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S2027 (s2027-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S2027 (s2027-il)
Reynolds number: 50,000
Max Cl/Cd: 28.36 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2027-il-50000-n5.txt
Download as CSV file: xf-s2027-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2027                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3942   0.10333   0.09636  -0.0417   1.0000   0.0500
 -10.750  -0.4000   0.09761   0.09072  -0.0446   1.0000   0.0493
 -10.500  -0.4104   0.09072   0.08391  -0.0486   1.0000   0.0485
 -10.250  -0.4390   0.08008   0.07331  -0.0561   1.0000   0.0468
  -9.750  -0.5213   0.06572   0.05871  -0.0659   1.0000   0.0447
  -9.500  -0.5427   0.06310   0.05607  -0.0641   1.0000   0.0446
  -9.250  -0.5623   0.06071   0.05362  -0.0615   1.0000   0.0445
  -9.000  -0.5807   0.05863   0.05145  -0.0582   1.0000   0.0445
  -8.750  -0.5980   0.05660   0.04929  -0.0546   1.0000   0.0445
  -8.500  -0.6121   0.05454   0.04706  -0.0511   1.0000   0.0445
  -8.250  -0.6223   0.05240   0.04470  -0.0479   1.0000   0.0445
  -8.000  -0.6175   0.04941   0.04131  -0.0474   0.9954   0.0449
  -7.750  -0.5930   0.04630   0.03800  -0.0498   0.9862   0.0463
  -7.500  -0.5665   0.04390   0.03538  -0.0520   0.9770   0.0487
  -7.250  -0.5372   0.04133   0.03242  -0.0541   0.9688   0.0510
  -7.000  -0.5083   0.03890   0.02956  -0.0555   0.9599   0.0528
  -6.750  -0.4759   0.03672   0.02697  -0.0568   0.9521   0.0547
  -6.500  -0.4422   0.03484   0.02487  -0.0582   0.9448   0.0569
  -6.250  -0.4112   0.03340   0.02337  -0.0592   0.9366   0.0601
  -6.000  -0.3763   0.03210   0.02184  -0.0608   0.9293   0.0671
  -5.750  -0.3495   0.03088   0.02064  -0.0614   0.9199   0.0748
  -5.500  -0.3171   0.02949   0.01917  -0.0627   0.9128   0.0869
  -5.250  -0.2958   0.02828   0.01801  -0.0623   0.9020   0.1089
  -4.750  -0.2525   0.02517   0.01618  -0.0629   0.8838   0.2935
  -4.500  -0.2346   0.02463   0.01611  -0.0614   0.8730   0.3960
  -4.250  -0.2109   0.02455   0.01620  -0.0601   0.8643   0.4737
  -4.000  -0.1870   0.02464   0.01626  -0.0587   0.8551   0.5287
  -3.750  -0.1652   0.02481   0.01636  -0.0569   0.8452   0.5680
  -3.500  -0.1368   0.02487   0.01626  -0.0561   0.8379   0.6049
  -3.250  -0.1167   0.02503   0.01630  -0.0541   0.8273   0.6326
  -3.000  -0.0909   0.02510   0.01625  -0.0528   0.8192   0.6589
  -2.750  -0.0671   0.02514   0.01614  -0.0515   0.8101   0.6834
  -2.500  -0.0444   0.02521   0.01609  -0.0499   0.8009   0.7047
  -2.250  -0.0174   0.02515   0.01587  -0.0491   0.7934   0.7269
  -2.000   0.0035   0.02522   0.01585  -0.0474   0.7834   0.7458
  -1.750   0.0332   0.02510   0.01559  -0.0469   0.7770   0.7647
  -1.500   0.0530   0.02519   0.01558  -0.0452   0.7665   0.7829
  -1.250   0.0790   0.02513   0.01540  -0.0444   0.7587   0.8014
  -1.000   0.1035   0.02511   0.01529  -0.0435   0.7499   0.8198
  -0.750   0.1292   0.02514   0.01522  -0.0428   0.7411   0.8372
  -0.500   0.1603   0.02505   0.01503  -0.0429   0.7337   0.8546
  -0.250   0.1881   0.02512   0.01503  -0.0429   0.7243   0.8726
   0.000   0.2256   0.02498   0.01476  -0.0442   0.7176   0.8898
   0.250   0.2577   0.02510   0.01482  -0.0453   0.7077   0.9083
   0.500   0.3020   0.02490   0.01449  -0.0479   0.7016   0.9243
   0.750   0.3405   0.02507   0.01460  -0.0506   0.6911   0.9417
   1.000   0.3864   0.02501   0.01446  -0.0542   0.6831   0.9572
   1.250   0.4330   0.02496   0.01434  -0.0581   0.6743   0.9727
   1.500   0.4769   0.02503   0.01435  -0.0619   0.6646   0.9905
   1.750   0.5070   0.02493   0.01417  -0.0628   0.6573   1.0000
   2.000   0.5112   0.02533   0.01453  -0.0598   0.6468   1.0000
   2.250   0.5270   0.02545   0.01456  -0.0580   0.6392   1.0000
   2.500   0.5413   0.02578   0.01483  -0.0563   0.6298   1.0000
   2.750   0.5584   0.02614   0.01513  -0.0550   0.6207   1.0000
