Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S9027 (8%) (s9027-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S9027 (8%) (s9027-il)
Reynolds number: 50,000
Max Cl/Cd: 23.89 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9027-il-50000-n5.txt
Download as CSV file: xf-s9027-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.7206   0.09052   0.08334   0.0021   1.0000   0.0621
  -9.750  -0.7389   0.08118   0.07406  -0.0049   1.0000   0.0612
  -9.500  -0.8108   0.06632   0.05902  -0.0159   1.0000   0.0560
  -9.250  -0.8118   0.06288   0.05549  -0.0161   1.0000   0.0573
  -9.000  -0.8098   0.05971   0.05220  -0.0162   1.0000   0.0592
  -8.750  -0.8109   0.05569   0.04791  -0.0164   1.0000   0.0611
  -8.500  -0.8107   0.05125   0.04306  -0.0163   1.0000   0.0631
  -8.250  -0.8066   0.04680   0.03805  -0.0159   1.0000   0.0650
  -8.000  -0.7975   0.04259   0.03318  -0.0152   1.0000   0.0668
  -7.750  -0.7820   0.03950   0.02971  -0.0144   1.0000   0.0692
  -7.500  -0.7635   0.03761   0.02770  -0.0137   1.0000   0.0737
  -7.250  -0.7451   0.03517   0.02468  -0.0129   1.0000   0.0800
  -7.000  -0.7244   0.03328   0.02276  -0.0122   1.0000   0.0851
  -6.750  -0.7026   0.03132   0.02044  -0.0113   1.0000   0.0921
  -6.500  -0.6812   0.02991   0.01899  -0.0106   1.0000   0.1013
  -6.250  -0.6584   0.02833   0.01719  -0.0097   1.0000   0.1110
  -6.000  -0.6358   0.02707   0.01580  -0.0090   1.0000   0.1237
  -5.750  -0.6127   0.02586   0.01452  -0.0082   1.0000   0.1374
  -5.500  -0.5896   0.02474   0.01338  -0.0074   1.0000   0.1531
  -5.250  -0.5664   0.02372   0.01234  -0.0066   1.0000   0.1726
  -5.000  -0.5427   0.02272   0.01129  -0.0058   1.0000   0.1935
  -4.750  -0.5192   0.02184   0.01045  -0.0051   1.0000   0.2207
  -4.500  -0.4957   0.02099   0.00970  -0.0044   1.0000   0.2509
  -4.250  -0.4721   0.02020   0.00902  -0.0037   1.0000   0.2868
  -4.000  -0.4492   0.01946   0.00844  -0.0029   1.0000   0.3283
  -3.750  -0.4270   0.01878   0.00790  -0.0018   1.0000   0.3742
  -3.500  -0.4051   0.01815   0.00747  -0.0005   1.0000   0.4246
  -3.250  -0.3837   0.01756   0.00711   0.0010   1.0000   0.4808
  -3.000  -0.3628   0.01702   0.00683   0.0027   1.0000   0.5413
  -2.750  -0.3421   0.01655   0.00659   0.0048   1.0000   0.6058
  -2.500  -0.3211   0.01615   0.00644   0.0071   1.0000   0.6715
  -2.250  -0.2982   0.01585   0.00633   0.0092   1.0000   0.7386
  -2.000  -0.2693   0.01565   0.00625   0.0103   1.0000   0.8051
  -1.750  -0.2292   0.01556   0.00613   0.0091   1.0000   0.8693
  -1.500  -0.1768   0.01552   0.00598   0.0050   1.0000   0.9237
  -1.250  -0.1191   0.01542   0.00572  -0.0007   1.0000   0.9677
  -1.000  -0.0630   0.01522   0.00537  -0.0068   1.0000   1.0000
  -0.750  -0.0478   0.01506   0.00516  -0.0051   1.0000   1.0000
  -0.500  -0.0320   0.01495   0.00502  -0.0034   1.0000   1.0000
