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S2027 (s2027-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S2027 (s2027-il)
Reynolds number: 200,000
Max Cl/Cd: 69.34 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2027-il-200000.txt
Download as CSV file: xf-s2027-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3748   0.11079   0.10732  -0.0344   1.0000   0.0644
 -11.000  -0.4079   0.10261   0.09925  -0.0451   1.0000   0.0678
 -10.750  -0.4148   0.09589   0.09259  -0.0477   1.0000   0.0687
 -10.500  -0.3959   0.09451   0.09121  -0.0447   1.0000   0.0698
 -10.250  -0.3855   0.09218   0.08890  -0.0443   1.0000   0.0711
 -10.000  -0.3809   0.08906   0.08580  -0.0451   1.0000   0.0727
  -9.750  -0.3820   0.08510   0.08188  -0.0470   1.0000   0.0748
  -8.750  -0.5148   0.05832   0.05487  -0.0712   0.9797   0.0825
  -8.500  -0.5260   0.04032   0.03555  -0.0759   0.9689   0.0426
  -8.250  -0.5159   0.03313   0.02721  -0.0765   0.9584   0.0362
  -8.000  -0.4885   0.03126   0.02498  -0.0772   0.9499   0.0356
  -7.750  -0.4587   0.02927   0.02269  -0.0782   0.9431   0.0354
  -7.500  -0.4367   0.02680   0.01994  -0.0777   0.9330   0.0356
  -7.250  -0.4122   0.02436   0.01734  -0.0776   0.9253   0.0367
  -7.000  -0.3896   0.02305   0.01593  -0.0768   0.9154   0.0377
  -6.750  -0.3670   0.02184   0.01462  -0.0757   0.9058   0.0383
  -6.500  -0.3441   0.02075   0.01343  -0.0745   0.8978   0.0390
  -6.250  -0.3228   0.01983   0.01245  -0.0731   0.8873   0.0398
  -6.000  -0.3012   0.01899   0.01155  -0.0718   0.8784   0.0412
  -5.750  -0.2798   0.01823   0.01069  -0.0704   0.8695   0.0428
  -5.500  -0.2579   0.01761   0.00998  -0.0692   0.8598   0.0446
  -5.250  -0.2384   0.01666   0.00901  -0.0677   0.8523   0.0482
  -5.000  -0.2158   0.01613   0.00843  -0.0668   0.8421   0.0549
  -4.750  -0.1946   0.01525   0.00758  -0.0656   0.8338   0.0712
  -4.500  -0.1787   0.01355   0.00672  -0.0642   0.8249   0.2267
  -4.250  -0.1571   0.01288   0.00642  -0.0634   0.8159   0.3245
  -4.000  -0.1338   0.01244   0.00620  -0.0625   0.8083   0.4014
  -3.750  -0.1102   0.01218   0.00618  -0.0616   0.7989   0.4738
  -3.500  -0.0850   0.01206   0.00609  -0.0607   0.7920   0.5231
  -3.250  -0.0599   0.01206   0.00614  -0.0599   0.7822   0.5637
  -3.000  -0.0341   0.01208   0.00615  -0.0590   0.7747   0.5969
  -2.750  -0.0080   0.01210   0.00612  -0.0584   0.7657   0.6219
  -2.500   0.0184   0.01210   0.00607  -0.0577   0.7575   0.6408
  -2.250   0.0450   0.01209   0.00601  -0.0571   0.7493   0.6591
  -2.000   0.0714   0.01210   0.00598  -0.0565   0.7406   0.6766
  -1.750   0.0983   0.01208   0.00588  -0.0559   0.7329   0.6929
  -1.500   0.1247   0.01208   0.00586  -0.0554   0.7239   0.7079
  -1.250   0.1517   0.01206   0.00575  -0.0548   0.7168   0.7223
  -1.000   0.1779   0.01205   0.00575  -0.0544   0.7072   0.7361
  -0.750   0.2047   0.01204   0.00567  -0.0538   0.6998   0.7497
  -0.500   0.2311   0.01203   0.00564  -0.0534   0.6908   0.7631
  -0.250   0.2577   0.01203   0.00559  -0.0529   0.6828   0.7765
   0.000   0.2842   0.01201   0.00554  -0.0524   0.6744   0.7899
   0.250   0.3103   0.01202   0.00554  -0.0519   0.6661   0.8032
   0.500   0.3364   0.01201   0.00548  -0.0512   0.6582   0.8162
   0.750   0.3618   0.01202   0.00551  -0.0506   0.6495   0.8297
   1.000   0.3877   0.01201   0.00545  -0.0499   0.6421   0.8437
   1.250   0.4122   0.01202   0.00550  -0.0490   0.6329   0.8586
   1.500   0.4376   0.01203   0.00546  -0.0482   0.6258   0.8741
   1.750   0.4616   0.01204   0.00551  -0.0472   0.6166   0.8911
   2.000   0.4871   0.01206   0.00550  -0.0465   0.6091   0.9095
   2.250   0.5153   0.01207   0.00552  -0.0463   0.6002   0.9278
