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S4062-095-87 (s4062-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S4062-095-87 (s4062-il)
Reynolds number: 50,000
Max Cl/Cd: 38.41 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4062-il-50000-n5.txt
Download as CSV file: xf-s4062-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4062-095-87                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3208   0.10371   0.09708  -0.0417   1.0000   0.0586
  -8.500  -0.3261   0.10144   0.09492  -0.0403   1.0000   0.0560
  -8.000  -0.3703   0.09779   0.09157  -0.0382   1.0000   0.0494
  -7.750  -0.3749   0.09598   0.08983  -0.0353   1.0000   0.0486
  -7.500  -0.3868   0.09439   0.08833  -0.0327   1.0000   0.0480
  -7.250  -0.3988   0.09269   0.08673  -0.0305   1.0000   0.0474
  -7.000  -0.4074   0.09028   0.08437  -0.0298   0.9995   0.0467
  -6.750  -0.3932   0.08531   0.07939  -0.0358   0.9921   0.0455
  -6.500  -0.3774   0.07993   0.07399  -0.0427   0.9849   0.0443
  -6.250  -0.3626   0.07427   0.06828  -0.0496   0.9771   0.0432
  -6.000  -0.3433   0.06763   0.06151  -0.0579   0.9704   0.0421
  -5.750  -0.3249   0.06122   0.05489  -0.0648   0.9633   0.0417
  -5.500  -0.2998   0.05546   0.04883  -0.0713   0.9579   0.0424
  -5.250  -0.2787   0.05065   0.04366  -0.0754   0.9511   0.0439
  -5.000  -0.2488   0.04549   0.03793  -0.0804   0.9464   0.0454
  -4.750  -0.2213   0.04115   0.03294  -0.0833   0.9414   0.0465
  -4.500  -0.1919   0.03730   0.02833  -0.0854   0.9364   0.0480
  -4.250  -0.1587   0.03438   0.02477  -0.0874   0.9327   0.0509
  -4.000  -0.1297   0.03296   0.02310  -0.0884   0.9282   0.0571
  -3.750  -0.1019   0.03119   0.02088  -0.0886   0.9230   0.0634
  -3.500  -0.0699   0.02995   0.01940  -0.0897   0.9189   0.0762
  -3.250  -0.0371   0.02892   0.01829  -0.0909   0.9153   0.0952
  -3.000  -0.0133   0.02814   0.01736  -0.0904   0.9092   0.1192
  -2.750   0.0183   0.02747   0.01665  -0.0914   0.9048   0.1539
  -2.500   0.0542   0.02687   0.01604  -0.0932   0.9016   0.2000
  -2.250   0.0756   0.02652   0.01574  -0.0924   0.8949   0.2416
  -2.000   0.1068   0.02609   0.01544  -0.0934   0.8903   0.3035
  -1.750   0.1410   0.02562   0.01525  -0.0948   0.8870   0.3908
  -1.500   0.1587   0.02531   0.01529  -0.0932   0.8799   0.4874
  -1.250   0.1814   0.02471   0.01532  -0.0915   0.8752   0.6578
  -1.000   0.2229   0.02421   0.01506  -0.0931   0.8720   1.0000
  -0.750   0.2416   0.02460   0.01513  -0.0920   0.8640   1.0000
  -0.500   0.2749   0.02491   0.01511  -0.0933   0.8593   1.0000
  -0.250   0.2984   0.02531   0.01525  -0.0930   0.8526   1.0000
   0.250   0.3626   0.02597   0.01547  -0.0950   0.8427   1.0000
   0.500   0.3787   0.02648   0.01582  -0.0934   0.8338   1.0000
   0.750   0.4128   0.02678   0.01597  -0.0946   0.8291   1.0000
   1.000   0.4318   0.02729   0.01636  -0.0936   0.8208   1.0000
   1.250   0.4640   0.02760   0.01656  -0.0944   0.8153   1.0000
   1.500   0.4851   0.02809   0.01697  -0.0936   0.8071   1.0000
   1.750   0.5163   0.02838   0.01720  -0.0943   0.8009   1.0000
   2.000   0.5379   0.02886   0.01763  -0.0935   0.7922   1.0000
   2.250   0.5701   0.02908   0.01783  -0.0941   0.7859   1.0000
   2.500   0.5909   0.02955   0.01829  -0.0932   0.7761   1.0000
   2.750   0.6265   0.02957   0.01831  -0.0941   0.7702   1.0000
