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S4083 (8%) (s4083-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S4083 (8%) (s4083-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.84 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4083-il-1000000-n5.txt
Download as CSV file: xf-s4083-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3056   0.08964   0.08813  -0.0188   1.0000   0.0067
  -8.750  -0.3044   0.08609   0.08459  -0.0192   1.0000   0.0067
  -8.250  -0.3037   0.07884   0.07737  -0.0200   1.0000   0.0067
  -6.750  -0.2835   0.05295   0.05153  -0.0345   0.9731   0.0061
  -6.500  -0.3270   0.06393   0.06241  -0.0416   0.9830   0.0061
  -6.250  -0.3084   0.05853   0.05697  -0.0486   0.9734   0.0057
  -6.000  -0.2812   0.05087   0.04923  -0.0589   0.9636   0.0052
  -5.750  -0.2507   0.01658   0.01313  -0.0801   0.9522   0.0044
  -5.500  -0.2128   0.01489   0.01117  -0.0829   0.9428   0.0046
  -5.250  -0.1542   0.01328   0.00923  -0.0901   0.9285   0.0049
  -5.000  -0.0952   0.01208   0.00766  -0.0973   0.8889   0.0053
  -4.750  -0.0680   0.01147   0.00664  -0.0972   0.8262   0.0055
  -4.500  -0.0469   0.01109   0.00591  -0.0956   0.7692   0.0057
  -4.250  -0.0247   0.01068   0.00522  -0.0943   0.7251   0.0058
  -4.000  -0.0012   0.01031   0.00461  -0.0932   0.6883   0.0060
  -3.750   0.0229   0.01001   0.00409  -0.0923   0.6545   0.0061
  -3.500   0.0476   0.00979   0.00369  -0.0916   0.6242   0.0064
  -3.250   0.0730   0.00961   0.00337  -0.0909   0.5979   0.0066
  -3.000   0.0985   0.00938   0.00299  -0.0903   0.5754   0.0066
  -2.750   0.1242   0.00910   0.00258  -0.0898   0.5554   0.0067
  -2.500   0.1502   0.00889   0.00224  -0.0892   0.5378   0.0067
  -2.250   0.1764   0.00866   0.00189  -0.0887   0.5222   0.0069
  -2.000   0.2028   0.00849   0.00160  -0.0883   0.5069   0.0073
  -1.750   0.2294   0.00837   0.00140  -0.0878   0.4940   0.0084
  -1.500   0.2562   0.00831   0.00126  -0.0875   0.4811   0.0097
  -1.250   0.2829   0.00822   0.00116  -0.0871   0.4692   0.0181
  -1.000   0.3096   0.00812   0.00109  -0.0868   0.4590   0.0428
  -0.750   0.3359   0.00794   0.00104  -0.0864   0.4494   0.0976
  -0.500   0.3623   0.00780   0.00101  -0.0861   0.4394   0.1524
  -0.250   0.3884   0.00757   0.00100  -0.0858   0.4301   0.2479
   0.000   0.4144   0.00740   0.00102  -0.0855   0.4216   0.3335
   0.250   0.4406   0.00725   0.00104  -0.0851   0.4134   0.4134
   0.500   0.4666   0.00711   0.00107  -0.0847   0.4053   0.4954
   0.750   0.4924   0.00700   0.00112  -0.0843   0.3967   0.5748
   1.000   0.5183   0.00692   0.00118  -0.0838   0.3880   0.6436
   1.250   0.5439   0.00688   0.00123  -0.0832   0.3788   0.6983
   1.500   0.5653   0.00655   0.00129  -0.0817   0.3711   0.8370
   2.000   0.6399   0.00652   0.00140  -0.0858   0.3547   1.0000
   2.250   0.6664   0.00662   0.00146  -0.0854   0.3477   1.0000
   2.500   0.6928   0.00673   0.00152  -0.0850   0.3400   1.0000
   2.750   0.7193   0.00684   0.00159  -0.0846   0.3327   1.0000
   3.250   0.7719   0.00708   0.00176  -0.0838   0.3150   1.0000
   3.500   0.7981   0.00722   0.00186  -0.0834   0.3061   1.0000