  -0.250  -0.0160   0.01489   0.00493  -0.0017   1.0000   1.0000
   0.000   0.0000   0.01487   0.00490   0.0000   1.0000   1.0000
   0.250   0.0160   0.01489   0.00493   0.0017   1.0000   1.0000
   0.500   0.0320   0.01495   0.00502   0.0034   1.0000   1.0000
   0.750   0.0478   0.01506   0.00516   0.0051   1.0000   1.0000
   1.000   0.0630   0.01522   0.00537   0.0068   1.0000   1.0000
   1.250   0.1191   0.01542   0.00571   0.0007   0.9677   1.0000
   1.500   0.1768   0.01551   0.00598  -0.0050   0.9236   1.0000
   1.750   0.2291   0.01556   0.00613  -0.0090   0.8694   1.0000
   2.000   0.2692   0.01565   0.00625  -0.0103   0.8053   1.0000
   2.250   0.2981   0.01585   0.00633  -0.0092   0.7386   1.0000
   2.500   0.3209   0.01615   0.00644  -0.0070   0.6716   1.0000
   2.750   0.3420   0.01655   0.00659  -0.0048   0.6059   1.0000
   3.000   0.3627   0.01702   0.00683  -0.0027   0.5414   1.0000
   3.250   0.3836   0.01756   0.00711  -0.0009   0.4809   1.0000
   3.500   0.4050   0.01815   0.00747   0.0006   0.4246   1.0000
   3.750   0.4268   0.01878   0.00790   0.0018   0.3742   1.0000
   4.000   0.4491   0.01946   0.00844   0.0029   0.3283   1.0000
   4.250   0.4721   0.02020   0.00902   0.0038   0.2868   1.0000
   4.500   0.4956   0.02099   0.00970   0.0045   0.2509   1.0000
   4.750   0.5192   0.02184   0.01045   0.0051   0.2207   1.0000
   5.000   0.5427   0.02272   0.01129   0.0058   0.1936   1.0000
   5.250   0.5664   0.02372   0.01234   0.0066   0.1726   1.0000
   5.500   0.5897   0.02474   0.01338   0.0074   0.1531   1.0000
   5.750   0.6128   0.02586   0.01452   0.0082   0.1375   1.0000
   6.000   0.6358   0.02707   0.01580   0.0089   0.1236   1.0000
   6.250   0.6586   0.02834   0.01719   0.0097   0.1109   1.0000
   6.500   0.6813   0.02992   0.01900   0.0105   0.1012   1.0000
   6.750   0.7028   0.03132   0.02045   0.0113   0.0920   1.0000
   7.000   0.7246   0.03329   0.02277   0.0121   0.0851   1.0000
   7.250   0.7453   0.03518   0.02469   0.0128   0.0800   1.0000
   7.500   0.7638   0.03762   0.02771   0.0137   0.0736   1.0000
   7.750   0.7824   0.03951   0.02972   0.0144   0.0692   1.0000
   8.000   0.7979   0.04262   0.03321   0.0151   0.0668   1.0000
   8.250   0.8070   0.04685   0.03811   0.0158   0.0649   1.0000
   8.500   0.8112   0.05132   0.04313   0.0162   0.0630   1.0000
   8.750   0.8115   0.05573   0.04796   0.0162   0.0611   1.0000
   9.000   0.8100   0.05984   0.05234   0.0160   0.0593   1.0000
   9.250   0.8127   0.06291   0.05552   0.0160   0.0573   1.0000
   9.500   0.8093   0.06669   0.05942   0.0155   0.0562   1.0000
   9.750   0.7392   0.08148   0.07436   0.0045   0.0614   1.0000
  10.000   0.7215   0.09072   0.08354  -0.0024   0.0623   1.0000
<< Back to S9027 (8%) (s9027-il)

Polar data table (+)

Polar graphs


<< Back to S9027 (8%) (s9027-il)