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S2027 (s2027-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S2027 (s2027-il)
Reynolds number: 100,000
Max Cl/Cd: 50.82 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2027-il-100000-n5.txt
Download as CSV file: xf-s2027-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4427   0.09270   0.08772  -0.0443   1.0000   0.0273
 -11.250  -0.4578   0.08429   0.07933  -0.0493   1.0000   0.0270
 -11.000  -0.4791   0.07539   0.07041  -0.0555   1.0000   0.0266
 -10.750  -0.5026   0.06761   0.06256  -0.0616   1.0000   0.0262
 -10.500  -0.5277   0.06123   0.05607  -0.0664   1.0000   0.0260
 -10.250  -0.5499   0.05659   0.05130  -0.0689   1.0000   0.0258
 -10.000  -0.5715   0.05328   0.04788  -0.0689   1.0000   0.0257
  -9.750  -0.5955   0.05134   0.04588  -0.0656   1.0000   0.0256
  -9.500  -0.6198   0.04985   0.04431  -0.0610   1.0000   0.0256
  -9.250  -0.6107   0.04543   0.03936  -0.0644   0.9844   0.0263
  -9.000  -0.5948   0.04169   0.03506  -0.0669   0.9730   0.0270
  -8.750  -0.5753   0.03866   0.03148  -0.0686   0.9624   0.0276
  -8.500  -0.5508   0.03572   0.02825  -0.0702   0.9544   0.0281
  -8.250  -0.5260   0.03345   0.02572  -0.0712   0.9451   0.0285
  -8.000  -0.5005   0.03153   0.02359  -0.0718   0.9360   0.0291
  -7.750  -0.4726   0.02981   0.02168  -0.0726   0.9281   0.0297
  -7.500  -0.4489   0.02839   0.02009  -0.0724   0.9178   0.0305
  -7.250  -0.4234   0.02707   0.01862  -0.0724   0.9090   0.0314
  -7.000  -0.3992   0.02590   0.01731  -0.0720   0.8998   0.0324
  -6.750  -0.3767   0.02497   0.01620  -0.0712   0.8897   0.0343
  -6.500  -0.3541   0.02396   0.01511  -0.0706   0.8812   0.0364
  -6.250  -0.3333   0.02313   0.01425  -0.0697   0.8711   0.0386
  -6.000  -0.3118   0.02234   0.01336  -0.0688   0.8616   0.0412
  -5.750  -0.2892   0.02158   0.01242  -0.0678   0.8533   0.0441
  -5.500  -0.2688   0.02078   0.01159  -0.0668   0.8432   0.0485
  -5.250  -0.2463   0.02004   0.01077  -0.0659   0.8351   0.0571
  -5.000  -0.2255   0.01915   0.01004  -0.0649   0.8257   0.0838
  -4.750  -0.2049   0.01823   0.00943  -0.0641   0.8169   0.1440
  -4.500  -0.1834   0.01743   0.00892  -0.0634   0.8087   0.2200
  -4.250  -0.1641   0.01661   0.00866  -0.0624   0.7994   0.3332
  -4.000  -0.1421   0.01613   0.00852  -0.0612   0.7922   0.4239
  -3.750  -0.1190   0.01597   0.00848  -0.0602   0.7825   0.4795
  -3.500  -0.0938   0.01586   0.00834  -0.0592   0.7752   0.5184
  -3.250  -0.0688   0.01582   0.00825  -0.0584   0.7661   0.5493
  -3.000  -0.0431   0.01578   0.00813  -0.0576   0.7581   0.5765
  -2.750  -0.0175   0.01575   0.00803  -0.0568   0.7497   0.6006
  -2.500   0.0082   0.01573   0.00793  -0.0561   0.7414   0.6222
  -2.250   0.0342   0.01570   0.00781  -0.0553   0.7335   0.6412
  -2.000   0.0598   0.01569   0.00774  -0.0547   0.7248   0.6588
  -1.750   0.0863   0.01564   0.00759  -0.0540   0.7174   0.6755
  -1.500   0.1118   0.01565   0.00754  -0.0534   0.7083   0.6911
  -1.250   0.1385   0.01559   0.00739  -0.0527   0.7014   0.7060
  -1.000   0.1639   0.01561   0.00736  -0.0521   0.6920   0.7202
  -0.750   0.1904   0.01558   0.00725  -0.0515   0.6846   0.7341
  -0.500   0.2162   0.01558   0.00722  -0.0510   0.6757   0.7480
  -0.250   0.2425   0.01557   0.00715  -0.0505   0.6679   0.7618
   0.000   0.2684   0.01557   0.00710  -0.0499   0.6596   0.7757
   0.250   0.2942   0.01559   0.00708  -0.0493   0.6514   0.7898
   0.500   0.3202   0.01559   0.00702  -0.0487   0.6435   0.8041
   0.750   0.3456   0.01562   0.00705  -0.0480   0.6350   0.8185
   1.000   0.3718   0.01561   0.00699  -0.0474   0.6275   0.8334
   1.250   0.3971   0.01566   0.00705  -0.0468   0.6186   0.8492
