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S4233-136-84 (s4233-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S4233-136-84 (s4233-il)
Reynolds number: 100,000
Max Cl/Cd: 52.23 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4233-il-100000.txt
Download as CSV file: xf-s4233-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4233-136-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3179   0.09953   0.09503  -0.0457   1.0000   0.1286
  -9.250  -0.3454   0.09813   0.09381  -0.0458   1.0000   0.1328
  -9.000  -0.3872   0.09824   0.09410  -0.0429   1.0000   0.1336
  -8.750  -0.4285   0.09824   0.09426  -0.0398   1.0000   0.1339
  -8.500  -0.4065   0.09480   0.09083  -0.0354   1.0000   0.1369
  -8.250  -0.4099   0.09377   0.08985  -0.0316   1.0000   0.1398
  -8.000  -0.4153   0.09129   0.08742  -0.0325   0.9973   0.1439
  -7.750  -0.4306   0.08488   0.08108  -0.0447   0.9857   0.1510
  -7.500  -0.4239   0.07973   0.07586  -0.0545   0.9748   0.1631
  -7.250  -0.3879   0.07716   0.07331  -0.0512   0.9730   0.1698
  -7.000  -0.4565   0.05139   0.04597  -0.0738   0.9507   0.0793
  -6.750  -0.4284   0.04665   0.04100  -0.0764   0.9456   0.0731
  -6.500  -0.4177   0.04228   0.03547  -0.0755   0.9360   0.0648
  -6.250  -0.3873   0.03809   0.03098  -0.0777   0.9313   0.0630
  -6.000  -0.3661   0.03543   0.02795  -0.0774   0.9239   0.0616
  -5.750  -0.3346   0.03286   0.02492  -0.0785   0.9181   0.0606
  -5.500  -0.2927   0.03052   0.02213  -0.0810   0.9148   0.0609
  -5.250  -0.2744   0.02933   0.02073  -0.0793   0.9058   0.0620
  -5.000  -0.2335   0.02800   0.01912  -0.0814   0.9015   0.0653
  -4.750  -0.2079   0.02665   0.01791  -0.0814   0.8950   0.0708
  -4.500  -0.1777   0.02572   0.01689  -0.0817   0.8886   0.0771
  -4.250  -0.1400   0.02428   0.01557  -0.0834   0.8849   0.0926
  -4.000  -0.1301   0.02307   0.01483  -0.0809   0.8754   0.1499
  -3.750  -0.1055   0.02123   0.01436  -0.0811   0.8705   0.4114
  -3.500  -0.0912   0.02127   0.01478  -0.0786   0.8620   0.5179
  -3.250  -0.0652   0.02147   0.01518  -0.0772   0.8561   0.6031
  -3.000  -0.0432   0.02176   0.01547  -0.0754   0.8494   0.6496
  -2.750  -0.0217   0.02199   0.01568  -0.0735   0.8421   0.6866
  -2.500   0.0112   0.02202   0.01562  -0.0732   0.8383   0.7241
  -2.250   0.0205   0.02241   0.01603  -0.0696   0.8284   0.7502
  -2.000   0.0495   0.02239   0.01594  -0.0684   0.8239   0.7807
  -1.750   0.0606   0.02272   0.01626  -0.0651   0.8151   0.8071
  -1.500   0.0856   0.02270   0.01617  -0.0635   0.8096   0.8355
  -1.250   0.1054   0.02284   0.01627  -0.0612   0.8032   0.8613
  -1.000   0.1275   0.02297   0.01635  -0.0596   0.7959   0.8878
  -0.750   0.1698   0.02277   0.01603  -0.0611   0.7925   0.9136
  -0.500   0.2095   0.02311   0.01628  -0.0636   0.7848   0.9371
  -0.250   0.2711   0.02298   0.01601  -0.0696   0.7804   0.9556
   0.000   0.3446   0.02258   0.01545  -0.0776   0.7777   0.9677
   0.250   0.4050   0.02256   0.01533  -0.0844   0.7715   0.9825
   0.500   0.4674   0.02228   0.01497  -0.0915   0.7656   0.9961
   0.750   0.5004   0.02191   0.01450  -0.0927   0.7612   1.0000
   1.000   0.4884   0.02263   0.01521  -0.0877   0.7494   1.0000
   1.250   0.5094   0.02236   0.01485  -0.0864   0.7453   1.0000
   1.500   0.5015   0.02319   0.01564  -0.0818   0.7334   1.0000
   1.750   0.5294   0.02307   0.01543  -0.0816   0.7287   1.0000
   2.000   0.5408   0.02374   0.01605  -0.0797   0.7185   1.0000
   2.250   0.5770   0.02335   0.01559  -0.0803   0.7150   1.0000
   2.500   0.5877   0.02423   0.01646  -0.0785   0.7037   1.0000
   2.750   0.6245   0.02380   0.01597  -0.0791   0.7001   1.0000
   3.000   0.6369   0.02469   0.01687  -0.0775   0.6891   1.0000
   3.250   0.6741   0.02421   0.01636  -0.0781   0.6852   1.0000