   3.750   0.8243   0.00736   0.00196  -0.0830   0.2967   1.0000
   4.000   0.8506   0.00748   0.00208  -0.0826   0.2893   1.0000
   4.250   0.8766   0.00764   0.00220  -0.0822   0.2801   1.0000
   4.500   0.9023   0.00783   0.00234  -0.0818   0.2673   1.0000
   4.750   0.9279   0.00802   0.00248  -0.0813   0.2550   1.0000
   5.000   0.9534   0.00823   0.00266  -0.0808   0.2414   1.0000
   5.250   0.9781   0.00852   0.00285  -0.0802   0.2188   1.0000
   5.500   1.0022   0.00887   0.00309  -0.0796   0.1933   1.0000
   5.750   1.0264   0.00921   0.00334  -0.0789   0.1736   1.0000
   6.000   1.0498   0.00964   0.00365  -0.0782   0.1475   1.0000
   6.250   1.0708   0.01033   0.00409  -0.0771   0.1052   1.0000
   6.500   1.0929   0.01090   0.00451  -0.0761   0.0764   1.0000
   6.750   1.1146   0.01150   0.00497  -0.0751   0.0505   1.0000
   7.000   1.1351   0.01224   0.00554  -0.0739   0.0232   1.0000
   7.500   1.1789   0.01336   0.00659  -0.0719   0.0045   1.0000
   7.750   1.2023   0.01374   0.00700  -0.0711   0.0038   1.0000
   8.000   1.2253   0.01414   0.00745  -0.0703   0.0035   1.0000
   8.250   1.2483   0.01453   0.00789  -0.0695   0.0033   1.0000
   8.500   1.2707   0.01497   0.00838  -0.0686   0.0032   1.0000
   8.750   1.2927   0.01544   0.00892  -0.0677   0.0030   1.0000
   9.000   1.3141   0.01594   0.00949  -0.0667   0.0029   1.0000
   9.250   1.3347   0.01651   0.01013  -0.0655   0.0027   1.0000
   9.500   1.3549   0.01710   0.01079  -0.0643   0.0026   1.0000
   9.750   1.3742   0.01774   0.01150  -0.0630   0.0025   1.0000
  10.000   1.3925   0.01844   0.01229  -0.0616   0.0024   1.0000
  10.250   1.4099   0.01918   0.01311  -0.0600   0.0024   1.0000
  10.500   1.4254   0.02004   0.01408  -0.0582   0.0023   1.0000
  10.750   1.4400   0.02092   0.01505  -0.0563   0.0022   1.0000
  11.000   1.4526   0.02187   0.01610  -0.0541   0.0021   1.0000
  11.250   1.4609   0.02305   0.01739  -0.0513   0.0021   1.0000
  11.500   1.4628   0.02427   0.01874  -0.0475   0.0020   1.0000
  11.750   1.4609   0.02567   0.02027  -0.0433   0.0019   1.0000
  12.000   1.4580   0.02720   0.02193  -0.0394   0.0019   1.0000
  12.250   1.4575   0.02870   0.02354  -0.0363   0.0019   1.0000
  12.500   1.4554   0.03045   0.02540  -0.0336   0.0019   1.0000
  12.750   1.4529   0.03243   0.02749  -0.0315   0.0019   1.0000
  13.000   1.4503   0.03470   0.02989  -0.0300   0.0019   1.0000
  13.250   1.4477   0.03729   0.03259  -0.0292   0.0018   1.0000
  13.500   1.4438   0.04036   0.03579  -0.0292   0.0018   1.0000
  13.750   1.4347   0.04447   0.04006  -0.0299   0.0018   1.0000
  14.000   1.4296   0.04839   0.04410  -0.0310   0.0018   1.0000
  14.250   1.4227   0.05278   0.04862  -0.0325   0.0018   1.0000
  14.500   1.4137   0.05760   0.05356  -0.0342   0.0018   1.0000
  14.750   1.4072   0.06215   0.05823  -0.0360   0.0018   1.0000
  15.000   1.3928   0.06796   0.06417  -0.0382   0.0018   1.0000
  15.250   1.3797   0.07366   0.07000  -0.0406   0.0018   1.0000
  15.500   1.3656   0.07971   0.07617  -0.0431   0.0018   1.0000
  15.750   1.3535   0.08561   0.08218  -0.0457   0.0018   1.0000
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