   1.500   0.4242   0.01566   0.00699  -0.0463   0.6116   0.8656
   1.750   0.4509   0.01572   0.00709  -0.0461   0.6022   0.8827
   2.000   0.4810   0.01575   0.00708  -0.0463   0.5946   0.9006
   2.250   0.5131   0.01581   0.00715  -0.0472   0.5854   0.9197
   2.500   0.5483   0.01589   0.00721  -0.0487   0.5769   0.9394
   2.750   0.5870   0.01595   0.00723  -0.0510   0.5682   0.9584
   3.000   0.6265   0.01607   0.00736  -0.0537   0.5586   0.9793
   3.250   0.6645   0.01617   0.00739  -0.0561   0.5503   1.0000
   3.500   0.6843   0.01637   0.00756  -0.0550   0.5414   1.0000
   3.750   0.7071   0.01655   0.00769  -0.0544   0.5336   1.0000
   4.000   0.7304   0.01676   0.00788  -0.0538   0.5249   1.0000
   4.250   0.7543   0.01699   0.00809  -0.0533   0.5166   1.0000
   4.500   0.7789   0.01720   0.00826  -0.0529   0.5084   1.0000
   5.000   0.8281   0.01768   0.00872  -0.0521   0.4918   1.0000
   5.250   0.8515   0.01798   0.00908  -0.0516   0.4822   1.0000
   5.500   0.8761   0.01825   0.00933  -0.0512   0.4741   1.0000
   5.750   0.9001   0.01854   0.00967  -0.0507   0.4652   1.0000
   6.000   0.9239   0.01885   0.01002  -0.0502   0.4563   1.0000
   6.250   0.9484   0.01914   0.01030  -0.0498   0.4482   1.0000
   6.500   0.9711   0.01950   0.01074  -0.0492   0.4387   1.0000
   6.750   0.9951   0.01982   0.01108  -0.0487   0.4305   1.0000
   7.000   1.0176   0.02019   0.01152  -0.0481   0.4211   1.0000
   7.250   1.0401   0.02057   0.01196  -0.0474   0.4122   1.0000
   7.500   1.0631   0.02092   0.01233  -0.0468   0.4037   1.0000
   7.750   1.0840   0.02137   0.01290  -0.0460   0.3939   1.0000
   8.000   1.1059   0.02177   0.01335  -0.0453   0.3852   1.0000
   8.250   1.1265   0.02222   0.01387  -0.0444   0.3758   1.0000
   8.500   1.1462   0.02271   0.01445  -0.0434   0.3662   1.0000
   8.750   1.1666   0.02316   0.01493  -0.0425   0.3574   1.0000
   9.000   1.1842   0.02370   0.01561  -0.0413   0.3473   1.0000
   9.250   1.2015   0.02425   0.01625  -0.0400   0.3374   1.0000
   9.500   1.2178   0.02479   0.01683  -0.0386   0.3272   1.0000
   9.750   1.2313   0.02539   0.01751  -0.0368   0.3160   1.0000
  10.000   1.2417   0.02606   0.01828  -0.0347   0.3045   1.0000
  10.250   1.2502   0.02678   0.01909  -0.0324   0.2933   1.0000
  10.500   1.2577   0.02759   0.01995  -0.0301   0.2822   1.0000
  10.750   1.2640   0.02852   0.02090  -0.0279   0.2708   1.0000
  11.000   1.2686   0.02963   0.02211  -0.0259   0.2586   1.0000
  11.250   1.2724   0.03089   0.02345  -0.0240   0.2463   1.0000
  11.500   1.2754   0.03230   0.02493  -0.0222   0.2342   1.0000
  11.750   1.2773   0.03388   0.02658  -0.0207   0.2222   1.0000
  12.000   1.2779   0.03569   0.02844  -0.0193   0.2100   1.0000
  12.250   1.2769   0.03773   0.03053  -0.0181   0.1977   1.0000
  12.500   1.2744   0.04004   0.03291  -0.0171   0.1851   1.0000
  12.750   1.2703   0.04266   0.03556  -0.0164   0.1724   1.0000
  13.000   1.2645   0.04559   0.03853  -0.0159   0.1591   1.0000
  13.250   1.2569   0.04888   0.04184  -0.0157   0.1460   1.0000
  13.500   1.2479   0.05250   0.04547  -0.0158   0.1332   1.0000
  13.750   1.2380   0.05643   0.04942  -0.0162   0.1211   1.0000
  14.000   1.2279   0.06060   0.05361  -0.0168   0.1100   1.0000
  14.250   1.2165   0.06514   0.05817  -0.0178   0.0996   1.0000
  14.500   1.2049   0.06988   0.06293  -0.0190   0.0915   1.0000
  14.750   1.1933   0.07488   0.06795  -0.0204   0.0829   1.0000
  15.000   1.1833   0.07978   0.07291  -0.0219   0.0759   1.0000
  15.250   1.1718   0.08504   0.07820  -0.0237   0.0703   1.0000
  15.500   1.1634   0.08999   0.08324  -0.0255   0.0644   1.0000
  15.750   1.1531   0.09535   0.08864  -0.0275   0.0597   1.0000
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