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S9000 (9%) (s9000-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S9000 (9%) (s9000-il)
Reynolds number: 50,000
Max Cl/Cd: 37.89 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9000-il-50000-n5.txt
Download as CSV file: xf-s9000-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4406   0.10205   0.09489  -0.0293   1.0000   0.0415
  -9.000  -0.4353   0.09854   0.09143  -0.0290   1.0000   0.0407
  -8.750  -0.4334   0.09490   0.08786  -0.0297   1.0000   0.0400
  -8.500  -0.4330   0.09125   0.08428  -0.0307   1.0000   0.0393
  -8.250  -0.4348   0.08748   0.08060  -0.0319   1.0000   0.0387
  -8.000  -0.4393   0.08359   0.07682  -0.0332   1.0000   0.0382
  -7.750  -0.4451   0.07971   0.07304  -0.0348   1.0000   0.0376
  -7.500  -0.4486   0.07512   0.06853  -0.0377   1.0000   0.0369
  -7.250  -0.4522   0.07029   0.06373  -0.0403   1.0000   0.0363
  -7.000  -0.4547   0.06552   0.05893  -0.0424   1.0000   0.0357
  -6.750  -0.4557   0.06073   0.05405  -0.0441   1.0000   0.0351
  -6.500  -0.4540   0.05604   0.04918  -0.0453   1.0000   0.0349
  -6.250  -0.4484   0.05172   0.04460  -0.0460   1.0000   0.0350
  -6.000  -0.4392   0.04776   0.04034  -0.0464   1.0000   0.0358
  -5.750  -0.4269   0.04399   0.03618  -0.0466   1.0000   0.0371
  -5.500  -0.4115   0.04035   0.03199  -0.0465   1.0000   0.0386
  -5.250  -0.3932   0.03701   0.02809  -0.0462   1.0000   0.0399
  -5.000  -0.3725   0.03393   0.02440  -0.0456   1.0000   0.0411
  -4.750  -0.3515   0.03128   0.02141  -0.0449   1.0000   0.0429
  -4.500  -0.3309   0.02956   0.01954  -0.0442   1.0000   0.0478
  -4.250  -0.3077   0.02772   0.01725  -0.0431   1.0000   0.0531
  -4.000  -0.2861   0.02606   0.01554  -0.0421   1.0000   0.0595
  -3.750  -0.2638   0.02466   0.01393  -0.0409   1.0000   0.0697
  -3.500  -0.2418   0.02346   0.01268  -0.0399   1.0000   0.0848
  -3.250  -0.2192   0.02236   0.01148  -0.0390   1.0000   0.1078
  -3.000  -0.1959   0.02117   0.01051  -0.0387   1.0000   0.1513
  -2.750  -0.1723   0.01992   0.00981  -0.0387   1.0000   0.2479
  -2.500  -0.1506   0.01884   0.00948  -0.0383   1.0000   0.4050
  -2.250  -0.1353   0.01808   0.00947  -0.0355   1.0000   0.5749
  -2.000  -0.1266   0.01777   0.00962  -0.0306   1.0000   0.7289
  -1.750  -0.1157   0.01759   0.00958  -0.0262   1.0000   0.8558
  -1.500  -0.0689   0.01744   0.00915  -0.0301   0.9943   1.0000
  -1.250  -0.0252   0.01774   0.00899  -0.0340   0.9838   1.0000
  -1.000   0.0165   0.01799   0.00889  -0.0374   0.9723   1.0000
  -0.750   0.0568   0.01822   0.00882  -0.0405   0.9602   1.0000
  -0.500   0.0966   0.01842   0.00875  -0.0433   0.9477   1.0000
  -0.250   0.1361   0.01859   0.00871  -0.0460   0.9348   1.0000
   0.000   0.1754   0.01874   0.00869  -0.0485   0.9217   1.0000
   0.250   0.2147   0.01886   0.00866  -0.0509   0.9084   1.0000
   0.500   0.2541   0.01895   0.00864  -0.0531   0.8951   1.0000
   0.750   0.2938   0.01901   0.00861  -0.0554   0.8818   1.0000
   1.000   0.3316   0.01905   0.00859  -0.0571   0.8676   1.0000
   1.250   0.3677   0.01907   0.00857  -0.0584   0.8523   1.0000
