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S9027 (8%) (s9027-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S9027 (8%) (s9027-il)
Reynolds number: 200,000
Max Cl/Cd: 40.72 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9027-il-200000.txt
Download as CSV file: xf-s9027-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9027 (8%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.7551   0.08382   0.08031  -0.0008   1.0000   0.0426
 -10.250  -0.7834   0.07184   0.06836  -0.0098   1.0000   0.0410
 -10.000  -0.8191   0.06240   0.05881  -0.0182   1.0000   0.0396
  -9.750  -0.8533   0.05605   0.05226  -0.0195   1.0000   0.0386
  -9.500  -0.8833   0.04823   0.04395  -0.0197   1.0000   0.0374
  -9.250  -0.8936   0.04224   0.03743  -0.0187   1.0000   0.0371
  -9.000  -0.8895   0.03816   0.03291  -0.0175   1.0000   0.0377
  -8.750  -0.8773   0.03551   0.02993  -0.0164   1.0000   0.0394
  -8.500  -0.8638   0.03278   0.02677  -0.0152   1.0000   0.0411
  -8.250  -0.8479   0.03009   0.02363  -0.0139   1.0000   0.0421
  -8.000  -0.8289   0.02806   0.02120  -0.0128   1.0000   0.0432
  -7.750  -0.8112   0.02497   0.01774  -0.0117   1.0000   0.0450
  -7.500  -0.7895   0.02350   0.01624  -0.0110   1.0000   0.0478
  -7.250  -0.7667   0.02217   0.01471  -0.0102   1.0000   0.0503
  -7.000  -0.7434   0.02085   0.01320  -0.0093   1.0000   0.0531
  -6.750  -0.7199   0.01953   0.01168  -0.0084   1.0000   0.0560
  -6.500  -0.6975   0.01821   0.01041  -0.0076   1.0000   0.0612
  -6.250  -0.6730   0.01760   0.00963  -0.0068   1.0000   0.0676
  -6.000  -0.6507   0.01641   0.00852  -0.0059   1.0000   0.0760
  -5.750  -0.6276   0.01552   0.00761  -0.0050   1.0000   0.0854
  -5.500  -0.6038   0.01486   0.00695  -0.0042   1.0000   0.0972
  -5.250  -0.5801   0.01425   0.00636  -0.0034   1.0000   0.1104
  -5.000  -0.5564   0.01366   0.00583  -0.0027   1.0000   0.1258
  -4.750  -0.5326   0.01313   0.00535  -0.0019   1.0000   0.1452
  -4.500  -0.5091   0.01257   0.00490  -0.0011   1.0000   0.1683
  -4.250  -0.4856   0.01204   0.00449  -0.0003   1.0000   0.1951
  -4.000  -0.4621   0.01155   0.00414   0.0005   1.0000   0.2268
  -3.750  -0.4387   0.01110   0.00382   0.0014   1.0000   0.2639
  -3.500  -0.4155   0.01065   0.00356   0.0022   1.0000   0.3046
  -3.250  -0.3924   0.01023   0.00333   0.0031   1.0000   0.3504
  -3.000  -0.3696   0.00981   0.00315   0.0041   1.0000   0.4034
  -2.750  -0.3471   0.00942   0.00299   0.0052   1.0000   0.4613
  -2.500  -0.3251   0.00903   0.00288   0.0065   1.0000   0.5240
  -2.250  -0.3036   0.00867   0.00281   0.0080   1.0000   0.5902
  -2.000  -0.2824   0.00835   0.00277   0.0096   1.0000   0.6544
  -1.750  -0.2619   0.00807   0.00276   0.0115   1.0000   0.7188
  -1.500  -0.2417   0.00786   0.00279   0.0136   1.0000   0.7823
  -1.250  -0.2204   0.00773   0.00288   0.0157   1.0000   0.8457
  -1.000  -0.1856   0.00777   0.00304   0.0151   1.0000   0.9104
  -0.750  -0.1316   0.00790   0.00316   0.0103   1.0000   0.9555
