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FX 66-S-196 AIRFOIL (fx66s196-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 66-S-196 AIRFOIL (fx66s196-il)
Reynolds number: 50,000
Max Cl/Cd: 9.51 at α=16°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66s196-il-50000-n5.txt
Download as CSV file: xf-fx66s196-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-196 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.2476   0.10745   0.10101  -0.0914   0.9160   0.0559
 -12.500  -0.2564   0.09839   0.09192  -0.0979   0.9073   0.0551
 -12.000  -0.3601   0.07368   0.06665  -0.1166   0.8889   0.0511
 -11.750  -0.3765   0.06877   0.06146  -0.1197   0.8776   0.0511
 -11.500  -0.3913   0.06484   0.05726  -0.1213   0.8656   0.0511
 -11.250  -0.4024   0.06142   0.05361  -0.1219   0.8549   0.0513
 -11.000  -0.4069   0.05839   0.05032  -0.1220   0.8457   0.0517
 -10.750  -0.4105   0.05594   0.04767  -0.1214   0.8356   0.0522
 -10.500  -0.4099   0.05363   0.04514  -0.1206   0.8275   0.0530
 -10.250  -0.4081   0.05162   0.04293  -0.1194   0.8194   0.0538
 -10.000  -0.4040   0.04992   0.04102  -0.1181   0.8125   0.0554
  -9.750  -0.3978   0.04829   0.03916  -0.1168   0.8050   0.0574
  -9.500  -0.3863   0.04646   0.03693  -0.1158   0.7996   0.0599
  -9.250  -0.3734   0.04489   0.03498  -0.1146   0.7924   0.0623
  -9.000  -0.3390   0.04316   0.03324  -0.1150   0.7877   0.0659
  -8.750  -0.3095   0.04195   0.03183  -0.1150   0.7832   0.0715
  -8.500  -0.2778   0.04102   0.03081  -0.1147   0.7779   0.0779
  -8.250  -0.2552   0.04024   0.02989  -0.1137   0.7734   0.0861
  -8.000  -0.2350   0.03940   0.02905  -0.1125   0.7697   0.0944
  -7.750  -0.2248   0.03886   0.02849  -0.1106   0.7640   0.1040
  -7.500  -0.2166   0.03816   0.02780  -0.1087   0.7590   0.1156
  -7.250  -0.2114   0.03726   0.02698  -0.1065   0.7550   0.1287
  -7.000  -0.2137   0.03659   0.02646  -0.1038   0.7496   0.1433
  -6.750  -0.2165   0.03584   0.02587  -0.1009   0.7443   0.1638
  -6.500  -0.2200   0.03474   0.02502  -0.0981   0.7403   0.1961
  -6.250  -0.2270   0.03378   0.02446  -0.0948   0.7361   0.2447
  -6.000  -0.2348   0.03353   0.02502  -0.0903   0.7309   0.3326
  -5.750  -0.1985   0.03693   0.02895  -0.0854   0.7278   0.4651
  -5.500  -0.2047   0.03590   0.02756  -0.0838   0.7241   0.5130
  -5.250  -0.1951   0.03712   0.02860  -0.0805   0.7196   0.5413
  -5.000  -0.1843   0.03856   0.02991  -0.0768   0.7148   0.5649
  -4.750  -0.1694   0.03956   0.03070  -0.0739   0.7114   0.5899
  -4.500  -0.1457   0.04062   0.03158  -0.0713   0.7090   0.6096
  -4.250  -0.1239   0.04143   0.03220  -0.0690   0.7066   0.6264
  -4.000  -0.1361   0.04223   0.03296  -0.0643   0.7001   0.6394
  -3.750  -0.1182   0.04295   0.03355  -0.0616   0.6967   0.6504
  -3.500  -0.0991   0.04318   0.03360  -0.0600   0.6942   0.6616
  -3.250  -0.0799   0.04312   0.03332  -0.0590   0.6922   0.6732
  -3.000  -0.0944   0.04420   0.03443  -0.0538   0.6862   0.6799
  -2.750  -0.0911   0.04442   0.03452  -0.0516   0.6820   0.6890
  -2.500  -0.0729   0.04458   0.03452  -0.0503   0.6792   0.6948
  -2.250  -0.0518   0.04440   0.03413  -0.0504   0.6771   0.7023
  -2.000  -0.0645   0.04538   0.03511  -0.0461   0.6723   0.7074
  -1.750  -0.0689   0.04612   0.03581  -0.0430   0.6680   0.7132
  -1.500  -0.0532   0.04628   0.03579  -0.0429   0.6650   0.7196
  -1.250  -0.0314   0.04642   0.03580  -0.0425   0.6628   0.7232
  -1.000  -0.0046   0.04645   0.03566  -0.0430   0.6611   0.7269
  -0.750  -0.0161   0.04771   0.03690  -0.0401   0.6558   0.7313
  -0.500  -0.0045   0.04838   0.03745  -0.0399   0.6529   0.7356
  -0.250   0.0122   0.04889   0.03787  -0.0394   0.6503   0.7385
   0.000   0.0347   0.04922   0.03808  -0.0396   0.6480   0.7415
   0.250   0.0611   0.04948   0.03820  -0.0404   0.6461   0.7449
   0.500   0.0691   0.05045   0.03910  -0.0398   0.6424   0.7486