   1.500   0.4030   0.01908   0.00856  -0.0594   0.8362   1.0000
   1.750   0.4377   0.01907   0.00853  -0.0603   0.8195   1.0000
   2.000   0.4719   0.01905   0.00850  -0.0609   0.8025   1.0000
   2.250   0.5024   0.01910   0.00855  -0.0609   0.7831   1.0000
   2.500   0.5326   0.01915   0.00862  -0.0608   0.7630   1.0000
   2.750   0.5638   0.01917   0.00864  -0.0607   0.7429   1.0000
   3.000   0.5914   0.01928   0.00876  -0.0601   0.7198   1.0000
   3.250   0.6196   0.01939   0.00886  -0.0596   0.6968   1.0000
   3.500   0.6476   0.01952   0.00903  -0.0589   0.6732   1.0000
   3.750   0.6735   0.01973   0.00925  -0.0581   0.6476   1.0000
   4.000   0.6994   0.01996   0.00948  -0.0572   0.6215   1.0000
   4.250   0.7248   0.02022   0.00977  -0.0562   0.5945   1.0000
   4.500   0.7496   0.02053   0.01007  -0.0552   0.5666   1.0000
   4.750   0.7737   0.02089   0.01041  -0.0542   0.5379   1.0000
   5.000   0.7974   0.02130   0.01082  -0.0531   0.5091   1.0000
   5.250   0.8207   0.02176   0.01131  -0.0520   0.4803   1.0000
   5.500   0.8434   0.02228   0.01182  -0.0509   0.4512   1.0000
   5.750   0.8657   0.02285   0.01240  -0.0498   0.4221   1.0000
   6.000   0.8872   0.02347   0.01301  -0.0487   0.3928   1.0000
   6.250   0.9083   0.02416   0.01373  -0.0475   0.3637   1.0000
   6.500   0.9287   0.02490   0.01448  -0.0463   0.3352   1.0000
   6.750   0.9488   0.02572   0.01531  -0.0451   0.3080   1.0000
   7.000   0.9684   0.02661   0.01620  -0.0439   0.2821   1.0000
   7.250   0.9873   0.02757   0.01715  -0.0427   0.2576   1.0000
   7.500   1.0058   0.02861   0.01831  -0.0415   0.2334   1.0000
   7.750   1.0235   0.02973   0.01947  -0.0403   0.2106   1.0000
   8.000   1.0404   0.03093   0.02069  -0.0390   0.1901   1.0000
   8.250   1.0570   0.03222   0.02206  -0.0377   0.1709   1.0000
   8.500   1.0734   0.03363   0.02357  -0.0364   0.1540   1.0000
   8.750   1.0884   0.03510   0.02513  -0.0350   0.1385   1.0000
   9.000   1.1043   0.03677   0.02697  -0.0337   0.1257   1.0000
   9.250   1.1197   0.03858   0.02893  -0.0324   0.1146   1.0000
   9.500   1.1322   0.04034   0.03079  -0.0310   0.1040   1.0000
   9.750   1.1450   0.04224   0.03280  -0.0296   0.0952   1.0000
  10.000   1.1555   0.04448   0.03537  -0.0280   0.0867   1.0000
  10.250   1.1638   0.04655   0.03749  -0.0265   0.0797   1.0000
  10.500   1.1695   0.04914   0.04046  -0.0247   0.0736   1.0000
  10.750   1.1745   0.05125   0.04252  -0.0230   0.0684   1.0000
  11.000   1.1704   0.05439   0.04616  -0.0209   0.0642   1.0000
  11.250   1.1681   0.05747   0.04951  -0.0193   0.0609   1.0000
  11.500   1.1687   0.06011   0.05218  -0.0182   0.0578   1.0000
  11.750   1.1597   0.06398   0.05631  -0.0174   0.0559   1.0000
  12.000   1.1433   0.06866   0.06137  -0.0175   0.0547   1.0000
  12.250   1.1252   0.07398   0.06700  -0.0187   0.0539   1.0000
  12.500   1.1046   0.08017   0.07344  -0.0211   0.0537   1.0000
  12.750   1.0817   0.08739   0.08088  -0.0248   0.0539   1.0000
  13.000   1.0571   0.09578   0.08944  -0.0298   0.0547   1.0000
  13.250   1.0323   0.10519   0.09897  -0.0356   0.0556   1.0000
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