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S2050 8.93% (s2050-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S2050 8.93% (s2050-il)
Reynolds number: 50,000
Max Cl/Cd: 34.6 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2050-il-50000-n5.txt
Download as CSV file: xf-s2050-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2050 8.93%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5379   0.09441   0.08718  -0.0227   1.0000   0.0449
  -9.250  -0.5430   0.08909   0.08195  -0.0255   1.0000   0.0444
  -8.750  -0.5945   0.07064   0.06355  -0.0398   1.0000   0.0400
  -8.500  -0.6051   0.06594   0.05877  -0.0415   1.0000   0.0399
  -8.250  -0.6139   0.06122   0.05387  -0.0426   1.0000   0.0399
  -8.000  -0.6185   0.05661   0.04904  -0.0432   1.0000   0.0401
  -7.750  -0.6148   0.05311   0.04541  -0.0430   1.0000   0.0411
  -7.500  -0.6091   0.04950   0.04156  -0.0428   1.0000   0.0420
  -7.250  -0.6006   0.04581   0.03755  -0.0425   1.0000   0.0431
  -7.000  -0.5891   0.04220   0.03355  -0.0420   1.0000   0.0444
  -6.750  -0.5746   0.03875   0.02962  -0.0414   1.0000   0.0467
  -6.500  -0.5569   0.03541   0.02555  -0.0408   1.0000   0.0510
  -6.250  -0.5382   0.03353   0.02362  -0.0401   1.0000   0.0561
  -6.000  -0.5169   0.03109   0.02066  -0.0392   1.0000   0.0635
  -5.750  -0.4962   0.02947   0.01895  -0.0384   1.0000   0.0734
  -5.500  -0.4747   0.02791   0.01726  -0.0375   1.0000   0.0859
  -5.250  -0.4526   0.02646   0.01566  -0.0365   1.0000   0.1002
  -5.000  -0.4302   0.02516   0.01422  -0.0355   1.0000   0.1159
  -4.750  -0.4083   0.02402   0.01304  -0.0345   1.0000   0.1336
  -4.500  -0.3863   0.02298   0.01201  -0.0335   1.0000   0.1534
  -4.250  -0.3640   0.02201   0.01102  -0.0326   1.0000   0.1772
  -4.000  -0.3418   0.02106   0.01017  -0.0319   1.0000   0.2080
  -3.750  -0.3197   0.02011   0.00937  -0.0313   1.0000   0.2484
  -3.500  -0.2978   0.01912   0.00865  -0.0307   1.0000   0.3079
  -3.250  -0.2771   0.01809   0.00817  -0.0298   1.0000   0.4059
  -3.000  -0.2615   0.01743   0.00823  -0.0268   1.0000   0.5367
  -2.750  -0.2464   0.01732   0.00837  -0.0232   1.0000   0.6449
  -2.500  -0.2305   0.01732   0.00832  -0.0201   1.0000   0.7130
  -2.250  -0.2163   0.01729   0.00829  -0.0165   1.0000   0.7624
  -2.000  -0.2028   0.01724   0.00822  -0.0128   1.0000   0.8057
  -1.750  -0.1888   0.01716   0.00811  -0.0093   1.0000   0.8462
  -1.250  -0.1391   0.01695   0.00774  -0.0070   1.0000   0.9326
  -1.000  -0.0819   0.01686   0.00747  -0.0128   1.0000   0.9832
  -0.750  -0.0625   0.01676   0.00725  -0.0128   1.0000   1.0000
  -0.500  -0.0484   0.01677   0.00713  -0.0118   1.0000   1.0000
  -0.250  -0.0272   0.01689   0.00713  -0.0121   0.9985   1.0000
   0.000   0.0195   0.01724   0.00734  -0.0168   0.9851   1.0000
   0.250   0.0651   0.01752   0.00751  -0.0212   0.9712   1.0000
   0.500   0.1075   0.01770   0.00762  -0.0247   0.9553   1.0000
   0.750   0.1492   0.01784   0.00773  -0.0280   0.9386   1.0000
