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S4083 (8%) (s4083-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S4083 (8%) (s4083-il)
Reynolds number: 200,000
Max Cl/Cd: 73.3 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4083-il-200000.txt
Download as CSV file: xf-s4083-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3703   0.08747   0.08414  -0.0181   1.0000   0.0354
  -7.000  -0.3735   0.08497   0.08170  -0.0179   1.0000   0.0363
  -6.750  -0.3730   0.08205   0.07885  -0.0190   1.0000   0.0372
  -6.500  -0.3696   0.07874   0.07558  -0.0218   1.0000   0.0385
  -6.250  -0.3588   0.07472   0.07158  -0.0298   1.0000   0.0400
  -6.000  -0.3419   0.07020   0.06699  -0.0376   1.0000   0.0406
  -5.750  -0.3272   0.06597   0.06265  -0.0417   1.0000   0.0408
  -5.500  -0.3280   0.06012   0.05691  -0.0410   1.0000   0.0419
  -5.250  -0.3210   0.05772   0.05455  -0.0391   1.0000   0.0430
  -5.000  -0.3095   0.05502   0.05186  -0.0390   1.0000   0.0445
  -4.750  -0.2942   0.05176   0.04854  -0.0405   1.0000   0.0468
  -4.500  -0.2722   0.04763   0.04426  -0.0439   1.0000   0.0505
  -4.250  -0.2445   0.04160   0.03777  -0.0491   1.0000   0.0549
  -4.000  -0.2307   0.03934   0.03559  -0.0483   1.0000   0.0569
  -3.750  -0.2126   0.03710   0.03327  -0.0483   1.0000   0.0605
  -3.500  -0.1684   0.03290   0.02867  -0.0539   0.9960   0.0709
  -3.250  -0.1250   0.03006   0.02561  -0.0586   0.9904   0.0854
  -3.000  -0.0802   0.02725   0.02252  -0.0630   0.9849   0.0996
  -2.750  -0.0294   0.01933   0.01303  -0.0633   0.9814   0.0371
  -2.500   0.0144   0.01685   0.01006  -0.0657   0.9754   0.0343
  -2.250   0.0553   0.01518   0.00815  -0.0677   0.9663   0.0343
  -2.000   0.0966   0.01388   0.00676  -0.0698   0.9565   0.0369
  -1.750   0.1381   0.01270   0.00557  -0.0721   0.9455   0.0450
  -1.500   0.1782   0.01140   0.00435  -0.0740   0.9316   0.0816
  -1.250   0.2151   0.00950   0.00398  -0.0764   0.9138   0.4664
  -1.000   0.2724   0.00795   0.00368  -0.0813   0.8960   1.0000
  -0.750   0.3297   0.00781   0.00317  -0.0870   0.8588   1.0000
  -0.250   0.4077   0.00811   0.00269  -0.0907   0.7570   1.0000
   0.000   0.4336   0.00840   0.00263  -0.0899   0.7161   1.0000
   0.250   0.4584   0.00869   0.00262  -0.0890   0.6826   1.0000
   0.500   0.4830   0.00896   0.00264  -0.0881   0.6546   1.0000
   0.750   0.5079   0.00923   0.00268  -0.0873   0.6307   1.0000
   1.000   0.5329   0.00949   0.00275  -0.0865   0.6099   1.0000
   1.250   0.5582   0.00975   0.00283  -0.0859   0.5918   1.0000
   1.500   0.5837   0.00999   0.00293  -0.0852   0.5746   1.0000
   1.750   0.6092   0.01023   0.00304  -0.0847   0.5590   1.0000
   2.000   0.6349   0.01048   0.00319  -0.0841   0.5448   1.0000
   2.250   0.6606   0.01072   0.00333  -0.0835   0.5314   1.0000
   2.500   0.6863   0.01097   0.00348  -0.0830   0.5188   1.0000
   3.000   0.7377   0.01145   0.00385  -0.0820   0.4946   1.0000
   3.250   0.7634   0.01169   0.00405  -0.0815   0.4830   1.0000
   3.500   0.7891   0.01194   0.00426  -0.0810   0.4722   1.0000
