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S9000 (9%) (s9000-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S9000 (9%) (s9000-il)
Reynolds number: 1,000,000
Max Cl/Cd: 108.18 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9000-il-1000000.txt
Download as CSV file: xf-s9000-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9000 (9%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4398   0.08479   0.08319  -0.0271   1.0000   0.0092
  -8.500  -0.4429   0.08096   0.07939  -0.0283   1.0000   0.0094
  -8.250  -0.4485   0.07714   0.07560  -0.0294   1.0000   0.0095
  -8.000  -0.4593   0.07338   0.07188  -0.0300   1.0000   0.0096
  -7.750  -0.4758   0.07013   0.06869  -0.0297   1.0000   0.0095
  -7.500  -0.4854   0.06469   0.06325  -0.0345   1.0000   0.0094
  -7.250  -0.4872   0.05763   0.05613  -0.0405   0.9993   0.0095
  -7.000  -0.4632   0.04708   0.04535  -0.0521   0.9960   0.0099
  -6.750  -0.4349   0.03839   0.03627  -0.0582   0.9934   0.0109
  -6.500  -0.4085   0.03338   0.03084  -0.0618   0.9895   0.0110
  -6.250  -0.3526   0.01080   0.00783  -0.0688   0.9842   0.0120
  -6.000  -0.3259   0.00913   0.00599  -0.0700   0.9809   0.0125
  -5.750  -0.3283   0.01481   0.01046  -0.0685   0.9805   0.0066
  -5.500  -0.2987   0.01202   0.00722  -0.0688   0.9770   0.0056
  -5.250  -0.2652   0.01110   0.00618  -0.0700   0.9747   0.0055
  -5.000  -0.2304   0.01022   0.00519  -0.0715   0.9729   0.0055
  -4.750  -0.1949   0.00951   0.00440  -0.0732   0.9712   0.0055
  -4.500  -0.1670   0.00892   0.00374  -0.0732   0.9647   0.0057
  -4.250  -0.1350   0.00843   0.00319  -0.0739   0.9595   0.0061
  -4.000  -0.1046   0.00805   0.00276  -0.0743   0.9523   0.0070
  -3.750  -0.0730   0.00754   0.00224  -0.0749   0.9446   0.0149
  -3.500  -0.0430   0.00720   0.00197  -0.0753   0.9343   0.0331
  -3.250  -0.0130   0.00693   0.00175  -0.0757   0.9227   0.0530
  -3.000   0.0156   0.00663   0.00155  -0.0759   0.9086   0.0924
  -2.750   0.0428   0.00625   0.00139  -0.0758   0.8920   0.1635
  -2.500   0.0697   0.00598   0.00126  -0.0757   0.8742   0.2269
  -2.250   0.0965   0.00577   0.00115  -0.0755   0.8573   0.2866
  -2.000   0.1233   0.00557   0.00107  -0.0753   0.8409   0.3509
  -1.750   0.1501   0.00537   0.00101  -0.0751   0.8242   0.4179
  -1.500   0.1768   0.00515   0.00096  -0.0749   0.8070   0.4984
  -1.250   0.2033   0.00497   0.00093  -0.0746   0.7894   0.5747
  -1.000   0.2297   0.00482   0.00092  -0.0742   0.7706   0.6520
  -0.750   0.2562   0.00476   0.00094  -0.0738   0.7505   0.7102
  -0.500   0.2829   0.00477   0.00095  -0.0734   0.7315   0.7442
  -0.250   0.3096   0.00480   0.00097  -0.0730   0.7130   0.7730
   0.000   0.3363   0.00483   0.00099  -0.0726   0.6935   0.7955
   0.500   0.3894   0.00497   0.00104  -0.0718   0.6521   0.8323
   0.750   0.4153   0.00506   0.00108  -0.0712   0.6269   0.8508
   1.000   0.4411   0.00516   0.00112  -0.0707   0.6025   0.8683
   1.250   0.4671   0.00525   0.00117  -0.0701   0.5809   0.8840
   1.500   0.4924   0.00533   0.00122  -0.0694   0.5603   0.9015
   1.750   0.5166   0.00542   0.00127  -0.0685   0.5392   0.9199
   2.000   0.5398   0.00551   0.00133  -0.0673   0.5161   0.9413
   2.250   0.5649   0.00559   0.00136  -0.0666   0.4947   0.9670
   2.500   0.5995   0.00574   0.00141  -0.0681   0.4677   0.9991
   2.750   0.6264   0.00596   0.00150  -0.0680   0.4385   1.0000
   3.000   0.6533   0.00617   0.00161  -0.0679   0.4129   1.0000
   3.250   0.6803   0.00637   0.00172  -0.0678   0.3895   1.0000
   3.500   0.7071   0.00659   0.00184  -0.0676   0.3650   1.0000