   3.000   0.5828   0.02625   0.01516  -0.0544   0.6132   1.0000
   3.250   0.5998   0.02678   0.01566  -0.0532   0.6032   1.0000
   3.500   0.6290   0.02675   0.01558  -0.0530   0.5968   1.0000
   3.750   0.6451   0.02741   0.01625  -0.0518   0.5862   1.0000
   4.000   0.6689   0.02771   0.01652  -0.0512   0.5780   1.0000
   4.250   0.6921   0.02804   0.01687  -0.0506   0.5694   1.0000
   4.500   0.7118   0.02860   0.01745  -0.0497   0.5600   1.0000
   4.750   0.7402   0.02869   0.01751  -0.0496   0.5529   1.0000
   5.000   0.7567   0.02945   0.01833  -0.0484   0.5427   1.0000
   5.250   0.7865   0.02948   0.01837  -0.0483   0.5359   1.0000
   5.500   0.8027   0.03028   0.01924  -0.0472   0.5256   1.0000
   5.750   0.8236   0.03083   0.01984  -0.0464   0.5168   1.0000
   6.000   0.8493   0.03110   0.02015  -0.0460   0.5089   1.0000
   6.250   0.8647   0.03198   0.02115  -0.0448   0.4990   1.0000
   6.500   0.8966   0.03190   0.02109  -0.0448   0.4923   1.0000
   6.750   0.9072   0.03306   0.02238  -0.0433   0.4817   1.0000
   7.000   0.9291   0.03357   0.02296  -0.0426   0.4734   1.0000
   7.250   0.9505   0.03410   0.02360  -0.0418   0.4647   1.0000
   7.500   0.9632   0.03515   0.02477  -0.0404   0.4551   1.0000
   7.750   0.9948   0.03508   0.02475  -0.0403   0.4480   1.0000
   8.000   0.9997   0.03657   0.02640  -0.0384   0.4375   1.0000
   8.250   1.0216   0.03706   0.02698  -0.0376   0.4294   1.0000
   8.500   1.0382   0.03784   0.02790  -0.0364   0.4203   1.0000
   8.750   1.0444   0.03925   0.02945  -0.0346   0.4108   1.0000
   9.000   1.0793   0.03891   0.02920  -0.0347   0.4033   1.0000
   9.250   1.0692   0.04115   0.03158  -0.0316   0.3931   1.0000
   9.500   1.0860   0.04185   0.03239  -0.0304   0.3846   1.0000
   9.750   1.1004   0.04266   0.03336  -0.0291   0.3756   1.0000
  10.000   1.0916   0.04516   0.03598  -0.0269   0.3659   1.0000
  10.250   1.1294   0.04433   0.03525  -0.0266   0.3578   1.0000
  10.500   1.1113   0.04762   0.03869  -0.0244   0.3477   1.0000
  10.750   1.1078   0.05006   0.04125  -0.0231   0.3380   1.0000
  11.000   1.1527   0.04816   0.03945  -0.0224   0.3290   1.0000
  11.250   1.1185   0.05345   0.04488  -0.0211   0.3186   1.0000
  11.500   1.1116   0.05651   0.04806  -0.0204   0.3084   1.0000
  11.750   1.1432   0.05524   0.04693  -0.0191   0.2984   1.0000
  12.000   1.1361   0.05829   0.05010  -0.0185   0.2876   1.0000
  12.250   1.1087   0.06419   0.05612  -0.0191   0.2770   1.0000
  12.500   1.1157   0.06577   0.05781  -0.0185   0.2664   1.0000
  12.750   1.1374   0.06524   0.05737  -0.0172   0.2550   1.0000
  13.000   1.1311   0.06861   0.06085  -0.0174   0.2439   1.0000
  13.250   1.1013   0.07585   0.06820  -0.0193   0.2335   1.0000
  13.500   1.0997   0.07883   0.07128  -0.0196   0.2223   1.0000
  13.750   1.1095   0.07992   0.07245  -0.0191   0.2106   1.0000
  14.000   1.1179   0.08123   0.07381  -0.0188   0.1983   1.0000
  14.250   1.1228   0.08312   0.07577  -0.0188   0.1858   1.0000
  14.500   1.0934   0.09147   0.08424  -0.0219   0.1764   1.0000
  14.750   1.0880   0.09559   0.08846  -0.0232   0.1654   1.0000
  15.000   1.0904   0.09828   0.09118  -0.0237   0.1540   1.0000
  15.250   1.0942   0.10072   0.09361  -0.0242   0.1425   1.0000
  15.500   1.0994   0.10288   0.09570  -0.0246   0.1312   1.0000
  15.750   1.0783   0.11079   0.10380  -0.0281   0.1239   1.0000
  16.000   1.0772   0.11447   0.10747  -0.0294   0.1144   1.0000
  16.250   1.0840   0.11646   0.10935  -0.0299   0.1048   1.0000
  16.500   1.0635   0.12487   0.11797  -0.0340   0.0993   1.0000
  16.750   1.0685   0.12738   0.12040  -0.0349   0.0911   1.0000
  17.000   1.0488   0.13608   0.12928  -0.0394   0.0867   1.0000
  17.250   1.0577   0.13770   0.13080  -0.0400   0.0793   1.0000
  17.500   1.0293   0.14931   0.14261  -0.0464   0.0771   1.0000
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