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S9000 (9%) (s9000-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S9000 (9%) (s9000-il)
Reynolds number: 100,000
Max Cl/Cd: 53.26 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9000-il-100000.txt
Download as CSV file: xf-s9000-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4213   0.09626   0.09138  -0.0262   1.0000   0.0917
  -8.250  -0.4442   0.09401   0.08928  -0.0313   1.0000   0.0937
  -8.000  -0.4673   0.09069   0.08610  -0.0380   1.0000   0.0941
  -7.750  -0.4232   0.08653   0.08185  -0.0272   1.0000   0.0999
  -7.500  -0.4280   0.08378   0.07919  -0.0273   1.0000   0.1027
  -7.250  -0.4456   0.08026   0.07580  -0.0326   1.0000   0.1066
  -7.000  -0.4649   0.07544   0.07091  -0.0411   1.0000   0.1084
  -6.750  -0.4416   0.07336   0.06901  -0.0319   1.0000   0.1132
  -6.500  -0.4552   0.06924   0.06471  -0.0402   1.0000   0.1216
  -6.250  -0.4445   0.06582   0.06149  -0.0356   1.0000   0.1253
  -6.000  -0.4482   0.06220   0.05761  -0.0403   1.0000   0.1367
  -5.750  -0.4357   0.05968   0.05534  -0.0351   1.0000   0.1415
  -5.500  -0.4314   0.05616   0.05173  -0.0363   1.0000   0.1533
  -5.250  -0.4239   0.05307   0.04852  -0.0369   1.0000   0.1664
  -5.000  -0.3930   0.03873   0.03290  -0.0439   1.0000   0.0740
  -4.750  -0.3659   0.03258   0.02542  -0.0436   1.0000   0.0535
  -4.500  -0.3446   0.02887   0.02137  -0.0432   1.0000   0.0518
  -4.250  -0.3206   0.02607   0.01809  -0.0426   1.0000   0.0513
  -4.000  -0.2957   0.02387   0.01544  -0.0417   1.0000   0.0522
  -3.750  -0.2716   0.02194   0.01330  -0.0412   1.0000   0.0584
  -3.500  -0.2467   0.02063   0.01177  -0.0403   1.0000   0.0657
  -3.250  -0.2222   0.01934   0.01041  -0.0396   1.0000   0.0805
  -3.000  -0.1980   0.01790   0.00916  -0.0391   1.0000   0.1069
  -2.750  -0.1738   0.01658   0.00822  -0.0387   1.0000   0.1591
  -2.500  -0.1494   0.01474   0.00764  -0.0389   1.0000   0.3741
  -2.250  -0.1332   0.01384   0.00778  -0.0366   1.0000   0.6085
  -2.000  -0.1252   0.01368   0.00810  -0.0317   1.0000   0.7732
  -1.750  -0.1195   0.01362   0.00822  -0.0262   1.0000   0.8930
  -1.500  -0.0881   0.01351   0.00792  -0.0278   1.0000   1.0000
  -1.250  -0.0497   0.01393   0.00800  -0.0310   0.9949   1.0000
  -1.000   0.0014   0.01440   0.00816  -0.0363   0.9846   1.0000
  -0.750   0.0501   0.01475   0.00827  -0.0410   0.9733   1.0000
  -0.500   0.0970   0.01502   0.00833  -0.0452   0.9616   1.0000
  -0.250   0.1431   0.01522   0.00837  -0.0491   0.9496   1.0000
   0.000   0.1892   0.01534   0.00836  -0.0529   0.9377   1.0000
   0.250   0.2368   0.01537   0.00829  -0.0568   0.9260   1.0000
   0.500   0.2886   0.01527   0.00812  -0.0612   0.9156   1.0000
   0.750   0.3341   0.01511   0.00791  -0.0643   0.9028   1.0000
   1.000   0.3782   0.01491   0.00769  -0.0670   0.8898   1.0000
   1.250   0.4204   0.01468   0.00745  -0.0691   0.8762   1.0000
   1.500   0.4609   0.01442   0.00718  -0.0708   0.8615   1.0000