   2.500   0.5496   0.01213   0.00556  -0.0475   0.5916   0.9453
   2.750   0.5900   0.01218   0.00555  -0.0501   0.5829   0.9609
   3.000   0.6333   0.01226   0.00564  -0.0534   0.5728   0.9753
   3.250   0.6794   0.01235   0.00566  -0.0574   0.5637   0.9875
   3.500   0.7254   0.01242   0.00569  -0.0615   0.5538   1.0000
   3.750   0.7390   0.01255   0.00581  -0.0595   0.5456   1.0000
   4.000   0.7597   0.01270   0.00587  -0.0585   0.5378   1.0000
   4.250   0.7823   0.01288   0.00605  -0.0578   0.5286   1.0000
   4.500   0.8076   0.01307   0.00615  -0.0575   0.5208   1.0000
   4.750   0.8320   0.01326   0.00637  -0.0570   0.5113   1.0000
   5.000   0.8574   0.01347   0.00656  -0.0567   0.5028   1.0000
   5.250   0.8830   0.01367   0.00672  -0.0565   0.4939   1.0000
   5.500   0.9079   0.01390   0.00697  -0.0561   0.4846   1.0000
   5.750   0.9342   0.01413   0.00715  -0.0559   0.4765   1.0000
   6.000   0.9585   0.01435   0.00743  -0.0555   0.4665   1.0000
   6.250   0.9837   0.01461   0.00769  -0.0552   0.4576   1.0000
   6.500   1.0090   0.01486   0.00792  -0.0549   0.4487   1.0000
   6.750   1.0331   0.01513   0.00826  -0.0544   0.4389   1.0000
   7.000   1.0580   0.01541   0.00852  -0.0541   0.4300   1.0000
   7.250   1.0820   0.01568   0.00882  -0.0536   0.4203   1.0000
   7.500   1.1055   0.01599   0.00920  -0.0530   0.4105   1.0000
   7.750   1.1300   0.01632   0.00949  -0.0526   0.4017   1.0000
   8.000   1.1524   0.01662   0.00988  -0.0519   0.3915   1.0000
   8.250   1.1749   0.01697   0.01028  -0.0512   0.3815   1.0000
   8.500   1.1972   0.01732   0.01062  -0.0505   0.3713   1.0000
   8.750   1.2178   0.01764   0.01098  -0.0495   0.3600   1.0000
   9.000   1.2371   0.01799   0.01142  -0.0484   0.3482   1.0000
   9.250   1.2559   0.01838   0.01185  -0.0472   0.3365   1.0000
   9.500   1.2735   0.01878   0.01228  -0.0458   0.3246   1.0000
   9.750   1.2905   0.01924   0.01275  -0.0444   0.3133   1.0000
  10.000   1.3057   0.01971   0.01329  -0.0427   0.3017   1.0000
  10.250   1.3195   0.02022   0.01389  -0.0409   0.2902   1.0000
  10.500   1.3294   0.02076   0.01448  -0.0384   0.2784   1.0000
  10.750   1.3359   0.02140   0.01515  -0.0356   0.2654   1.0000
  11.000   1.3410   0.02218   0.01595  -0.0330   0.2513   1.0000
  11.250   1.3449   0.02312   0.01690  -0.0304   0.2360   1.0000
  11.500   1.3478   0.02425   0.01804  -0.0281   0.2198   1.0000
  11.750   1.3495   0.02560   0.01940  -0.0260   0.2034   1.0000
  12.000   1.3506   0.02716   0.02094  -0.0241   0.1876   1.0000
  12.250   1.3500   0.02896   0.02272  -0.0224   0.1717   1.0000
  12.500   1.3491   0.03095   0.02471  -0.0209   0.1545   1.0000
  12.750   1.3445   0.03338   0.02709  -0.0196   0.1365   1.0000
  13.000   1.3375   0.03616   0.02982  -0.0184   0.1205   1.0000
  13.250   1.3289   0.03928   0.03289  -0.0176   0.1059   1.0000
  13.500   1.3198   0.04263   0.03621  -0.0170   0.0919   1.0000
  13.750   1.3094   0.04629   0.03984  -0.0168   0.0802   1.0000
  14.000   1.2991   0.05014   0.04369  -0.0168   0.0709   1.0000
  14.250   1.2885   0.05425   0.04782  -0.0171   0.0617   1.0000
  14.500   1.2770   0.05863   0.05223  -0.0176   0.0556   1.0000
  14.750   1.2637   0.06347   0.05708  -0.0185   0.0493   1.0000
  15.000   1.2532   0.06809   0.06179  -0.0194   0.0441   1.0000
  15.250   1.2427   0.07287   0.06661  -0.0206   0.0405   1.0000
  15.500   1.2308   0.07789   0.07166  -0.0219   0.0376   1.0000
  15.750   1.2262   0.08206   0.07596  -0.0230   0.0347   1.0000
  16.000   1.2206   0.08645   0.08041  -0.0243   0.0325   1.0000
  16.250   1.2138   0.09076   0.08469  -0.0253   0.0305   1.0000
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