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S2050 8.93% (s2050-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S2050 8.93% (s2050-il)
Reynolds number: 200,000
Max Cl/Cd: 63.53 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2050-il-200000.txt
Download as CSV file: xf-s2050-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5260   0.08699   0.08343  -0.0237   1.0000   0.0549
  -8.750  -0.5295   0.08276   0.07925  -0.0256   1.0000   0.0559
  -8.500  -0.5368   0.07810   0.07464  -0.0282   1.0000   0.0571
  -8.250  -0.5508   0.07285   0.06947  -0.0320   1.0000   0.0575
  -8.000  -0.5671   0.06689   0.06352  -0.0369   1.0000   0.0580
  -7.750  -0.6331   0.04312   0.03860  -0.0439   1.0000   0.0290
  -7.500  -0.6306   0.03809   0.03325  -0.0432   1.0000   0.0280
  -7.250  -0.6233   0.03318   0.02784  -0.0423   1.0000   0.0270
  -7.000  -0.6102   0.02899   0.02309  -0.0412   1.0000   0.0265
  -6.750  -0.5925   0.02582   0.01943  -0.0402   1.0000   0.0266
  -6.500  -0.5718   0.02368   0.01691  -0.0392   1.0000   0.0278
  -6.250  -0.5491   0.02257   0.01548  -0.0383   1.0000   0.0296
  -6.000  -0.5281   0.01981   0.01248  -0.0374   1.0000   0.0313
  -5.750  -0.5056   0.01842   0.01101  -0.0366   1.0000   0.0335
  -5.500  -0.4822   0.01727   0.00975  -0.0357   1.0000   0.0371
  -5.250  -0.4592   0.01590   0.00836  -0.0349   1.0000   0.0435
  -5.000  -0.4353   0.01511   0.00758  -0.0343   1.0000   0.0581
  -4.750  -0.4110   0.01453   0.00693  -0.0337   1.0000   0.0751
  -4.500  -0.3871   0.01390   0.00638  -0.0333   1.0000   0.0933
  -4.250  -0.3628   0.01343   0.00594  -0.0329   1.0000   0.1116
  -4.000  -0.3382   0.01292   0.00545  -0.0324   1.0000   0.1314
  -3.750  -0.3135   0.01238   0.00503  -0.0322   1.0000   0.1559
  -3.500  -0.2886   0.01187   0.00465  -0.0320   1.0000   0.1892
  -3.250  -0.2634   0.01128   0.00434  -0.0319   1.0000   0.2425
  -3.000  -0.2382   0.01057   0.00411  -0.0321   1.0000   0.3443
  -2.750  -0.2142   0.00977   0.00405  -0.0319   1.0000   0.5089
  -2.500  -0.1935   0.00958   0.00429  -0.0304   1.0000   0.6344
  -2.250  -0.1728   0.00965   0.00446  -0.0289   1.0000   0.6897
  -2.000  -0.1528   0.00977   0.00462  -0.0273   1.0000   0.7259
  -1.750  -0.1242   0.00995   0.00481  -0.0275   0.9969   0.7569
  -1.500  -0.0833   0.01012   0.00499  -0.0300   0.9886   0.7844
  -1.250  -0.0436   0.01022   0.00511  -0.0320   0.9802   0.8072
  -1.000  -0.0029   0.01027   0.00514  -0.0343   0.9718   0.8293
  -0.750   0.0323   0.01019   0.00509  -0.0353   0.9610   0.8474
  -0.500   0.0679   0.01007   0.00499  -0.0363   0.9506   0.8638
  -0.250   0.1060   0.00992   0.00486  -0.0378   0.9423   0.8797
   0.000   0.1400   0.00972   0.00468  -0.0383   0.9318   0.8964
   0.250   0.1719   0.00950   0.00449  -0.0383   0.9201   0.9133
   0.500   0.2044   0.00927   0.00428  -0.0384   0.9077   0.9288
   0.750   0.2396   0.00905   0.00406  -0.0391   0.8939   0.9429
   1.000   0.2796   0.00886   0.00387  -0.0410   0.8777   0.9539