   1.750   0.4992   0.01416   0.00691  -0.0719   0.8456   1.0000
   2.000   0.5319   0.01400   0.00674  -0.0719   0.8267   1.0000
   2.250   0.5624   0.01390   0.00664  -0.0716   0.8062   1.0000
   2.500   0.5933   0.01381   0.00650  -0.0713   0.7862   1.0000
   2.750   0.6197   0.01385   0.00651  -0.0703   0.7623   1.0000
   3.000   0.6463   0.01390   0.00650  -0.0693   0.7378   1.0000
   3.250   0.6728   0.01397   0.00654  -0.0683   0.7125   1.0000
   3.500   0.6986   0.01409   0.00658  -0.0672   0.6862   1.0000
   3.750   0.7235   0.01427   0.00669  -0.0661   0.6584   1.0000
   4.000   0.7481   0.01449   0.00687  -0.0649   0.6299   1.0000
   4.250   0.7724   0.01476   0.00705  -0.0638   0.6007   1.0000
   4.500   0.7960   0.01508   0.00730  -0.0626   0.5698   1.0000
   4.750   0.8192   0.01543   0.00758  -0.0614   0.5378   1.0000
   5.000   0.8421   0.01581   0.00790  -0.0602   0.5053   1.0000
   5.250   0.8648   0.01626   0.00823  -0.0590   0.4732   1.0000
   5.500   0.8870   0.01675   0.00864  -0.0578   0.4405   1.0000
   5.750   0.9089   0.01729   0.00911  -0.0566   0.4077   1.0000
   6.000   0.9306   0.01790   0.00964  -0.0554   0.3760   1.0000
   6.250   0.9519   0.01857   0.01020  -0.0542   0.3450   1.0000
   6.500   0.9728   0.01930   0.01082  -0.0530   0.3147   1.0000
   6.750   0.9930   0.02005   0.01152  -0.0518   0.2842   1.0000
   7.000   1.0130   0.02089   0.01229  -0.0506   0.2555   1.0000
   7.250   1.0327   0.02183   0.01317  -0.0494   0.2288   1.0000
   7.500   1.0520   0.02283   0.01410  -0.0482   0.2035   1.0000
   7.750   1.0715   0.02397   0.01526  -0.0469   0.1805   1.0000
   8.000   1.0916   0.02531   0.01647  -0.0459   0.1615   1.0000
   8.250   1.1106   0.02663   0.01788  -0.0446   0.1433   1.0000
   8.500   1.1303   0.02811   0.01942  -0.0435   0.1280   1.0000
   8.750   1.1492   0.02962   0.02103  -0.0423   0.1146   1.0000
   9.000   1.1680   0.03127   0.02274  -0.0412   0.1028   1.0000
   9.250   1.1859   0.03299   0.02450  -0.0400   0.0919   1.0000
   9.500   1.2042   0.03495   0.02645  -0.0390   0.0819   1.0000
   9.750   1.2169   0.03684   0.02876  -0.0370   0.0736   1.0000
  10.000   1.2325   0.03972   0.03177  -0.0358   0.0669   1.0000
  10.250   1.2425   0.04170   0.03408  -0.0337   0.0607   1.0000
  10.500   1.2555   0.04552   0.03798  -0.0327   0.0564   1.0000
  10.750   1.2552   0.04871   0.04182  -0.0296   0.0544   1.0000
  11.000   1.2520   0.05195   0.04551  -0.0268   0.0520   1.0000
  11.250   1.2547   0.05422   0.04794  -0.0248   0.0488   1.0000
  11.500   1.2570   0.05779   0.05153  -0.0235   0.0463   1.0000
  11.750   1.2421   0.06244   0.05648  -0.0209   0.0458   1.0000
  12.000   1.2230   0.06630   0.06061  -0.0185   0.0457   1.0000
  12.250   1.2025   0.07039   0.06497  -0.0171   0.0456   1.0000
  12.500   1.1816   0.07516   0.06997  -0.0171   0.0457   1.0000
  12.750   1.1602   0.07992   0.07499  -0.0182   0.0459   1.0000
  13.000   1.1345   0.08542   0.08075  -0.0211   0.0464   1.0000
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