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S2050 8.93% (s2050-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S2050 8.93% (s2050-il)
Reynolds number: 100,000
Max Cl/Cd: 47.04 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2050-il-100000-n5.txt
Download as CSV file: xf-s2050-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5589   0.09055   0.08538  -0.0233   1.0000   0.0219
  -9.750  -0.5669   0.08428   0.07917  -0.0265   1.0000   0.0219
  -9.500  -0.5759   0.07785   0.07281  -0.0301   1.0000   0.0217
  -9.250  -0.5870   0.07035   0.06535  -0.0351   1.0000   0.0212
  -9.000  -0.6099   0.06239   0.05737  -0.0412   1.0000   0.0209
  -8.750  -0.6304   0.05718   0.05207  -0.0433   1.0000   0.0204
  -8.500  -0.6451   0.05189   0.04658  -0.0444   1.0000   0.0202
  -8.250  -0.6531   0.04688   0.04123  -0.0446   1.0000   0.0203
  -8.000  -0.6541   0.04224   0.03610  -0.0443   1.0000   0.0206
  -7.750  -0.6486   0.03798   0.03133  -0.0436   1.0000   0.0209
  -7.500  -0.6378   0.03426   0.02707  -0.0428   1.0000   0.0213
  -7.250  -0.6227   0.03108   0.02336  -0.0418   1.0000   0.0219
  -7.000  -0.6046   0.02851   0.02037  -0.0408   1.0000   0.0226
  -6.750  -0.5859   0.02651   0.01822  -0.0400   1.0000   0.0237
  -6.500  -0.5654   0.02496   0.01651  -0.0392   1.0000   0.0252
  -6.250  -0.5439   0.02362   0.01495  -0.0383   1.0000   0.0283
  -6.000  -0.5226   0.02223   0.01341  -0.0375   1.0000   0.0323
  -5.750  -0.5005   0.02101   0.01207  -0.0367   1.0000   0.0375
  -5.500  -0.4782   0.01988   0.01089  -0.0359   1.0000   0.0455
  -5.250  -0.4552   0.01913   0.01011  -0.0354   1.0000   0.0589
  -5.000  -0.4319   0.01847   0.00938  -0.0348   1.0000   0.0744
  -4.750  -0.4086   0.01777   0.00862  -0.0341   1.0000   0.0889
  -4.500  -0.3851   0.01710   0.00794  -0.0336   1.0000   0.1035
  -4.250  -0.3616   0.01648   0.00737  -0.0330   1.0000   0.1201
  -4.000  -0.3379   0.01592   0.00685  -0.0325   1.0000   0.1393
  -3.750  -0.3140   0.01541   0.00640  -0.0321   1.0000   0.1641
  -3.500  -0.2901   0.01490   0.00599  -0.0316   1.0000   0.1969
  -3.250  -0.2662   0.01438   0.00565  -0.0313   1.0000   0.2423
  -3.000  -0.2423   0.01382   0.00537  -0.0310   1.0000   0.3099
  -2.750  -0.2189   0.01321   0.00518  -0.0307   1.0000   0.4064
  -2.500  -0.1978   0.01272   0.00522  -0.0294   1.0000   0.5266
  -2.250  -0.1782   0.01262   0.00541  -0.0275   1.0000   0.6237
  -2.000  -0.1517   0.01268   0.00552  -0.0271   0.9969   0.6815
  -1.750  -0.1157   0.01277   0.00562  -0.0286   0.9877   0.7254
  -1.500  -0.0810   0.01283   0.00566  -0.0296   0.9778   0.7591
  -1.250  -0.0468   0.01285   0.00567  -0.0305   0.9673   0.7872
  -1.000  -0.0131   0.01284   0.00565  -0.0313   0.9566   0.8114
  -0.750   0.0188   0.01278   0.00559  -0.0315   0.9449   0.8344
  -0.500   0.0494   0.01270   0.00550  -0.0315   0.9324   0.8580
  -0.250   0.0797   0.01257   0.00539  -0.0313   0.9197   0.8797
   0.000   0.1123   0.01243   0.00525  -0.0316   0.9067   0.9001
   0.250   0.1472   0.01229   0.00511  -0.0325   0.8928   0.9176
