   0.9287   0.1513
  -5.000  -0.3307   0.02085   0.01218  -0.0429   0.9241   0.1655
  -4.750  -0.3032   0.02066   0.01183  -0.0429   0.9206   0.1777
  -4.500  -0.2735   0.02034   0.01150  -0.0434   0.9178   0.1877
  -4.250  -0.2528   0.02011   0.01117  -0.0422   0.9127   0.1954
  -4.000  -0.2268   0.01986   0.01085  -0.0418   0.9084   0.2045
  -3.750  -0.1975   0.01956   0.01054  -0.0421   0.9050   0.2135
  -3.500  -0.1733   0.01931   0.01024  -0.0413   0.8980   0.2224
  -3.250  -0.1414   0.01895   0.00984  -0.0417   0.8910   0.2344
  -3.000  -0.1171   0.01860   0.00950  -0.0406   0.8809   0.2462
  -2.750  -0.0885   0.01823   0.00914  -0.0403   0.8735   0.2609
  -2.500  -0.0644   0.01792   0.00888  -0.0393   0.8650   0.2801
  -2.250  -0.0397   0.01758   0.00864  -0.0384   0.8574   0.3077
  -2.000  -0.0147   0.01717   0.00839  -0.0375   0.8500   0.3497
  -1.750   0.0081   0.01675   0.00823  -0.0363   0.8418   0.4137
  -1.500   0.0332   0.01612   0.00802  -0.0353   0.8348   0.5196
  -1.250   0.0578   0.01548   0.00797  -0.0340   0.8258   0.6634
  -1.000   0.1363   0.01493   0.00789  -0.0420   0.8204   0.8481
  -0.750   0.1863   0.01486   0.00778  -0.0455   0.8100   0.9066
  -0.500   0.2219   0.01482   0.00764  -0.0462   0.7989   0.9398
  -0.250   0.2622   0.01470   0.00742  -0.0480   0.7862   0.9638
   0.000   0.3049   0.01452   0.00714  -0.0505   0.7704   0.9831
   0.250   0.3568   0.01419   0.00671  -0.0550   0.7510   1.0000
   0.500   0.3772   0.01407   0.00651  -0.0533   0.7295   1.0000
   0.750   0.3977   0.01393   0.00628  -0.0516   0.7045   1.0000
   1.000   0.4184   0.01383   0.00605  -0.0498   0.6713   1.0000
   1.250   0.4389   0.01372   0.00572  -0.0479   0.6275   1.0000
   1.500   0.4589   0.01373   0.00538  -0.0458   0.5752   1.0000
   1.750   0.4787   0.01397   0.00525  -0.0439   0.5268   1.0000
   2.000   0.4988   0.01431   0.00529  -0.0424   0.4877   1.0000
   2.250   0.5195   0.01467   0.00541  -0.0411   0.4557   1.0000
   2.500   0.5403   0.01502   0.00557  -0.0399   0.4280   1.0000
   2.750   0.5614   0.01537   0.00577  -0.0387   0.4044   1.0000
   3.000   0.5826   0.01571   0.00597  -0.0376   0.3832   1.0000
   3.250   0.6038   0.01607   0.00619  -0.0365   0.3647   1.0000
   3.500   0.6251   0.01641   0.00643  -0.0354   0.3473   1.0000
   3.750   0.6463   0.01676   0.00671  -0.0343   0.3313   1.0000
   4.000   0.6675   0.01713   0.00699  -0.0332   0.3165   1.0000
   4.250   0.6886   0.01751   0.00729  -0.0320   0.3033   1.0000
   4.500   0.7095   0.01790   0.00761  -0.0309   0.2916   1.0000
   4.750   0.7306   0.01830   0.00798  -0.0298   0.2812   1.0000
   5.000   0.7519   0.01869   0.00836  -0.0287   0.2715   1.0000
   5.250   0.7727   0.01912   0.00874  -0.0276   0.2632   1.0000
   5.500   0.7936   0.01954   0.00916  -0.0265   0.2547   1.0000
   5.750   0.8145   0.01999   0.00960  -0.0254   0.2473   1.0000
   6.000   0.8353   0.02045   0.01008  -0.0243   0.2404   1.0000
   6.250   0.8561   0.02093   0.01057  -0.0232   0.2345   1.0000
   6.500   0.8772   0.02141   0.01110  -0.0221   0.2289   1.0000
   6.750   0.8979   0.02194   0.01162  -0.0210   0.2245   1.0000
   7.000   0.9193   0.02248   0.01223  -0.0200   0.2200   1.0000
   7.250   0.9406   0.02302   0.01286  -0.0190   0.2157   1.0000
   7.500   0.9614   0.02357   0.01349  -0.0180   0.2117   1.0000
   7.750   0.9794   0.02401   0.01402  -0.0166   0.2037   1.0000
   8.000   0.9937   0.02432   0.01435  -0.0147   0.1917   1.0000
   8.250   1.0093   0.02472   0.01480  -0.0131   0.1827   1.0000
   8.500   1.0227   0.02509   0.01521  -0.0112   0.1688   1.0000
   8.750   1.0377   0.02554   0.01573  -0.0095   0.1559   1.0000
   9.000   1.0523   0.02605   0.01628  -0.0078   0.1415   1.0000
   9.250   1.0674   0.02663   0.01694  -0.0061   0.1205   1.0000
   9.750   1.0618   0.03040   0.01996   0.0006   0.0250   1.0000
  10.000   1.0637   0.03208   0.02174   0.0034   0.0205   1.0000
  10.250   1.0691   0.03351   0.02333   0.0056   0.0188   1.0000
  10.500   1.0742   0.03500   0.02502   0.0076   0.0178   1.0000
  10.750   1.0773   0.03669   0.02691   0.0095   0.0171   1.0000
  11.000   1.0776   0.03866   0.02909   0.0113   0.0164   1.0000
  11.250   1.0763   0.04085   0.03148   0.0128   0.0160   1.0000
  11.500   1.0726   0.04335   0.03420   0.0140   0.0157   1.0000
  11.750   1.0663   0.04626   0.03731   0.0148   0.0156   1.0000
  12.000   1.0546   0.04999   0.04126   0.0150   0.0153   1.0000
  12.250   1.0423   0.05420   0.04568   0.0144   0.0152   1.0000
  12.500   1.0251   0.05959   0.05128   0.0126   0.0152   1.0000
  12.750   1.0047   0.06628   0.05820   0.0095   0.0152   1.0000
  13.000   0.9817   0.07415   0.06628   0.0055   0.0153   1.0000
  13.250   0.9618   0.08173   0.07405   0.0018   0.0156   1.0000
  13.500   0.9408   0.08958   0.08206  -0.0019   0.0157   1.0000
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