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S4110 (s4110-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4110 (s4110-il)
Reynolds number: 100,000
Max Cl/Cd: 57.86 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4110-il-100000-n5.txt
Download as CSV file: xf-s4110-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4110                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4040   0.10221   0.09691  -0.0325   1.0000   0.0295
  -9.250  -0.3982   0.09921   0.09395  -0.0321   1.0000   0.0290
  -9.000  -0.3951   0.09605   0.09083  -0.0324   1.0000   0.0285
  -8.750  -0.3936   0.09285   0.08768  -0.0330   1.0000   0.0281
  -8.500  -0.3937   0.08959   0.08448  -0.0335   1.0000   0.0278
  -8.250  -0.3968   0.08613   0.08109  -0.0342   1.0000   0.0276
  -8.000  -0.4011   0.08298   0.07803  -0.0345   1.0000   0.0274
  -7.750  -0.4090   0.07995   0.07510  -0.0344   1.0000   0.0272
  -7.500  -0.4166   0.07667   0.07192  -0.0350   1.0000   0.0271
  -7.250  -0.4220   0.07292   0.06825  -0.0366   1.0000   0.0269
  -7.000  -0.4270   0.06854   0.06392  -0.0392   1.0000   0.0272
  -6.750  -0.4299   0.06379   0.05918  -0.0419   1.0000   0.0272
  -6.500  -0.4305   0.05829   0.05362  -0.0450   1.0000   0.0273
  -6.250  -0.4277   0.05242   0.04760  -0.0479   1.0000   0.0272
  -6.000  -0.4206   0.04613   0.04101  -0.0508   1.0000   0.0275
  -5.750  -0.3981   0.03889   0.03317  -0.0559   0.9973   0.0276
  -5.500  -0.3652   0.03259   0.02604  -0.0608   0.9930   0.0279
  -5.250  -0.3322   0.02825   0.02089  -0.0637   0.9887   0.0286
  -5.000  -0.2978   0.02528   0.01721  -0.0658   0.9851   0.0296
  -4.750  -0.2654   0.02350   0.01525  -0.0675   0.9809   0.0313
  -4.500  -0.2328   0.02234   0.01388  -0.0689   0.9758   0.0344
  -4.250  -0.1978   0.02106   0.01229  -0.0704   0.9719   0.0396
  -4.000  -0.1657   0.02008   0.01124  -0.0716   0.9667   0.0452
  -3.750  -0.1329   0.01915   0.01021  -0.0727   0.9614   0.0546
  -3.500  -0.0967   0.01862   0.00961  -0.0746   0.9573   0.0701
  -3.250  -0.0661   0.01813   0.00907  -0.0753   0.9506   0.0854
  -3.000  -0.0316   0.01759   0.00847  -0.0768   0.9456   0.1000
  -2.750   0.0030   0.01705   0.00791  -0.0782   0.9407   0.1139
  -2.500   0.0343   0.01663   0.00748  -0.0790   0.9339   0.1322
  -2.250   0.0711   0.01611   0.00706  -0.0808   0.9296   0.1577
  -2.000   0.1015   0.01566   0.00677  -0.0815   0.9224   0.2007
  -1.750   0.1358   0.01511   0.00653  -0.0829   0.9169   0.2833
  -1.500   0.1671   0.01454   0.00642  -0.0837   0.9108   0.4143
  -1.250   0.1964   0.01400   0.00636  -0.0838   0.9036   0.5638
  -1.000   0.2239   0.01348   0.00632  -0.0829   0.8975   0.7167
  -0.750   0.2561   0.01299   0.00619  -0.0824   0.8903   0.9191
  -0.500   0.2994   0.01285   0.00588  -0.0852   0.8847   1.0000
  -0.250   0.3280   0.01288   0.00577  -0.0852   0.8744   1.0000
   0.000   0.3590   0.01289   0.00565  -0.0856   0.8652   1.0000
   0.250   0.3921   0.01285   0.00549  -0.0863   0.8566   1.0000
   0.500   0.4204   0.01287   0.00543  -0.0861   0.8450   1.0000
   0.750   0.4495   0.01288   0.00536  -0.0861   0.8336   1.0000
   1.000   0.4791   0.01288   0.00529  -0.0860   0.8220   1.0000
   1.250   0.5085   0.01288   0.00522  -0.0859   0.8098   1.0000
   1.500   0.5370   0.01289   0.00517  -0.0856   0.7963   1.0000
   1.750   0.5646   0.01291   0.00516  -0.0851   0.7814   1.0000
   2.000   0.5916   0.01296   0.00516  -0.0846   0.7651   1.0000
   2.250   0.6185   0.01301   0.00518  -0.0840   0.7479   1.0000
