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S2050 8.93% (s2050-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S2050 8.93% (s2050-il)
Reynolds number: 200,000
Max Cl/Cd: 58.21 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2050-il-200000-n5.txt
Download as CSV file: xf-s2050-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5850   0.08604   0.08237  -0.0231   1.0000   0.0114
 -10.000  -0.6027   0.07782   0.07425  -0.0274   1.0000   0.0111
  -9.750  -0.6555   0.05786   0.05427  -0.0420   1.0000   0.0105
  -9.500  -0.6867   0.05097   0.04722  -0.0463   1.0000   0.0103
  -9.250  -0.7113   0.04544   0.04141  -0.0470   1.0000   0.0102
  -9.000  -0.7252   0.04014   0.03569  -0.0466   1.0000   0.0102
  -8.750  -0.7278   0.03569   0.03076  -0.0457   1.0000   0.0102
  -8.500  -0.7218   0.03215   0.02677  -0.0446   1.0000   0.0103
  -8.250  -0.7104   0.02928   0.02348  -0.0435   1.0000   0.0105
  -8.000  -0.6954   0.02689   0.02072  -0.0425   1.0000   0.0107
  -7.750  -0.6780   0.02486   0.01837  -0.0415   1.0000   0.0110
  -7.500  -0.6591   0.02313   0.01636  -0.0405   1.0000   0.0114
  -7.250  -0.6389   0.02163   0.01460  -0.0396   1.0000   0.0119
  -7.000  -0.6179   0.02039   0.01317  -0.0388   1.0000   0.0125
  -6.750  -0.5967   0.01937   0.01209  -0.0381   1.0000   0.0137
  -6.500  -0.5744   0.01852   0.01114  -0.0374   1.0000   0.0149
  -6.250  -0.5518   0.01757   0.01004  -0.0367   1.0000   0.0160
  -6.000  -0.5290   0.01662   0.00897  -0.0360   1.0000   0.0173
  -5.750  -0.5057   0.01583   0.00811  -0.0354   1.0000   0.0196
  -5.500  -0.4819   0.01509   0.00729  -0.0349   1.0000   0.0237
  -5.250  -0.4580   0.01445   0.00667  -0.0344   1.0000   0.0326
  -5.000  -0.4338   0.01395   0.00619  -0.0339   1.0000   0.0442
  -4.750  -0.4095   0.01355   0.00581  -0.0335   1.0000   0.0566
  -4.500  -0.3852   0.01322   0.00551  -0.0330   1.0000   0.0730
  -4.250  -0.3608   0.01288   0.00518  -0.0326   1.0000   0.0869
  -4.000  -0.3362   0.01256   0.00486  -0.0322   1.0000   0.1002
  -3.750  -0.2994   0.01223   0.00457  -0.0344   0.9960   0.1200
  -3.500  -0.2631   0.01191   0.00428  -0.0364   0.9916   0.1443
  -3.250  -0.2268   0.01155   0.00404  -0.0385   0.9867   0.1786
  -3.000  -0.1908   0.01114   0.00382  -0.0406   0.9818   0.2273
  -2.500  -0.1207   0.01015   0.00339  -0.0443   0.9696   0.3803
  -2.250  -0.0885   0.00962   0.00326  -0.0455   0.9613   0.4838
  -2.000  -0.0567   0.00925   0.00328  -0.0462   0.9527   0.5862
  -1.750  -0.0222   0.00911   0.00325  -0.0473   0.9446   0.6449
  -1.500   0.0098   0.00901   0.00319  -0.0478   0.9334   0.6796
  -1.250   0.0438   0.00893   0.00313  -0.0488   0.9222   0.7066
  -1.000   0.0790   0.00885   0.00306  -0.0500   0.9099   0.7284
  -0.750   0.1144   0.00876   0.00298  -0.0512   0.8956   0.7460
  -0.500   0.1500   0.00869   0.00290  -0.0523   0.8787   0.7622
  -0.250   0.1846   0.00864   0.00284  -0.0533   0.8595   0.7789
   0.000   0.2164   0.00863   0.00280  -0.0536   0.8371   0.7943
   0.250   0.2463   0.00865   0.00277  -0.0536   0.8134   0.8076
   0.500   0.2740   0.00869   0.00275  -0.0531   0.7885   0.8198
   0.750   0.3008   0.00877   0.00275  -0.0525   0.7633   0.8310
   1.000   0.3266   0.00885   0.00277  -0.0517   0.7380   0.8406
   1.250   0.3520   0.00895   0.00279  -0.0509   0.7122   0.8496