   0.500   0.1856   0.01215   0.00496  -0.0343   0.8780   0.9322
   0.750   0.2267   0.01202   0.00482  -0.0366   0.8621   0.9449
   1.000   0.2702   0.01191   0.00468  -0.0394   0.8446   0.9560
   1.250   0.3128   0.01182   0.00459  -0.0422   0.8235   0.9676
   1.500   0.3555   0.01176   0.00448  -0.0449   0.8005   0.9790
   2.000   0.4240   0.01180   0.00443  -0.0473   0.7461   1.0000
   2.250   0.4508   0.01192   0.00447  -0.0470   0.7177   1.0000
   2.500   0.4774   0.01207   0.00454  -0.0467   0.6884   1.0000
   2.750   0.5037   0.01226   0.00464  -0.0463   0.6578   1.0000
   3.000   0.5298   0.01247   0.00478  -0.0459   0.6262   1.0000
   3.250   0.5555   0.01272   0.00493  -0.0454   0.5931   1.0000
   3.500   0.5809   0.01299   0.00511  -0.0448   0.5585   1.0000
   4.000   0.6307   0.01366   0.00559  -0.0436   0.4856   1.0000
   4.250   0.6551   0.01405   0.00587  -0.0429   0.4479   1.0000
   4.500   0.6793   0.01448   0.00619  -0.0422   0.4094   1.0000
   4.750   0.7032   0.01495   0.00658  -0.0416   0.3702   1.0000
   5.000   0.7267   0.01547   0.00698  -0.0409   0.3304   1.0000
   5.250   0.7499   0.01606   0.00743  -0.0402   0.2901   1.0000
   5.500   0.7729   0.01668   0.00794  -0.0396   0.2500   1.0000
   5.750   0.7960   0.01735   0.00851  -0.0390   0.2128   1.0000
   6.000   0.8184   0.01811   0.00918  -0.0383   0.1782   1.0000
   6.250   0.8406   0.01894   0.00990  -0.0376   0.1432   1.0000
   6.500   0.8618   0.01991   0.01068  -0.0369   0.1091   1.0000
   6.750   0.8829   0.02092   0.01157  -0.0362   0.0829   1.0000
   7.000   0.9037   0.02200   0.01264  -0.0353   0.0651   1.0000
   7.250   0.9236   0.02319   0.01387  -0.0343   0.0529   1.0000
   7.500   0.9425   0.02447   0.01516  -0.0332   0.0447   1.0000
   7.750   0.9619   0.02573   0.01657  -0.0321   0.0398   1.0000
   8.000   0.9799   0.02714   0.01806  -0.0309   0.0367   1.0000
   8.250   0.9971   0.02885   0.01987  -0.0296   0.0346   1.0000
   8.500   1.0163   0.03047   0.02170  -0.0284   0.0328   1.0000
   8.750   1.0351   0.03205   0.02351  -0.0274   0.0306   1.0000
   9.000   1.0525   0.03357   0.02515  -0.0263   0.0286   1.0000
   9.250   1.0683   0.03550   0.02717  -0.0253   0.0272   1.0000
   9.500   1.0835   0.03806   0.02994  -0.0241   0.0264   1.0000
   9.750   1.0974   0.04056   0.03281  -0.0228   0.0258   1.0000
  10.000   1.1076   0.04338   0.03601  -0.0212   0.0253   1.0000
  10.250   1.1132   0.04647   0.03951  -0.0195   0.0249   1.0000
  10.500   1.1135   0.04976   0.04319  -0.0175   0.0245   1.0000
  10.750   1.1073   0.05300   0.04678  -0.0152   0.0243   1.0000
  11.000   1.0956   0.05633   0.05042  -0.0130   0.0240   1.0000
  11.250   1.0806   0.06004   0.05440  -0.0117   0.0238   1.0000
  11.500   1.0626   0.06442   0.05905  -0.0119   0.0237   1.0000
  11.750   1.0420   0.06978   0.06464  -0.0138   0.0237   1.0000
  12.000   1.0188   0.07644   0.07152  -0.0177   0.0239   1.0000
  12.250   0.9934   0.08475   0.08001  -0.0235   0.0244   1.0000
  12.500   0.9656   0.09504   0.09045  -0.0311   0.0249   1.0000
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