   2.500   0.6454   0.01307   0.00522  -0.0834   0.7297   1.0000
   2.750   0.6725   0.01313   0.00523  -0.0827   0.7102   1.0000
   3.000   0.6982   0.01323   0.00530  -0.0819   0.6877   1.0000
   3.250   0.7241   0.01335   0.00536  -0.0811   0.6637   1.0000
   3.500   0.7496   0.01350   0.00546  -0.0803   0.6370   1.0000
   3.750   0.7745   0.01370   0.00558  -0.0793   0.6070   1.0000
   4.000   0.7989   0.01394   0.00572  -0.0783   0.5736   1.0000
   4.250   0.8228   0.01425   0.00589  -0.0773   0.5377   1.0000
   4.500   0.8459   0.01462   0.00615  -0.0762   0.4988   1.0000
   4.750   0.8685   0.01505   0.00644  -0.0750   0.4592   1.0000
   5.000   0.8904   0.01557   0.00678  -0.0738   0.4184   1.0000
   5.250   0.9119   0.01614   0.00718  -0.0727   0.3791   1.0000
   5.500   0.9330   0.01675   0.00764  -0.0716   0.3409   1.0000
   5.750   0.9539   0.01741   0.00819  -0.0704   0.3064   1.0000
   6.000   0.9748   0.01809   0.00875  -0.0694   0.2745   1.0000
   6.250   0.9955   0.01879   0.00935  -0.0683   0.2461   1.0000
   6.500   1.0162   0.01952   0.01000  -0.0672   0.2212   1.0000
   6.750   1.0369   0.02025   0.01071  -0.0662   0.1989   1.0000
   7.000   1.0571   0.02102   0.01144  -0.0651   0.1798   1.0000
   7.250   1.0768   0.02183   0.01219  -0.0640   0.1631   1.0000
   7.500   1.0968   0.02262   0.01300  -0.0630   0.1481   1.0000
   7.750   1.1161   0.02346   0.01384  -0.0618   0.1346   1.0000
   8.000   1.1350   0.02434   0.01478  -0.0606   0.1227   1.0000
   8.250   1.1540   0.02521   0.01572  -0.0595   0.1113   1.0000
   8.500   1.1723   0.02615   0.01674  -0.0582   0.1012   1.0000
   8.750   1.1890   0.02721   0.01783  -0.0568   0.0928   1.0000
   9.000   1.2055   0.02823   0.01893  -0.0554   0.0843   1.0000
   9.250   1.2218   0.02935   0.02017  -0.0540   0.0768   1.0000
   9.500   1.2354   0.03058   0.02145  -0.0523   0.0708   1.0000
   9.750   1.2506   0.03178   0.02284  -0.0508   0.0646   1.0000
  10.000   1.2621   0.03304   0.02415  -0.0489   0.0597   1.0000
  10.250   1.2736   0.03452   0.02578  -0.0470   0.0555   1.0000
  10.500   1.2838   0.03587   0.02729  -0.0450   0.0512   1.0000
  10.750   1.2900   0.03743   0.02887  -0.0429   0.0479   1.0000
  11.000   1.2991   0.03919   0.03088  -0.0410   0.0448   1.0000
  11.250   1.3059   0.04093   0.03285  -0.0391   0.0418   1.0000
  11.500   1.3098   0.04267   0.03469  -0.0372   0.0393   1.0000
  11.750   1.3114   0.04494   0.03700  -0.0355   0.0373   1.0000
  12.000   1.3150   0.04737   0.03977  -0.0339   0.0356   1.0000
  12.250   1.3157   0.04997   0.04265  -0.0325   0.0338   1.0000
  12.500   1.3143   0.05265   0.04553  -0.0314   0.0321   1.0000
  12.750   1.3117   0.05542   0.04845  -0.0306   0.0308   1.0000
  13.000   1.3077   0.05846   0.05160  -0.0303   0.0297   1.0000
  13.250   1.3015   0.06217   0.05538  -0.0301   0.0287   1.0000
  13.500   1.2921   0.06652   0.06006  -0.0306   0.0281   1.0000
  13.750   1.2803   0.07148   0.06532  -0.0316   0.0277   1.0000
  14.000   1.2657   0.07711   0.07123  -0.0335   0.0273   1.0000
  14.250   1.2490   0.08344   0.07782  -0.0362   0.0271   1.0000
  14.500   1.2296   0.09067   0.08531  -0.0399   0.0269   1.0000
  14.750   1.2080   0.09893   0.09379  -0.0447   0.0270   1.0000
  15.000   1.1837   0.10852   0.10360  -0.0508   0.0272   1.0000
  15.250   1.1562   0.11975   0.11501  -0.0581   0.0275   1.0000
  15.500   1.1256   0.13281   0.12821  -0.0667   0.0280   1.0000
  15.750   1.0921   0.14780   0.14328  -0.0760   0.0285   1.0000
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