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S4083 (8%) (s4083-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S4083 (8%) (s4083-il)
Reynolds number: 100,000
Max Cl/Cd: 51.8 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4083-il-100000.txt
Download as CSV file: xf-s4083-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4083 (8%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3693   0.09162   0.08695  -0.0183   1.0000   0.0755
  -7.000  -0.3745   0.08944   0.08487  -0.0191   1.0000   0.0780
  -6.750  -0.3771   0.08722   0.08275  -0.0278   1.0000   0.0801
  -6.500  -0.3726   0.08284   0.07842  -0.0323   1.0000   0.0811
  -6.250  -0.3651   0.07946   0.07511  -0.0241   1.0000   0.0838
  -6.000  -0.3576   0.07664   0.07233  -0.0238   1.0000   0.0879
  -5.750  -0.3416   0.07275   0.06828  -0.0396   1.0000   0.0943
  -5.500  -0.3400   0.06900   0.06474  -0.0321   1.0000   0.0970
  -5.250  -0.3307   0.06646   0.06223  -0.0307   1.0000   0.1033
  -5.000  -0.3145   0.06189   0.05758  -0.0374   1.0000   0.1106
  -4.750  -0.3049   0.05941   0.05517  -0.0350   1.0000   0.1165
  -4.500  -0.2866   0.05533   0.05099  -0.0394   1.0000   0.1257
  -4.250  -0.2665   0.05186   0.04738  -0.0428   1.0000   0.1385
  -4.000  -0.2551   0.04945   0.04504  -0.0405   1.0000   0.1450
  -3.750  -0.2370   0.04644   0.04198  -0.0417   1.0000   0.1578
  -3.500  -0.2186   0.04374   0.03921  -0.0425   1.0000   0.1732
  -3.250  -0.1982   0.04114   0.03649  -0.0440   1.0000   0.1966
  -3.000  -0.1275   0.03007   0.02361  -0.0531   1.0000   0.0786
  -2.750  -0.0976   0.02645   0.01934  -0.0532   1.0000   0.0647
  -2.500  -0.0722   0.02407   0.01660  -0.0529   1.0000   0.0612
  -2.250  -0.0474   0.02246   0.01461  -0.0524   1.0000   0.0611
  -2.000  -0.0252   0.02147   0.01332  -0.0515   1.0000   0.0644
  -1.750   0.0259   0.01994   0.01137  -0.0555   0.9905   0.0669
  -1.500   0.0776   0.01809   0.00955  -0.0598   0.9785   0.0795
  -1.250   0.1280   0.01625   0.00813  -0.0640   0.9648   0.1462
  -1.000   0.1771   0.01288   0.00742  -0.0671   0.9544   1.0000
  -0.750   0.2341   0.01267   0.00676  -0.0724   0.9359   1.0000
  -0.500   0.2869   0.01236   0.00613  -0.0768   0.9137   1.0000
  -0.250   0.3418   0.01205   0.00554  -0.0814   0.8898   1.0000
   0.000   0.3926   0.01183   0.00506  -0.0852   0.8583   1.0000
   0.250   0.4392   0.01176   0.00468  -0.0882   0.8230   1.0000
   0.500   0.4760   0.01191   0.00454  -0.0894   0.7860   1.0000
   0.750   0.5078   0.01217   0.00451  -0.0896   0.7534   1.0000
   1.000   0.5363   0.01249   0.00457  -0.0893   0.7250   1.0000
   1.250   0.5632   0.01285   0.00470  -0.0888   0.6997   1.0000
   1.500   0.5902   0.01322   0.00485  -0.0882   0.6783   1.0000
   1.750   0.6157   0.01359   0.00507  -0.0876   0.6575   1.0000
   2.000   0.6416   0.01397   0.00532  -0.0870   0.6393   1.0000
   2.250   0.6676   0.01436   0.00556  -0.0864   0.6229   1.0000
   2.500   0.6935   0.01477   0.00584  -0.0858   0.6075   1.0000
   2.750   0.7192   0.01517   0.00615  -0.0852   0.5927   1.0000
   3.000   0.7447   0.01558   0.00651  -0.0846   0.5785   1.0000
