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FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il)
Reynolds number: 50,000
Max Cl/Cd: 4.58 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66196v-il-50000.txt
Download as CSV file: xf-fx66196v-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-196 V1 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1828   0.12400   0.11841  -0.0713   0.9451   0.3221
 -10.250  -0.2513   0.10402   0.09850  -0.0894   0.9414   0.1620
 -10.000  -0.3389   0.09104   0.08569  -0.0984   0.9314   0.1382
  -9.750  -0.3483   0.08380   0.07835  -0.1045   0.9260   0.1325
  -9.500  -0.4463   0.08015   0.07464  -0.1029   0.9127   0.1234
  -9.250  -0.5123   0.07988   0.07412  -0.0978   0.9020   0.1216
  -9.000  -0.4996   0.07536   0.06953  -0.0992   0.8966   0.1197
  -8.750  -0.5197   0.07353   0.06758  -0.0959   0.8899   0.1188
  -8.500  -0.5361   0.07125   0.06513  -0.0934   0.8840   0.1178
  -8.250  -0.5416   0.06805   0.06159  -0.0929   0.8799   0.1169
  -8.000  -0.5577   0.06646   0.05977  -0.0893   0.8762   0.1167
  -7.750  -0.5697   0.06477   0.05784  -0.0860   0.8732   0.1164
  -7.500  -0.5731   0.06269   0.05542  -0.0838   0.8706   0.1169
  -7.250  -0.5680   0.06047   0.05282  -0.0825   0.8681   0.1171
  -7.000  -0.5552   0.05813   0.05002  -0.0820   0.8657   0.1180
  -6.750  -0.5319   0.05588   0.04720  -0.0825   0.8631   0.1197
  -6.500  -0.5248   0.05465   0.04560  -0.0805   0.8625   0.1223
  -6.250  -0.7612   0.06044   0.05331  -0.0410   1.0000   0.1123
  -6.000  -0.7466   0.05780   0.05027  -0.0409   1.0000   0.1143
  -5.750  -0.7299   0.05532   0.04736  -0.0408   1.0000   0.1155
  -5.500  -0.7113   0.05306   0.04466  -0.0404   1.0000   0.1170
  -5.250  -0.6918   0.05121   0.04236  -0.0400   1.0000   0.1191
  -5.000  -0.6727   0.04954   0.04042  -0.0395   1.0000   0.1237
  -4.750  -0.6543   0.04833   0.03922  -0.0386   1.0000   0.1299
  -4.500  -0.6339   0.04736   0.03794  -0.0376   1.0000   0.1360
  -4.250  -0.6163   0.04641   0.03720  -0.0362   1.0000   0.1452
  -4.000  -0.5985   0.04567   0.03653  -0.0348   1.0000   0.1581
  -3.750  -0.5807   0.04494   0.03590  -0.0335   1.0000   0.1755
  -3.500  -0.5618   0.04378   0.03504  -0.0331   1.0000   0.2096
  -3.250  -0.5499   0.04285   0.03668  -0.0296   1.0000   0.5231
  -3.000  -0.5518   0.04606   0.03988  -0.0197   1.0000   0.6020
  -2.750  -0.5521   0.04801   0.04181  -0.0112   1.0000   0.6381
  -2.500  -0.5505   0.04938   0.04309  -0.0040   1.0000   0.6698
  -2.250  -0.5476   0.05036   0.04395   0.0024   1.0000   0.6994
  -2.000  -0.5470   0.05109   0.04458   0.0094   1.0000   0.7267
  -1.750  -0.5481   0.05160   0.04502   0.0168   1.0000   0.7549
  -1.500  -0.5465   0.05224   0.04557   0.0239   0.9979   0.7871
  -1.250  -0.5380   0.05319   0.04637   0.0294   0.9934   0.8199
  -1.000  -0.5231   0.05363   0.04660   0.0320   0.9870   0.8438
  -0.750  -0.4994   0.05438   0.04711   0.0313   0.9817   0.8587
  -0.500  -0.4728   0.05474   0.04723   0.0295   0.9732   0.8680
  -0.250  -0.4471   0.05532   0.04757   0.0276   0.9679   0.8760
