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S9037 (9%) (s9037-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S9037 (9%) (s9037-il)
Reynolds number: 100,000
Max Cl/Cd: 56.84 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9037-il-100000.txt
Download as CSV file: xf-s9037-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9037 (9%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3465   0.10393   0.09910  -0.0327   1.0000   0.0757
  -8.500  -0.3590   0.10273   0.09803  -0.0361   1.0000   0.0764
  -8.250  -0.3729   0.10132   0.09676  -0.0378   1.0000   0.0767
  -8.000  -0.3393   0.09401   0.08937  -0.0330   1.0000   0.0796
  -7.750  -0.3352   0.09136   0.08678  -0.0321   1.0000   0.0819
  -7.500  -0.3379   0.08908   0.08459  -0.0315   1.0000   0.0845
  -7.250  -0.3478   0.08730   0.08292  -0.0305   1.0000   0.0866
  -7.000  -0.3638   0.08585   0.08161  -0.0297   1.0000   0.0882
  -6.750  -0.3834   0.08439   0.08025  -0.0329   1.0000   0.0897
  -6.500  -0.3993   0.08249   0.07829  -0.0383   1.0000   0.0905
  -6.250  -0.3955   0.07835   0.07432  -0.0320   1.0000   0.0919
  -6.000  -0.3936   0.07612   0.07216  -0.0274   1.0000   0.0941
  -5.750  -0.3948   0.07389   0.06997  -0.0261   1.0000   0.0968
  -5.500  -0.3953   0.07105   0.06679  -0.0372   1.0000   0.1044
  -5.250  -0.3930   0.06699   0.06293  -0.0334   1.0000   0.1058
  -5.000  -0.3896   0.06464   0.06065  -0.0298   1.0000   0.1082
  -4.750  -0.3827   0.06213   0.05812  -0.0297   1.0000   0.1134
  -4.500  -0.3712   0.05823   0.05408  -0.0331   1.0000   0.1212
  -4.250  -0.3616   0.05597   0.05182  -0.0320   1.0000   0.1264
  -4.000  -0.3346   0.05210   0.04780  -0.0363   0.9969   0.1380
  -3.750  -0.2912   0.04814   0.04349  -0.0440   0.9900   0.1627
  -3.500  -0.2238   0.03502   0.02862  -0.0521   0.9875   0.0618
  -3.250  -0.1808   0.03122   0.02431  -0.0557   0.9828   0.0599
  -3.000  -0.1412   0.02823   0.02075  -0.0580   0.9762   0.0580
  -2.750  -0.0957   0.02558   0.01745  -0.0607   0.9712   0.0565
  -2.500  -0.0572   0.02382   0.01530  -0.0622   0.9637   0.0588
  -2.250  -0.0133   0.02232   0.01365  -0.0649   0.9577   0.0713
  -2.000   0.0224   0.02103   0.01242  -0.0662   0.9492   0.0964
  -1.750   0.0651   0.01933   0.01133  -0.0689   0.9433   0.2060
  -1.500   0.0896   0.01721   0.01124  -0.0681   0.9351   0.6574
  -1.250   0.1492   0.01664   0.01084  -0.0729   0.9299   1.0000
  -1.000   0.1864   0.01679   0.01064  -0.0748   0.9192   1.0000
  -0.750   0.2299   0.01689   0.01043  -0.0777   0.9105   1.0000
  -0.500   0.2746   0.01690   0.01021  -0.0808   0.9017   1.0000
  -0.250   0.3115   0.01695   0.01006  -0.0825   0.8909   1.0000
   0.000   0.3534   0.01690   0.00985  -0.0848   0.8822   1.0000
   0.250   0.3932   0.01679   0.00961  -0.0866   0.8729   1.0000
   0.500   0.4249   0.01678   0.00949  -0.0869   0.8611   1.0000
   0.750   0.4575   0.01673   0.00935  -0.0873   0.8499   1.0000
   1.000   0.4924   0.01657   0.00910  -0.0879   0.8398   1.0000
   1.250   0.5262   0.01636   0.00882  -0.0882   0.8294   1.0000
   1.500   0.5543   0.01628   0.00869  -0.0876   0.8163   1.0000
   1.750   0.5823   0.01619   0.00855  -0.0869   0.8030   1.0000
   2.000   0.6100   0.01610   0.00842  -0.0861   0.7896   1.0000