   3.750   0.8149   0.01222   0.00448  -0.0805   0.4621   1.0000
   4.000   0.8405   0.01246   0.00471  -0.0800   0.4515   1.0000
   4.250   0.8660   0.01270   0.00500  -0.0794   0.4408   1.0000
   4.500   0.8914   0.01297   0.00526  -0.0789   0.4305   1.0000
   4.750   0.9168   0.01325   0.00550  -0.0783   0.4204   1.0000
   5.000   0.9418   0.01347   0.00577  -0.0777   0.4094   1.0000
   5.250   0.9667   0.01373   0.00610  -0.0771   0.3986   1.0000
   5.500   0.9916   0.01400   0.00640  -0.0765   0.3881   1.0000
   5.750   1.0163   0.01428   0.00669  -0.0758   0.3774   1.0000
   6.000   1.0406   0.01453   0.00698  -0.0751   0.3656   1.0000
   6.250   1.0646   0.01476   0.00732  -0.0743   0.3530   1.0000
   6.500   1.0884   0.01501   0.00765  -0.0735   0.3404   1.0000
   6.750   1.1121   0.01528   0.00799  -0.0727   0.3273   1.0000
   7.000   1.1353   0.01554   0.00833  -0.0718   0.3131   1.0000
   7.250   1.1580   0.01581   0.00870  -0.0708   0.2976   1.0000
   7.500   1.1798   0.01612   0.00903  -0.0697   0.2799   1.0000
   7.750   1.2014   0.01639   0.00938  -0.0686   0.2566   1.0000
   8.000   1.2218   0.01679   0.00977  -0.0674   0.2285   1.0000
   8.250   1.2410   0.01737   0.01027  -0.0661   0.1959   1.0000
   8.500   1.2587   0.01820   0.01095  -0.0647   0.1592   1.0000
   8.750   1.2758   0.01914   0.01183  -0.0632   0.1263   1.0000
   9.000   1.2889   0.02053   0.01299  -0.0613   0.0832   1.0000
   9.250   1.2871   0.02343   0.01543  -0.0572   0.0342   1.0000
   9.500   1.2921   0.02538   0.01748  -0.0539   0.0267   1.0000
   9.750   1.2994   0.02694   0.01921  -0.0510   0.0238   1.0000
  10.000   1.3069   0.02835   0.02074  -0.0483   0.0215   1.0000
  10.250   1.3082   0.02994   0.02242  -0.0448   0.0198   1.0000
  10.500   1.3043   0.03195   0.02452  -0.0409   0.0190   1.0000
  10.750   1.2974   0.03453   0.02721  -0.0371   0.0183   1.0000
  11.000   1.2994   0.03656   0.02938  -0.0346   0.0179   1.0000
  11.250   1.3025   0.03867   0.03164  -0.0325   0.0176   1.0000
  11.500   1.3057   0.04099   0.03416  -0.0307   0.0172   1.0000
  11.750   1.3088   0.04354   0.03688  -0.0291   0.0170   1.0000
  12.000   1.3111   0.04631   0.03984  -0.0277   0.0168   1.0000
  12.250   1.3116   0.04938   0.04312  -0.0266   0.0165   1.0000
  12.500   1.3103   0.05274   0.04671  -0.0257   0.0165   1.0000
  12.750   1.3063   0.05641   0.05062  -0.0254   0.0165   1.0000
  13.000   1.2991   0.06057   0.05502  -0.0255   0.0165   1.0000
  13.250   1.2897   0.06513   0.05983  -0.0262   0.0166   1.0000
  13.500   1.2782   0.07012   0.06505  -0.0276   0.0167   1.0000
  13.750   1.2649   0.07557   0.07073  -0.0296   0.0167   1.0000
  14.000   1.2501   0.08150   0.07688  -0.0322   0.0169   1.0000
  14.250   1.2337   0.08794   0.08352  -0.0354   0.0170   1.0000
  14.500   1.2165   0.09479   0.09057  -0.0391   0.0171   1.0000
  14.750   1.1987   0.10209   0.09805  -0.0433   0.0172   1.0000
  15.000   1.1802   0.10992   0.10605  -0.0481   0.0174   1.0000
  15.250   1.1617   0.11824   0.11452  -0.0533   0.0175   1.0000
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