   1.250   0.3225   0.00871   0.00369  -0.0436   0.8589   0.9624
   1.500   0.3625   0.00863   0.00357  -0.0457   0.8346   0.9715
   1.750   0.4047   0.00861   0.00348  -0.0483   0.8080   0.9788
   2.000   0.4453   0.00863   0.00343  -0.0508   0.7786   0.9873
   2.250   0.4857   0.00869   0.00340  -0.0532   0.7474   0.9965
   2.500   0.5091   0.00881   0.00341  -0.0526   0.7172   1.0000
   2.750   0.5267   0.00896   0.00346  -0.0507   0.6876   1.0000
   3.000   0.5490   0.00916   0.00356  -0.0498   0.6559   1.0000
   3.250   0.5735   0.00938   0.00366  -0.0492   0.6220   1.0000
   3.500   0.5987   0.00963   0.00378  -0.0487   0.5860   1.0000
   3.750   0.6239   0.00992   0.00393  -0.0482   0.5490   1.0000
   4.000   0.6488   0.01024   0.00413  -0.0477   0.5098   1.0000
   4.250   0.6734   0.01060   0.00435  -0.0471   0.4683   1.0000
   4.500   0.6977   0.01100   0.00459  -0.0465   0.4256   1.0000
   4.750   0.7219   0.01143   0.00489  -0.0459   0.3830   1.0000
   5.000   0.7460   0.01190   0.00522  -0.0453   0.3411   1.0000
   5.250   0.7698   0.01242   0.00559  -0.0447   0.2978   1.0000
   5.500   0.7929   0.01303   0.00599  -0.0441   0.2501   1.0000
   5.750   0.8157   0.01372   0.00647  -0.0435   0.2002   1.0000
   6.000   0.8384   0.01446   0.00701  -0.0429   0.1566   1.0000
   6.250   0.8606   0.01531   0.00766  -0.0422   0.1181   1.0000
   6.500   0.8818   0.01634   0.00849  -0.0413   0.0837   1.0000
   6.750   0.9016   0.01763   0.00967  -0.0401   0.0597   1.0000
   7.000   0.9216   0.01890   0.01097  -0.0388   0.0492   1.0000
   7.250   0.9406   0.02037   0.01243  -0.0375   0.0434   1.0000
   7.500   0.9628   0.02142   0.01358  -0.0366   0.0394   1.0000
   7.750   0.9838   0.02277   0.01495  -0.0356   0.0368   1.0000
   8.000   1.0036   0.02553   0.01775  -0.0346   0.0347   1.0000
   8.250   1.0265   0.02711   0.01953  -0.0337   0.0339   1.0000
   8.500   1.0485   0.02882   0.02151  -0.0328   0.0327   1.0000
   8.750   1.0690   0.03048   0.02342  -0.0317   0.0310   1.0000
   9.000   1.0880   0.03260   0.02580  -0.0306   0.0300   1.0000
   9.250   1.1045   0.03521   0.02873  -0.0293   0.0294   1.0000
   9.500   1.1172   0.03832   0.03222  -0.0276   0.0292   1.0000
   9.750   1.1237   0.04213   0.03651  -0.0254   0.0294   1.0000
  10.000   1.1212   0.04685   0.04177  -0.0227   0.0300   1.0000
  10.250   1.1119   0.05176   0.04715  -0.0200   0.0308   1.0000
  10.500   1.0976   0.05618   0.05191  -0.0174   0.0312   1.0000
  10.750   1.0772   0.06016   0.05614  -0.0146   0.0317   1.0000
  11.000   1.0550   0.06438   0.06057  -0.0132   0.0321   1.0000
  11.250   1.0313   0.06932   0.06570  -0.0140   0.0325   1.0000
  11.500   1.0070   0.07541   0.07194  -0.0169   0.0330   1.0000
  11.750   0.9821   0.08273   0.07938  -0.0217   0.0334   1.0000
  12.000   0.9594   0.09124   0.08797  -0.0273   0.0341   1.0000
  12.250   0.7811   0.11352   0.11069  -0.0410   0.0370   1.0000
  12.500   0.7925   0.11331   0.11049  -0.0400   0.0359   1.0000
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