   2.250   0.6375   0.01602   0.00831  -0.0853   0.7758   1.0000
   2.500   0.6648   0.01595   0.00820  -0.0845   0.7616   1.0000
   2.750   0.6919   0.01588   0.00809  -0.0836   0.7469   1.0000
   3.000   0.7190   0.01582   0.00799  -0.0827   0.7317   1.0000
   3.250   0.7461   0.01576   0.00791  -0.0818   0.7158   1.0000
   3.500   0.7709   0.01583   0.00796  -0.0806   0.6973   1.0000
   3.750   0.7964   0.01589   0.00799  -0.0796   0.6788   1.0000
   4.000   0.8226   0.01594   0.00799  -0.0787   0.6607   1.0000
   4.250   0.8479   0.01608   0.00813  -0.0777   0.6415   1.0000
   4.500   0.8725   0.01624   0.00827  -0.0767   0.6208   1.0000
   4.750   0.8980   0.01640   0.00836  -0.0757   0.6007   1.0000
   5.000   0.9217   0.01663   0.00858  -0.0746   0.5780   1.0000
   5.250   0.9459   0.01687   0.00881  -0.0736   0.5559   1.0000
   5.500   0.9697   0.01716   0.00906  -0.0725   0.5332   1.0000
   5.750   0.9928   0.01751   0.00940  -0.0714   0.5097   1.0000
   6.000   1.0163   0.01788   0.00971  -0.0703   0.4868   1.0000
   6.250   1.0385   0.01830   0.01015  -0.0692   0.4622   1.0000
   6.500   1.0602   0.01877   0.01061  -0.0680   0.4371   1.0000
   6.750   1.0815   0.01928   0.01108  -0.0667   0.4118   1.0000
   7.000   1.1023   0.01984   0.01157  -0.0654   0.3866   1.0000
   7.250   1.1224   0.02045   0.01216  -0.0641   0.3611   1.0000
   7.500   1.1416   0.02112   0.01284  -0.0627   0.3353   1.0000
   7.750   1.1603   0.02186   0.01357  -0.0613   0.3103   1.0000
   8.000   1.1786   0.02267   0.01434  -0.0598   0.2860   1.0000
   8.250   1.1961   0.02355   0.01514  -0.0583   0.2626   1.0000
   8.500   1.2124   0.02449   0.01612  -0.0566   0.2391   1.0000
   8.750   1.2278   0.02551   0.01712  -0.0550   0.2171   1.0000
   9.000   1.2424   0.02657   0.01819  -0.0532   0.1961   1.0000
   9.250   1.2569   0.02782   0.01936  -0.0515   0.1772   1.0000
   9.500   1.2701   0.02912   0.02075  -0.0496   0.1590   1.0000
   9.750   1.2826   0.03048   0.02211  -0.0477   0.1428   1.0000
  10.000   1.2958   0.03203   0.02368  -0.0459   0.1285   1.0000
  10.250   1.3080   0.03368   0.02538  -0.0441   0.1155   1.0000
  10.500   1.3188   0.03543   0.02727  -0.0421   0.1039   1.0000
  10.750   1.3304   0.03744   0.02938  -0.0404   0.0938   1.0000
  11.000   1.3401   0.03937   0.03129  -0.0385   0.0844   1.0000
  11.250   1.3429   0.04098   0.03307  -0.0357   0.0769   1.0000
  11.500   1.3451   0.04326   0.03555  -0.0332   0.0697   1.0000
  11.750   1.3514   0.04571   0.03790  -0.0316   0.0618   1.0000
  12.000   1.3411   0.04770   0.04031  -0.0283   0.0573   1.0000
  12.250   1.3453   0.05066   0.04312  -0.0270   0.0506   1.0000
  12.500   1.3344   0.05337   0.04627  -0.0246   0.0480   1.0000
  12.750   1.3268   0.05652   0.04971  -0.0230   0.0449   1.0000
  13.000   1.3258   0.05939   0.05255  -0.0222   0.0413   1.0000
  13.250   1.2003   0.06213   0.05637  -0.0163   0.0474   1.0000
  13.500   1.1803   0.06781   0.06234  -0.0165   0.0465   1.0000
  13.750   1.1582   0.07389   0.06869  -0.0174   0.0460   1.0000
  14.000   1.1325   0.08049   0.07556  -0.0192   0.0461   1.0000
  14.250   1.1038   0.08756   0.08290  -0.0217   0.0470   1.0000
  14.500   1.0731   0.09491   0.09048  -0.0250   0.0481   1.0000
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