   3.250   0.7700   0.01598   0.00687  -0.0840   0.5646   1.0000
   3.500   0.7951   0.01639   0.00725  -0.0834   0.5511   1.0000
   3.750   0.8201   0.01681   0.00766  -0.0827   0.5379   1.0000
   4.000   0.8451   0.01724   0.00810  -0.0821   0.5251   1.0000
   4.250   0.8700   0.01768   0.00860  -0.0814   0.5127   1.0000
   4.500   0.8950   0.01813   0.00907  -0.0808   0.5006   1.0000
   4.750   0.9200   0.01859   0.00954  -0.0801   0.4888   1.0000
   5.000   0.9453   0.01904   0.00998  -0.0795   0.4771   1.0000
   5.250   0.9699   0.01947   0.01049  -0.0787   0.4647   1.0000
   5.500   0.9938   0.01991   0.01102  -0.0779   0.4518   1.0000
   5.750   1.0177   0.02036   0.01156  -0.0770   0.4388   1.0000
   6.000   1.0414   0.02080   0.01209  -0.0762   0.4256   1.0000
   6.250   1.0650   0.02124   0.01266  -0.0752   0.4122   1.0000
   6.500   1.0884   0.02165   0.01316  -0.0743   0.3983   1.0000
   6.750   1.1115   0.02202   0.01362  -0.0732   0.3836   1.0000
   7.000   1.1343   0.02237   0.01405  -0.0721   0.3684   1.0000
   7.250   1.1569   0.02271   0.01450  -0.0710   0.3527   1.0000
   7.500   1.1795   0.02303   0.01485  -0.0698   0.3364   1.0000
   7.750   1.1989   0.02339   0.01543  -0.0682   0.3174   1.0000
   8.000   1.2187   0.02364   0.01577  -0.0666   0.2976   1.0000
   8.250   1.2368   0.02391   0.01615  -0.0647   0.2757   1.0000
   8.500   1.2536   0.02420   0.01645  -0.0628   0.2519   1.0000
   8.750   1.2675   0.02463   0.01700  -0.0605   0.2243   1.0000
   9.000   1.2787   0.02519   0.01765  -0.0580   0.1898   1.0000
   9.250   1.2866   0.02626   0.01862  -0.0555   0.1482   1.0000
   9.500   1.2873   0.02842   0.02047  -0.0522   0.1053   1.0000
   9.750   1.2819   0.03129   0.02312  -0.0481   0.0715   1.0000
  10.000   1.2762   0.03390   0.02560  -0.0442   0.0571   1.0000
  10.250   1.2750   0.03606   0.02785  -0.0405   0.0492   1.0000
  10.500   1.2724   0.03875   0.03042  -0.0373   0.0451   1.0000
  10.750   1.2795   0.04101   0.03293  -0.0348   0.0419   1.0000
  11.000   1.2879   0.04348   0.03553  -0.0328   0.0393   1.0000
  11.250   1.2978   0.04618   0.03831  -0.0311   0.0374   1.0000
  11.500   1.3150   0.05017   0.04242  -0.0305   0.0355   1.0000
  11.750   1.3185   0.05401   0.04655  -0.0288   0.0347   1.0000
  12.000   1.3125   0.05691   0.04978  -0.0267   0.0341   1.0000
  12.250   1.3026   0.06009   0.05328  -0.0251   0.0334   1.0000
  12.500   1.2922   0.06392   0.05741  -0.0243   0.0331   1.0000
  12.750   1.2796   0.06810   0.06187  -0.0243   0.0329   1.0000
  13.000   1.2643   0.07287   0.06691  -0.0252   0.0328   1.0000
  13.250   1.2475   0.07817   0.07247  -0.0270   0.0328   1.0000
  13.500   1.2296   0.08409   0.07861  -0.0296   0.0330   1.0000
  13.750   1.2105   0.09057   0.08531  -0.0329   0.0332   1.0000
  14.000   1.1910   0.09762   0.09255  -0.0368   0.0336   1.0000
  14.250   1.1704   0.10523   0.10033  -0.0413   0.0340   1.0000
  14.500   1.1502   0.11327   0.10851  -0.0462   0.0344   1.0000
  14.750   1.1316   0.12161   0.11695  -0.0510   0.0349   1.0000
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