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S2050 8.93% (s2050-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S2050 8.93% (s2050-il)
Reynolds number: 500,000
Max Cl/Cd: 70.6 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2050-il-500000-n5.txt
Download as CSV file: xf-s2050-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2050 8.93%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7860   0.05076   0.04810  -0.0458   1.0000   0.0048
 -11.000  -0.8100   0.04374   0.04088  -0.0514   1.0000   0.0048
 -10.750  -0.8297   0.04009   0.03708  -0.0516   1.0000   0.0048
 -10.500  -0.8444   0.03674   0.03350  -0.0503   1.0000   0.0048
 -10.250  -0.8484   0.03368   0.03017  -0.0491   1.0000   0.0048
 -10.000  -0.8466   0.03087   0.02706  -0.0477   1.0000   0.0049
  -9.750  -0.8391   0.02852   0.02444  -0.0464   1.0000   0.0050
  -9.500  -0.8275   0.02654   0.02220  -0.0453   1.0000   0.0051
  -9.250  -0.8125   0.02498   0.02041  -0.0442   1.0000   0.0052
  -9.000  -0.7961   0.02347   0.01867  -0.0432   1.0000   0.0054
  -8.750  -0.7776   0.02230   0.01730  -0.0422   1.0000   0.0055
  -8.500  -0.7586   0.02106   0.01587  -0.0413   1.0000   0.0056
  -8.250  -0.7393   0.01979   0.01442  -0.0404   1.0000   0.0057
  -8.000  -0.7208   0.01810   0.01252  -0.0395   1.0000   0.0059
  -7.750  -0.7002   0.01690   0.01117  -0.0387   1.0000   0.0060
  -7.500  -0.6785   0.01594   0.01010  -0.0380   1.0000   0.0063
  -7.250  -0.6559   0.01515   0.00922  -0.0374   1.0000   0.0065
  -7.000  -0.6328   0.01448   0.00844  -0.0367   1.0000   0.0068
  -6.750  -0.6093   0.01386   0.00774  -0.0362   1.0000   0.0071
  -6.500  -0.5802   0.01328   0.00707  -0.0367   0.9991   0.0076
  -6.250  -0.5474   0.01274   0.00644  -0.0380   0.9973   0.0080
  -6.000  -0.5139   0.01227   0.00589  -0.0394   0.9955   0.0085
  -5.750  -0.4807   0.01172   0.00528  -0.0408   0.9937   0.0100
  -5.500  -0.4485   0.01131   0.00482  -0.0419   0.9912   0.0120
  -5.250  -0.4154   0.01085   0.00437  -0.0432   0.9886   0.0169
  -5.000  -0.3814   0.01043   0.00401  -0.0447   0.9861   0.0278
  -4.750  -0.3463   0.01011   0.00371  -0.0464   0.9841   0.0379
  -4.500  -0.3161   0.00980   0.00344  -0.0470   0.9799   0.0491
  -4.250  -0.2837   0.00951   0.00320  -0.0481   0.9759   0.0641
  -4.000  -0.2493   0.00920   0.00297  -0.0497   0.9726   0.0814
  -3.750  -0.2185   0.00893   0.00275  -0.0504   0.9673   0.0983
  -3.500  -0.1868   0.00868   0.00255  -0.0512   0.9610   0.1139
  -3.250  -0.1554   0.00841   0.00235  -0.0520   0.9542   0.1349
  -3.000  -0.1229   0.00815   0.00215  -0.0530   0.9463   0.1586
  -2.750  -0.0894   0.00785   0.00197  -0.0543   0.9373   0.1933
  -2.500  -0.0530   0.00749   0.00178  -0.0563   0.9273   0.2430
  -2.250  -0.0156   0.00716   0.00158  -0.0584   0.9128   0.2956
  -2.000   0.0204   0.00679   0.00140  -0.0602   0.8915   0.3654
  -1.750   0.0520   0.00652   0.00125  -0.0610   0.8642   0.4324
  -1.500   0.0801   0.00628   0.00115  -0.0611   0.8359   0.5092
  -1.250   0.1067   0.00615   0.00115  -0.0607   0.8086   0.5804
  -1.000   0.1333   0.00616   0.00116  -0.0603   0.7828   0.6253
  -0.750   0.1599   0.00622   0.00118  -0.0598   0.7584   0.6544
  -0.500   0.1866   0.00629   0.00120  -0.0594   0.7348   0.6734
  -0.250   0.2133   0.00638   0.00121  -0.0590   0.7116   0.6884
   0.000   0.2401   0.00647   0.00124  -0.0586   0.6877   0.7011
   0.250   0.2668   0.00657   0.00126  -0.0583   0.6626   0.7136
   0.500   0.2933   0.00668   0.00130  -0.0578   0.6362   0.7271
   0.750   0.3197   0.00680   0.00135  -0.0574   0.6094   0.7394
   1.000   0.3461   0.00692   0.00141  -0.0570   0.5818   0.7500
   1.250   0.3726   0.00706   0.00147  -0.0566   0.5535   0.7605