   1.500   0.3774   0.00905   0.00282  -0.0501   0.6854   0.8594
   1.750   0.4017   0.00915   0.00286  -0.0491   0.6581   0.8692
   2.000   0.4258   0.00927   0.00292  -0.0480   0.6300   0.8794
   2.250   0.4501   0.00940   0.00297  -0.0471   0.6009   0.8902
   2.750   0.4984   0.00970   0.00311  -0.0452   0.5400   0.9149
   3.000   0.5233   0.00987   0.00321  -0.0444   0.5080   0.9305
   3.250   0.5508   0.01007   0.00332  -0.0443   0.4732   0.9489
   3.500   0.5820   0.01032   0.00345  -0.0451   0.4363   0.9745
   3.750   0.6107   0.01062   0.00365  -0.0455   0.4008   1.0000
   4.000   0.6364   0.01098   0.00388  -0.0453   0.3656   1.0000
   4.250   0.6619   0.01137   0.00413  -0.0451   0.3289   1.0000
   4.500   0.6869   0.01181   0.00441  -0.0448   0.2911   1.0000
   4.750   0.7122   0.01224   0.00475  -0.0445   0.2555   1.0000
   5.000   0.7374   0.01269   0.00509  -0.0442   0.2246   1.0000
   5.250   0.7623   0.01318   0.00548  -0.0439   0.1934   1.0000
   5.500   0.7866   0.01375   0.00590  -0.0435   0.1585   1.0000
   5.750   0.8101   0.01443   0.00640  -0.0431   0.1210   1.0000
   6.000   0.8339   0.01508   0.00691  -0.0427   0.0917   1.0000
   6.250   0.8575   0.01575   0.00747  -0.0422   0.0698   1.0000
   6.500   0.8814   0.01639   0.00808  -0.0417   0.0535   1.0000
   6.750   0.9047   0.01710   0.00878  -0.0411   0.0412   1.0000
   7.000   0.9274   0.01792   0.00964  -0.0404   0.0331   1.0000
   7.250   0.9497   0.01874   0.01051  -0.0397   0.0283   1.0000
   7.500   0.9712   0.01965   0.01150  -0.0388   0.0253   1.0000
   7.750   0.9934   0.02045   0.01240  -0.0380   0.0229   1.0000
   8.000   1.0146   0.02133   0.01337  -0.0372   0.0213   1.0000
   8.250   1.0335   0.02251   0.01462  -0.0361   0.0201   1.0000
   8.500   1.0519   0.02376   0.01601  -0.0349   0.0193   1.0000
   8.750   1.0710   0.02495   0.01734  -0.0338   0.0187   1.0000
   9.000   1.0894   0.02626   0.01881  -0.0326   0.0181   1.0000
   9.250   1.1073   0.02767   0.02038  -0.0314   0.0175   1.0000
   9.500   1.1247   0.02906   0.02193  -0.0302   0.0168   1.0000
   9.750   1.1415   0.03038   0.02339  -0.0291   0.0160   1.0000
  10.000   1.1568   0.03176   0.02491  -0.0278   0.0153   1.0000
  10.250   1.1698   0.03346   0.02675  -0.0264   0.0148   1.0000
  10.500   1.1797   0.03572   0.02919  -0.0248   0.0144   1.0000
  10.750   1.1865   0.03833   0.03204  -0.0229   0.0142   1.0000
  11.000   1.1909   0.04049   0.03448  -0.0207   0.0140   1.0000
  11.250   1.1903   0.04282   0.03709  -0.0182   0.0138   1.0000
  11.500   1.1857   0.04543   0.03998  -0.0157   0.0137   1.0000
  11.750   1.1777   0.04840   0.04322  -0.0138   0.0135   1.0000
  12.000   1.1668   0.05184   0.04693  -0.0128   0.0134   1.0000
  12.250   1.1540   0.05582   0.05116  -0.0128   0.0134   1.0000
  12.500   1.1387   0.06057   0.05617  -0.0141   0.0133   1.0000
  12.750   1.1212   0.06625   0.06208  -0.0168   0.0133   1.0000
  13.000   1.1027   0.07286   0.06890  -0.0207   0.0133   1.0000
  13.250   1.0822   0.08064   0.07688  -0.0260   0.0134   1.0000
  13.500   1.0596   0.08972   0.08615  -0.0324   0.0135   1.0000
  13.750   1.0351   0.10010   0.09668  -0.0396   0.0136   1.0000
  14.000   1.0083   0.11188   0.10859  -0.0474   0.0138   1.0000
  14.250   0.9758   0.12623   0.12304  -0.0563   0.0140   1.0000
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