   3.000   0.6462   0.03002   0.01880  -0.0929   0.7590   1.0000
   3.250   0.6720   0.03026   0.01906  -0.0924   0.7495   1.0000
   3.500   0.7053   0.03018   0.01902  -0.0927   0.7417   1.0000
   3.750   0.7272   0.03045   0.01936  -0.0916   0.7298   1.0000
   4.000   0.7523   0.03057   0.01957  -0.0908   0.7186   1.0000
   4.250   0.7857   0.03027   0.01937  -0.0907   0.7096   1.0000
   4.500   0.8132   0.03017   0.01936  -0.0900   0.6982   1.0000
   4.750   0.8369   0.03020   0.01954  -0.0888   0.6850   1.0000
   5.000   0.8617   0.03014   0.01960  -0.0877   0.6716   1.0000
   5.250   0.8874   0.02998   0.01958  -0.0866   0.6577   1.0000
   5.500   0.9135   0.02975   0.01954  -0.0854   0.6431   1.0000
   5.750   0.9401   0.02943   0.01937  -0.0842   0.6275   1.0000
   6.000   0.9679   0.02901   0.01911  -0.0831   0.6109   1.0000
   6.250   0.9870   0.02907   0.01933  -0.0811   0.5896   1.0000
   6.500   1.0131   0.02870   0.01913  -0.0797   0.5682   1.0000
   6.750   1.0340   0.02866   0.01923  -0.0778   0.5420   1.0000
   7.000   1.0576   0.02850   0.01915  -0.0762   0.5126   1.0000
   7.250   1.0819   0.02837   0.01902  -0.0745   0.4794   1.0000
   7.500   1.1011   0.02867   0.01932  -0.0725   0.4430   1.0000
   7.750   1.1195   0.02916   0.01965  -0.0705   0.4067   1.0000
   8.000   1.1325   0.03002   0.02041  -0.0682   0.3727   1.0000
   8.250   1.1439   0.03108   0.02135  -0.0659   0.3418   1.0000
   8.500   1.1538   0.03230   0.02248  -0.0636   0.3135   1.0000
   8.750   1.1629   0.03362   0.02372  -0.0614   0.2874   1.0000
   9.000   1.1714   0.03503   0.02513  -0.0593   0.2634   1.0000
   9.250   1.1794   0.03653   0.02664  -0.0574   0.2403   1.0000
   9.500   1.1868   0.03811   0.02818  -0.0555   0.2195   1.0000
   9.750   1.1940   0.03979   0.02991  -0.0537   0.1990   1.0000
  10.000   1.2007   0.04155   0.03170  -0.0520   0.1804   1.0000
  10.250   1.2067   0.04344   0.03358  -0.0504   0.1635   1.0000
  10.500   1.2130   0.04543   0.03559  -0.0489   0.1475   1.0000
  10.750   1.2183   0.04755   0.03784  -0.0475   0.1321   1.0000
  11.000   1.2233   0.04980   0.04014  -0.0462   0.1185   1.0000
  11.250   1.2260   0.05221   0.04260  -0.0450   0.1064   1.0000
  11.500   1.2278   0.05475   0.04515  -0.0439   0.0959   1.0000
  11.750   1.2299   0.05748   0.04806  -0.0430   0.0856   1.0000
  12.000   1.2332   0.06030   0.05105  -0.0421   0.0773   1.0000
  12.250   1.2337   0.06317   0.05388  -0.0415   0.0712   1.0000
  12.500   1.2373   0.06636   0.05742  -0.0407   0.0650   1.0000
  12.750   1.2378   0.06944   0.06052  -0.0403   0.0607   1.0000
  13.000   1.2391   0.07307   0.06448  -0.0399   0.0568   1.0000
  13.250   1.2390   0.07696   0.06869  -0.0396   0.0540   1.0000
  13.500   1.2367   0.08093   0.07287  -0.0397   0.0518   1.0000
  13.750   1.2360   0.08459   0.07661  -0.0399   0.0498   1.0000
  14.000   1.2296   0.08937   0.08158  -0.0407   0.0484   1.0000
  14.250   1.2147   0.09548   0.08805  -0.0426   0.0476   1.0000
  14.500   1.1980   0.10224   0.09512  -0.0453   0.0471   1.0000
  14.750   1.1788   0.10988   0.10302  -0.0490   0.0469   1.0000
  15.000   1.1576   0.11857   0.11194  -0.0538   0.0470   1.0000
  15.250   1.1355   0.12832   0.12189  -0.0596   0.0474   1.0000
  15.500   1.1128   0.13921   0.13291  -0.0664   0.0480   1.0000
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