  -0.500  -0.0765   0.00798   0.00321   0.0050   1.0000   0.9821
  -0.250  -0.0165   0.00798   0.00318  -0.0016   1.0000   0.9980
   0.000   0.0000   0.00794   0.00314   0.0000   1.0000   1.0000
   0.250   0.0164   0.00798   0.00318   0.0016   0.9980   1.0000
   0.500   0.0764   0.00798   0.00321  -0.0050   0.9821   1.0000
   0.750   0.1314   0.00790   0.00316  -0.0103   0.9557   1.0000
   1.000   0.1855   0.00777   0.00304  -0.0151   0.9106   1.0000
   1.250   0.2202   0.00773   0.00288  -0.0156   0.8455   1.0000
   1.500   0.2415   0.00786   0.00279  -0.0136   0.7825   1.0000
   1.750   0.2616   0.00807   0.00276  -0.0114   0.7187   1.0000
   2.000   0.2822   0.00835   0.00277  -0.0095   0.6546   1.0000
   2.250   0.3033   0.00866   0.00281  -0.0079   0.5901   1.0000
   2.500   0.3248   0.00903   0.00288  -0.0064   0.5240   1.0000
   2.750   0.3468   0.00941   0.00299  -0.0052   0.4616   1.0000
   3.000   0.3693   0.00981   0.00315  -0.0041   0.4035   1.0000
   3.250   0.3921   0.01022   0.00333  -0.0031   0.3508   1.0000
   3.500   0.4151   0.01065   0.00355  -0.0022   0.3048   1.0000
   3.750   0.4384   0.01109   0.00382  -0.0013   0.2641   1.0000
   4.000   0.4618   0.01155   0.00414  -0.0005   0.2271   1.0000
   4.250   0.4853   0.01204   0.00448   0.0003   0.1952   1.0000
   4.500   0.5088   0.01257   0.00490   0.0012   0.1684   1.0000
   4.750   0.5324   0.01313   0.00534   0.0020   0.1452   1.0000
   5.000   0.5562   0.01366   0.00583   0.0027   0.1260   1.0000
   5.250   0.5799   0.01425   0.00636   0.0035   0.1105   1.0000
   5.500   0.6037   0.01486   0.00695   0.0042   0.0973   1.0000
   5.750   0.6275   0.01552   0.00761   0.0050   0.0854   1.0000
   6.000   0.6507   0.01641   0.00852   0.0059   0.0759   1.0000
   6.250   0.6730   0.01761   0.00964   0.0068   0.0676   1.0000
   6.500   0.6976   0.01821   0.01040   0.0076   0.0612   1.0000
   6.750   0.7199   0.01958   0.01173   0.0084   0.0559   1.0000
   7.000   0.7435   0.02086   0.01321   0.0093   0.0531   1.0000
   7.250   0.7670   0.02217   0.01472   0.0102   0.0503   1.0000
   7.500   0.7898   0.02348   0.01622   0.0110   0.0477   1.0000
   7.750   0.8115   0.02496   0.01774   0.0117   0.0450   1.0000
   8.000   0.8293   0.02806   0.02119   0.0127   0.0431   1.0000
   8.250   0.8483   0.03012   0.02366   0.0139   0.0421   1.0000
   8.500   0.8642   0.03283   0.02682   0.0151   0.0411   1.0000
   8.750   0.8777   0.03559   0.03001   0.0163   0.0394   1.0000
   9.000   0.8904   0.03811   0.03285   0.0174   0.0376   1.0000
   9.250   0.8943   0.04225   0.03744   0.0185   0.0371   1.0000
   9.500   0.8836   0.04834   0.04407   0.0195   0.0374   1.0000
   9.750   0.8538   0.05617   0.05237   0.0193   0.0386   1.0000
  10.000   0.8196   0.06255   0.05897   0.0179   0.0397   1.0000
  10.250   0.7830   0.07234   0.06887   0.0090   0.0410   1.0000
  10.500   0.7506   0.08737   0.08388  -0.0017   0.0454   1.0000
  10.750   0.7558   0.08892   0.08543  -0.0012   0.0443   1.0000
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