   0.750   0.0771   0.05148   0.04007  -0.0392   0.6389   0.7519
   1.000   0.0924   0.05218   0.04072  -0.0387   0.6358   0.7551
   1.250   0.1139   0.05273   0.04119  -0.0389   0.6332   0.7591
   1.500   0.1398   0.05322   0.04158  -0.0396   0.6310   0.7635
   1.750   0.1697   0.05367   0.04193  -0.0410   0.6294   0.7671
   2.000   0.1632   0.05524   0.04352  -0.0390   0.6240   0.7698
   2.250   0.1788   0.05611   0.04435  -0.0389   0.6205   0.7725
   2.500   0.1999   0.05688   0.04507  -0.0393   0.6179   0.7757
   2.750   0.2249   0.05760   0.04574  -0.0402   0.6158   0.7789
   3.000   0.2549   0.05821   0.04628  -0.0416   0.6139   0.7819
   3.250   0.2521   0.05980   0.04790  -0.0402   0.6083   0.7846
   3.500   0.2676   0.06084   0.04895  -0.0401   0.6049   0.7876
   3.750   0.2889   0.06176   0.04986  -0.0407   0.6022   0.7909
   4.000   0.3162   0.06251   0.05058  -0.0417   0.5998   0.7945
   4.250   0.3295   0.06378   0.05186  -0.0418   0.5958   0.7985
   4.500   0.3377   0.06510   0.05322  -0.0412   0.5909   0.8021
   4.750   0.3582   0.06604   0.05419  -0.0415   0.5873   0.8065
   5.000   0.3860   0.06677   0.05494  -0.0424   0.5845   0.8119
   5.250   0.3949   0.06812   0.05634  -0.0419   0.5793   0.8171
   5.500   0.4065   0.06935   0.05764  -0.0416   0.5741   0.8231
   6.000   0.4564   0.07106   0.05949  -0.0428   0.5681   0.8371
   6.250   0.4571   0.07285   0.06136  -0.0420   0.5614   0.8450
   6.500   0.4738   0.07396   0.06258  -0.0420   0.5568   0.8540
   6.750   0.4990   0.07484   0.06359  -0.0427   0.5536   0.8658
   7.000   0.5135   0.07622   0.06509  -0.0429   0.5490   0.8809
   7.250   0.5235   0.07776   0.06678  -0.0431   0.5424   0.9021
   7.500   0.5521   0.07832   0.06750  -0.0447   0.5382   0.9912
   7.750   0.5610   0.08010   0.06931  -0.0449   0.5313   1.0000
   8.000   0.5822   0.08143   0.07068  -0.0461   0.5253   1.0000
   8.250   0.6147   0.08233   0.07161  -0.0476   0.5219   1.0000
   8.500   0.6147   0.08460   0.07394  -0.0476   0.5129   1.0000
   8.750   0.6405   0.08573   0.07512  -0.0486   0.5084   1.0000
   9.000   0.6524   0.08751   0.07696  -0.0490   0.5017   1.0000
   9.250   0.6669   0.08916   0.07867  -0.0494   0.4951   1.0000
   9.500   0.6958   0.09005   0.07965  -0.0503   0.4915   1.0000
   9.750   0.6961   0.09231   0.08199  -0.0501   0.4816   1.0000
  10.000   0.7249   0.09296   0.08272  -0.0507   0.4770   1.0000
  10.250   0.7278   0.09507   0.08491  -0.0506   0.4671   1.0000
  10.500   0.7558   0.09568   0.08565  -0.0511   0.4624   1.0000
  10.750   0.7569   0.09806   0.08813  -0.0510   0.4526   1.0000
  11.000   0.7839   0.09869   0.08887  -0.0514   0.4479   1.0000
  11.250   0.7847   0.10114   0.09143  -0.0513   0.4376   1.0000
  11.500   0.8138   0.10134   0.09179  -0.0515   0.4326   1.0000
  11.750   0.8151   0.10368   0.09423  -0.0514   0.4213   1.0000
  12.000   0.8420   0.10383   0.09453  -0.0514   0.4157   1.0000
  12.250   0.8472   0.10587   0.09671  -0.0514   0.4049   1.0000
  12.500   0.8533   0.10799   0.09895  -0.0515   0.3948   1.0000
  12.750   0.8795   0.10800   0.09916  -0.0514   0.3889   1.0000
  13.000   0.8829   0.11031   0.10160  -0.0515   0.3770   1.0000
  13.250   0.8948   0.11165   0.10310  -0.0515   0.3670   1.0000
  13.500   0.9203   0.11119   0.10283  -0.0510   0.3591   1.0000
  13.750   0.9254   0.11331   0.10510  -0.0511   0.3466   1.0000
  14.250   0.9718   0.11214   0.10437  -0.0499   0.3280   1.0000
  14.750   0.9944   0.11374   0.10633  -0.0492   0.2998   1.0000
  15.750   1.0630   0.11239   0.10554  -0.0465   0.2197   1.0000
  16.000   1.0753   0.11303   0.10601  -0.0461   0.1864   1.0000
  16.250   1.0796   0.11516   0.10786  -0.0461   0.1554   1.0000
  16.500   1.0779   0.11851   0.11094  -0.0466   0.1301   1.0000
  16.750   1.0744   0.12228   0.11443  -0.0475   0.1111   1.0000
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