   1.500   0.3991   0.00722   0.00155  -0.0563   0.5253   0.7706
   1.750   0.4255   0.00737   0.00163  -0.0559   0.4967   0.7787
   2.250   0.4781   0.00773   0.00183  -0.0552   0.4364   0.7942
   2.500   0.5044   0.00794   0.00194  -0.0549   0.4060   0.8026
   2.750   0.5306   0.00814   0.00208  -0.0545   0.3767   0.8109
   3.000   0.5568   0.00835   0.00222  -0.0542   0.3479   0.8183
   3.250   0.5827   0.00859   0.00237  -0.0538   0.3177   0.8262
   3.500   0.6082   0.00888   0.00255  -0.0534   0.2809   0.8344
   3.750   0.6337   0.00916   0.00275  -0.0530   0.2492   0.8439
   4.000   0.6592   0.00939   0.00294  -0.0525   0.2256   0.8536
   4.250   0.6841   0.00969   0.00316  -0.0520   0.1963   0.8641
   4.500   0.7079   0.01008   0.00342  -0.0513   0.1586   0.8765
   4.750   0.7313   0.01045   0.00369  -0.0504   0.1274   0.8914
   5.000   0.7538   0.01078   0.00396  -0.0493   0.1024   0.9098
   5.250   0.7756   0.01110   0.00423  -0.0481   0.0821   0.9346
   5.500   0.8036   0.01140   0.00451  -0.0482   0.0657   0.9832
   5.750   0.8298   0.01179   0.00486  -0.0481   0.0520   1.0000
   6.000   0.8554   0.01222   0.00524  -0.0478   0.0399   1.0000
   6.250   0.8805   0.01271   0.00566  -0.0475   0.0284   1.0000
   6.500   0.9055   0.01321   0.00613  -0.0471   0.0205   1.0000
   6.750   0.9308   0.01366   0.00659  -0.0467   0.0175   1.0000
   7.000   0.9556   0.01414   0.00712  -0.0463   0.0157   1.0000
   7.250   0.9798   0.01473   0.00775  -0.0458   0.0143   1.0000
   7.500   1.0043   0.01524   0.00833  -0.0453   0.0138   1.0000
   7.750   1.0284   0.01578   0.00895  -0.0448   0.0132   1.0000
   8.000   1.0520   0.01637   0.00961  -0.0442   0.0127   1.0000
   8.250   1.0753   0.01699   0.01032  -0.0435   0.0121   1.0000
   8.500   1.0981   0.01762   0.01102  -0.0429   0.0116   1.0000
   8.750   1.1202   0.01833   0.01179  -0.0421   0.0110   1.0000
   9.000   1.1408   0.01921   0.01276  -0.0412   0.0106   1.0000
   9.250   1.1591   0.02035   0.01400  -0.0400   0.0102   1.0000
   9.500   1.1774   0.02146   0.01522  -0.0387   0.0099   1.0000
   9.750   1.1970   0.02235   0.01624  -0.0377   0.0097   1.0000
  10.000   1.2156   0.02333   0.01734  -0.0366   0.0096   1.0000
  10.250   1.2333   0.02437   0.01850  -0.0353   0.0093   1.0000
  10.500   1.2504   0.02540   0.01967  -0.0341   0.0090   1.0000
  10.750   1.2665   0.02647   0.02087  -0.0327   0.0087   1.0000
  11.000   1.2815   0.02757   0.02210  -0.0313   0.0084   1.0000
  11.250   1.2948   0.02873   0.02338  -0.0297   0.0082   1.0000
  11.500   1.3051   0.02999   0.02479  -0.0277   0.0079   1.0000
  11.750   1.3116   0.03128   0.02621  -0.0253   0.0078   1.0000
  12.000   1.3161   0.03266   0.02771  -0.0228   0.0076   1.0000
  12.250   1.3188   0.03421   0.02939  -0.0204   0.0075   1.0000
  12.500   1.3189   0.03605   0.03135  -0.0183   0.0073   1.0000
  12.750   1.3163   0.03827   0.03371  -0.0165   0.0072   1.0000
  13.000   1.3110   0.04096   0.03656  -0.0153   0.0071   1.0000
  13.250   1.3011   0.04447   0.04024  -0.0149   0.0070   1.0000
  13.500   1.2866   0.04901   0.04499  -0.0154   0.0069   1.0000
  13.750   1.2769   0.05341   0.04956  -0.0169   0.0068   1.0000
  14.000   1.2674   0.05822   0.05455  -0.0190   0.0068   1.0000
  14.250   1.2541   0.06408   0.06060  -0.0222   0.0067   1.0000
  14.500   1.2422   0.07021   0.06690  -0.0258   0.0067   1.0000
  14.750   1.2278   0.07721   0.07407  -0.0302   0.0067   1.0000
  15.000   1.2092   0.08537   0.08239  -0.0353   0.0067   1.0000
  15.250   1.1845   0.09513   0.09233  -0.0413   0.0067   1.0000
  15.500   1.1631   0.10475   0.10210  -0.0473   0.0067   1.0000
  15.750   1.1396   0.11526   0.11274  -0.0537   0.0068   1.0000
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