   1.000   0.1912   0.01795   0.00782  -0.0311   0.9220   1.0000
   1.250   0.2342   0.01800   0.00789  -0.0342   0.9053   1.0000
   1.500   0.2783   0.01801   0.00793  -0.0372   0.8887   1.0000
   1.750   0.3187   0.01800   0.00798  -0.0395   0.8701   1.0000
   2.000   0.3570   0.01799   0.00802  -0.0412   0.8494   1.0000
   2.250   0.3972   0.01793   0.00805  -0.0429   0.8291   1.0000
   2.500   0.4313   0.01795   0.00813  -0.0436   0.8044   1.0000
   2.750   0.4653   0.01797   0.00820  -0.0442   0.7786   1.0000
   3.000   0.4976   0.01803   0.00829  -0.0443   0.7508   1.0000
   3.250   0.5277   0.01815   0.00846  -0.0440   0.7210   1.0000
   3.500   0.5559   0.01831   0.00864  -0.0433   0.6891   1.0000
   3.750   0.5829   0.01853   0.00885  -0.0425   0.6560   1.0000
   4.000   0.6085   0.01879   0.00914  -0.0415   0.6208   1.0000
   4.250   0.6337   0.01910   0.00944  -0.0404   0.5841   1.0000
   4.500   0.6579   0.01948   0.00978  -0.0393   0.5457   1.0000
   4.750   0.6816   0.01991   0.01015  -0.0381   0.5061   1.0000
   5.000   0.7044   0.02042   0.01062  -0.0369   0.4649   1.0000
   5.250   0.7266   0.02100   0.01113  -0.0357   0.4222   1.0000
   5.500   0.7481   0.02166   0.01172  -0.0345   0.3789   1.0000
   5.750   0.7690   0.02242   0.01239  -0.0333   0.3352   1.0000
   6.000   0.7892   0.02330   0.01315  -0.0322   0.2913   1.0000
   6.250   0.8089   0.02429   0.01407  -0.0311   0.2483   1.0000
   6.500   0.8284   0.02542   0.01511  -0.0301   0.2076   1.0000
   6.750   0.8475   0.02674   0.01633  -0.0291   0.1719   1.0000
   7.000   0.8657   0.02820   0.01770  -0.0280   0.1403   1.0000
   7.250   0.8838   0.02978   0.01922  -0.0270   0.1148   1.0000
   7.500   0.9011   0.03145   0.02081  -0.0259   0.0961   1.0000
   7.750   0.9188   0.03324   0.02262  -0.0249   0.0822   1.0000
   8.000   0.9376   0.03502   0.02459  -0.0238   0.0713   1.0000
   8.250   0.9579   0.03723   0.02703  -0.0228   0.0645   1.0000
   8.500   0.9768   0.03934   0.02928  -0.0219   0.0595   1.0000
   8.750   0.9947   0.04182   0.03199  -0.0209   0.0551   1.0000
   9.000   1.0103   0.04441   0.03498  -0.0198   0.0511   1.0000
   9.250   1.0243   0.04716   0.03807  -0.0188   0.0488   1.0000
   9.500   1.0362   0.05013   0.04128  -0.0177   0.0473   1.0000
   9.750   1.0457   0.05357   0.04493  -0.0167   0.0461   1.0000
  10.000   1.0463   0.05747   0.04926  -0.0152   0.0455   1.0000
  10.250   1.0404   0.06152   0.05376  -0.0137   0.0451   1.0000
  10.500   1.0280   0.06551   0.05809  -0.0121   0.0449   1.0000
  10.750   1.0115   0.06965   0.06250  -0.0112   0.0448   1.0000
  11.000   0.9918   0.07441   0.06749  -0.0117   0.0448   1.0000
  11.250   0.9714   0.07994   0.07320  -0.0139   0.0450   1.0000
  11.500   0.9498   0.08654   0.07993  -0.0178   0.0453   1.0000
  11.750   0.9295   0.09404   0.08753  -0.0228   0.0456   1.0000
  12.000   0.9112   0.10227   0.09581  -0.0284   0.0460   1.0000
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