   3.500   0.6877   0.02508   0.01725  -0.0766   0.6743   1.0000
   3.750   0.7250   0.02457   0.01672  -0.0772   0.6702   1.0000
   4.000   0.7398   0.02538   0.01759  -0.0758   0.6594   1.0000
   4.250   0.7773   0.02484   0.01703  -0.0763   0.6551   1.0000
   4.500   0.7928   0.02562   0.01786  -0.0750   0.6443   1.0000
   4.750   0.8308   0.02502   0.01726  -0.0756   0.6397   1.0000
   5.000   0.8468   0.02576   0.01809  -0.0742   0.6288   1.0000
   5.250   0.8858   0.02509   0.01742  -0.0749   0.6241   1.0000
   5.500   0.9021   0.02578   0.01821  -0.0735   0.6129   1.0000
   5.750   0.9429   0.02501   0.01745  -0.0744   0.6082   1.0000
   6.000   0.9588   0.02568   0.01823  -0.0729   0.5965   1.0000
   6.250   0.9825   0.02590   0.01853  -0.0721   0.5868   1.0000
   6.500   1.0188   0.02532   0.01799  -0.0725   0.5794   1.0000
   6.750   1.0384   0.02571   0.01850  -0.0713   0.5679   1.0000
   7.000   1.0666   0.02559   0.01846  -0.0709   0.5580   1.0000
   7.250   1.1021   0.02500   0.01790  -0.0711   0.5486   1.0000
   7.500   1.1234   0.02515   0.01816  -0.0699   0.5357   1.0000
   7.750   1.1475   0.02509   0.01820  -0.0689   0.5227   1.0000
   8.000   1.1732   0.02490   0.01809  -0.0680   0.5089   1.0000
   8.250   1.1982   0.02470   0.01796  -0.0671   0.4943   1.0000
   8.500   1.2220   0.02456   0.01788  -0.0659   0.4786   1.0000
   8.750   1.2447   0.02443   0.01780  -0.0647   0.4618   1.0000
   9.000   1.2675   0.02427   0.01765  -0.0634   0.4435   1.0000
   9.250   1.2806   0.02453   0.01801  -0.0610   0.4237   1.0000
   9.500   1.2932   0.02480   0.01834  -0.0585   0.4029   1.0000
   9.750   1.3041   0.02514   0.01868  -0.0558   0.3811   1.0000
  10.000   1.3061   0.02572   0.01930  -0.0521   0.3571   1.0000
  10.250   1.3021   0.02649   0.02004  -0.0477   0.3325   1.0000
  10.500   1.2955   0.02760   0.02109  -0.0435   0.3061   1.0000
  10.750   1.2875   0.02911   0.02249  -0.0399   0.2784   1.0000
  11.000   1.2780   0.03103   0.02430  -0.0367   0.2494   1.0000
  11.250   1.2677   0.03336   0.02650  -0.0340   0.2198   1.0000
  11.500   1.2560   0.03609   0.02907  -0.0317   0.1908   1.0000
  11.750   1.2427   0.03926   0.03205  -0.0297   0.1632   1.0000
  12.000   1.2286   0.04277   0.03536  -0.0281   0.1389   1.0000
  12.250   1.2155   0.04647   0.03891  -0.0269   0.1167   1.0000
  12.500   1.2019   0.05036   0.04260  -0.0258   0.0997   1.0000
  12.750   1.1919   0.05410   0.04621  -0.0249   0.0846   1.0000
  13.000   1.1874   0.05738   0.04936  -0.0239   0.0733   1.0000
  13.250   1.1887   0.06016   0.05213  -0.0230   0.0647   1.0000
  13.500   1.1969   0.06235   0.05434  -0.0218   0.0581   1.0000
  13.750   1.2132   0.06387   0.05564  -0.0204   0.0523   1.0000
  14.000   1.2224   0.06623   0.05827  -0.0197   0.0493   1.0000
  14.250   1.2382   0.06820   0.06038  -0.0187   0.0469   1.0000
  14.500   1.2553   0.07025   0.06248  -0.0179   0.0448   1.0000
  14.750   1.2922   0.07261   0.06485  -0.0166   0.0428   1.0000
  15.000   1.2884   0.07632   0.06887  -0.0164   0.0423   1.0000
  15.250   1.2809   0.08042   0.07329  -0.0166   0.0419   1.0000
  15.500   1.2703   0.08490   0.07808  -0.0171   0.0415   1.0000
  15.750   1.2566   0.08988   0.08335  -0.0182   0.0412   1.0000
  16.000   1.2435   0.09518   0.08892  -0.0195   0.0413   1.0000
  16.250   1.2244   0.10114   0.09516  -0.0217   0.0409   1.0000
  16.500   1.2066   0.10754   0.10181  -0.0243   0.0412   1.0000
  16.750   1.1865   0.11450   0.10901  -0.0277   0.0413   1.0000
  17.000   1.1651   0.12213   0.11686  -0.0318   0.0416   1.0000
  17.250   1.1435   0.13028   0.12520  -0.0364   0.0420   1.0000
  17.500   1.1226   0.13889   0.13396  -0.0415   0.0424   1.0000
  17.750   1.1037   0.14771   0.14290  -0.0468   0.0428   1.0000
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