   0.000  -0.4204   0.05575   0.04780   0.0255   0.9592   0.8837
   0.250  -0.3957   0.05629   0.04811   0.0234   0.9530   0.8899
   0.500  -0.3656   0.05705   0.04868   0.0206   0.9439   0.8958
   0.750  -0.3421   0.05756   0.04900   0.0187   0.9377   0.9017
   1.000  -0.3126   0.05833   0.04961   0.0159   0.9292   0.9073
   1.250  -0.2850   0.05941   0.05054   0.0134   0.9239   0.9140
   1.500  -0.2594   0.05985   0.05085   0.0113   0.9143   0.9202
   1.750  -0.2259   0.06151   0.05235   0.0076   0.9090   0.9269
   2.000  -0.2022   0.06176   0.05251   0.0057   0.8991   0.9339
   2.250  -0.1581   0.06452   0.05513  -0.0001   0.8945   0.9417
   2.500  -0.1394   0.06413   0.05469  -0.0013   0.8843   0.9486
   2.750  -0.0899   0.06725   0.05771  -0.0083   0.8790   0.9570
   3.000  -0.0685   0.06714   0.05755  -0.0103   0.8689   0.9646
   3.250  -0.0163   0.07049   0.06083  -0.0180   0.8634   0.9766
   3.500   0.0019   0.07017   0.06050  -0.0195   0.8521   0.9899
   3.750   0.0372   0.07304   0.06324  -0.0241   0.8475   1.0000
   4.000   0.0433   0.07223   0.06239  -0.0236   0.8369   1.0000
   4.250   0.0832   0.07543   0.06550  -0.0289   0.8321   1.0000
   4.500   0.0930   0.07513   0.06515  -0.0292   0.8218   1.0000
   4.750   0.1338   0.07839   0.06832  -0.0347   0.8168   1.0000
   5.000   0.1450   0.07856   0.06847  -0.0353   0.8076   1.0000
   5.250   0.1847   0.08173   0.07156  -0.0405   0.8017   1.0000
   5.500   0.1975   0.08237   0.07216  -0.0414   0.7927   1.0000
   5.750   0.2345   0.08540   0.07512  -0.0459   0.7865   1.0000
   6.000   0.2476   0.08637   0.07607  -0.0469   0.7781   1.0000
   6.250   0.2823   0.08933   0.07897  -0.0508   0.7710   1.0000
   6.500   0.2941   0.09047   0.08009  -0.0514   0.7628   1.0000
   6.750   0.3253   0.09328   0.08285  -0.0545   0.7555   1.0000
   7.000   0.3365   0.09461   0.08417  -0.0549   0.7475   1.0000
   7.250   0.3650   0.09733   0.08685  -0.0574   0.7400   1.0000
   7.500   0.3754   0.09880   0.08832  -0.0576   0.7322   1.0000
   7.750   0.4016   0.10146   0.09097  -0.0596   0.7244   1.0000
   8.000   0.4114   0.10309   0.09261  -0.0598   0.7171   1.0000
   8.250   0.4359   0.10568   0.09521  -0.0615   0.7088   1.0000
   8.500   0.4446   0.10736   0.09691  -0.0616   0.7010   1.0000
   8.750   0.4691   0.11010   0.09970  -0.0632   0.6929   1.0000
   9.000   0.4761   0.11173   0.10136  -0.0631   0.6847   1.0000
   9.250   0.5017   0.11475   0.10443  -0.0649   0.6768   1.0000
   9.500   0.5060   0.11620   0.10593  -0.0646   0.6680   1.0000
   9.750   0.5340   0.11967   0.10947  -0.0665   0.6606   1.0000
  10.000   0.5347   0.12082   0.11068  -0.0660   0.6514   1.0000
  10.250   0.5657   0.12489   0.11483  -0.0682   0.6445   1.0000
  10.500   0.5628   0.12563   0.11563  -0.0675   0.6345   1.0000
  10.750   0.5964   0.13033   0.12045  -0.0699   0.6283   1.0000
  11.000   0.5910   0.13066   0.12085  -0.0691   0.6173   1.0000
  11.250   0.6154   0.13478   0.12506  -0.0708   0.6115   1.0000
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