   3.750   0.7337   0.00682   0.00197  -0.0675   0.3425   1.0000
   4.000   0.7605   0.00703   0.00211  -0.0673   0.3208   1.0000
   4.250   0.7868   0.00731   0.00227  -0.0671   0.2944   1.0000
   4.500   0.8126   0.00762   0.00246  -0.0668   0.2644   1.0000
   4.750   0.8387   0.00790   0.00265  -0.0666   0.2426   1.0000
   5.000   0.8650   0.00816   0.00284  -0.0664   0.2230   1.0000
   5.250   0.8910   0.00845   0.00305  -0.0662   0.2040   1.0000
   5.500   0.9170   0.00874   0.00327  -0.0659   0.1865   1.0000
   5.750   0.9429   0.00903   0.00351  -0.0656   0.1691   1.0000
   6.000   0.9684   0.00936   0.00376  -0.0653   0.1506   1.0000
   6.250   0.9936   0.00972   0.00404  -0.0650   0.1340   1.0000
   6.500   1.0190   0.01005   0.00432  -0.0646   0.1195   1.0000
   6.750   1.0439   0.01043   0.00464  -0.0643   0.1018   1.0000
   7.000   1.0683   0.01086   0.00498  -0.0638   0.0853   1.0000
   7.250   1.0928   0.01127   0.00534  -0.0633   0.0727   1.0000
   7.500   1.1175   0.01165   0.00570  -0.0629   0.0629   1.0000
   7.750   1.1417   0.01207   0.00608  -0.0624   0.0533   1.0000
   8.000   1.1656   0.01252   0.00651  -0.0619   0.0449   1.0000
   8.250   1.1894   0.01296   0.00693  -0.0614   0.0388   1.0000
   8.500   1.2135   0.01337   0.00735  -0.0609   0.0338   1.0000
   8.750   1.2366   0.01386   0.00781  -0.0602   0.0282   1.0000
   9.000   1.2601   0.01428   0.00826  -0.0597   0.0238   1.0000
   9.250   1.2821   0.01487   0.00881  -0.0589   0.0180   1.0000
   9.500   1.3036   0.01549   0.00941  -0.0581   0.0139   1.0000
   9.750   1.3255   0.01605   0.01002  -0.0573   0.0117   1.0000
  10.000   1.3462   0.01671   0.01070  -0.0563   0.0099   1.0000
  10.250   1.3666   0.01737   0.01143  -0.0553   0.0086   1.0000
  10.500   1.3877   0.01792   0.01205  -0.0544   0.0078   1.0000
  10.750   1.4072   0.01859   0.01275  -0.0534   0.0069   1.0000
  11.000   1.4241   0.01949   0.01373  -0.0519   0.0059   1.0000
  11.250   1.4439   0.02004   0.01434  -0.0509   0.0053   1.0000
  11.500   1.4611   0.02078   0.01514  -0.0496   0.0043   1.0000
  11.750   1.4753   0.02174   0.01619  -0.0478   0.0034   1.0000
  12.000   1.4886   0.02267   0.01717  -0.0459   0.0026   1.0000
  12.250   1.4919   0.02403   0.01867  -0.0425   0.0022   1.0000
  12.500   1.5001   0.02498   0.01972  -0.0399   0.0019   1.0000
  12.750   1.5059   0.02611   0.02096  -0.0372   0.0019   1.0000
  13.000   1.5106   0.02735   0.02231  -0.0345   0.0017   1.0000
  13.250   1.5139   0.02875   0.02382  -0.0321   0.0017   1.0000
  13.500   1.5152   0.03037   0.02556  -0.0298   0.0016   1.0000
  13.750   1.5150   0.03225   0.02756  -0.0278   0.0015   1.0000
  14.000   1.5129   0.03442   0.02987  -0.0261   0.0015   1.0000
  14.250   1.5076   0.03711   0.03269  -0.0247   0.0014   1.0000
  14.500   1.5029   0.03998   0.03570  -0.0240   0.0014   1.0000
  14.750   1.4901   0.04407   0.03996  -0.0240   0.0014   1.0000
  15.000   1.4844   0.04768   0.04370  -0.0245   0.0014   1.0000
  15.250   1.4701   0.05280   0.04899  -0.0259   0.0014   1.0000
  15.500   1.4545   0.05857   0.05492  -0.0282   0.0013   1.0000
  15.750   1.4357   0.06539   0.06191  -0.0314   0.0013   1.0000
  16.000   1.4214   0.07181   0.06848  -0.0347   0.0013   1.0000
  16.250   1.4005   0.07989   0.07671  -0.0390   0.0013   1.0000
  16.500   1.3830   0.08760   0.08458  -0.0432   0.0014   1.0000
  16.750   1.3577   0.09724   0.09437  -0.0486   0.0014   1.0000
  17.000   1.3355   0.10649   0.10376  -0.0538   0.0014   1.0000
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