Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Rhode St. Genese 36 (rhodesg36-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Rhode St. Genese 36 (rhodesg36-il)
Reynolds number: 50,000
Max Cl/Cd: 27.78 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rhodesg36-il-50000-n5.txt
Download as CSV file: xf-rhodesg36-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Rhode St. Genese 36                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1576   0.10422   0.09728  -0.0683   0.9382   0.1058
 -10.500  -0.1380   0.10135   0.09442  -0.0685   0.9322   0.1028
 -10.250  -0.1540   0.09619   0.08924  -0.0737   0.9225   0.0965
 -10.000  -0.1509   0.09348   0.08656  -0.0744   0.9141   0.0959
  -9.750  -0.1566   0.09099   0.08410  -0.0745   0.9046   0.0952
  -9.500  -0.1640   0.08804   0.08117  -0.0756   0.8957   0.0947
  -9.250  -0.1679   0.08448   0.07760  -0.0775   0.8871   0.0940
  -9.000  -0.1788   0.08133   0.07442  -0.0776   0.8768   0.0933
  -8.750  -0.1785   0.07673   0.06972  -0.0807   0.8702   0.0920
  -8.500  -0.1941   0.07306   0.06594  -0.0802   0.8601   0.0908
  -8.250  -0.2076   0.06678   0.05926  -0.0823   0.8521   0.0888
  -8.000  -0.2071   0.06290   0.05507  -0.0822   0.8434   0.0882
  -7.750  -0.1940   0.05888   0.05067  -0.0833   0.8367   0.0884
  -7.500  -0.1809   0.05722   0.04897  -0.0821   0.8267   0.0894
  -7.250  -0.1475   0.05437   0.04589  -0.0844   0.8208   0.0913
  -7.000  -0.1400   0.05224   0.04351  -0.0823   0.8084   0.0923
  -6.750  -0.1036   0.04848   0.03924  -0.0848   0.8026   0.0935
  -6.500  -0.0950   0.04656   0.03700  -0.0822   0.7893   0.0941
  -6.250  -0.0576   0.04338   0.03321  -0.0839   0.7841   0.0964
  -6.000  -0.0484   0.04255   0.03227  -0.0811   0.7715   0.0980
  -5.750  -0.0115   0.04099   0.03056  -0.0822   0.7663   0.1008
  -5.500   0.0005   0.04013   0.02951  -0.0798   0.7553   0.1024
  -5.250   0.0343   0.03838   0.02737  -0.0802   0.7489   0.1051
  -5.000   0.0552   0.03766   0.02659  -0.0789   0.7391   0.1079
  -4.750   0.0850   0.03669   0.02551  -0.0787   0.7308   0.1119
  -4.500   0.1121   0.03568   0.02423  -0.0779   0.7219   0.1155
  -4.250   0.1396   0.03491   0.02349  -0.0773   0.7122   0.1192
  -4.000   0.1646   0.03425   0.02268  -0.0763   0.7017   0.1248
  -3.750   0.1989   0.03331   0.02170  -0.0765   0.6926   0.1310
  -3.500   0.2226   0.03276   0.02100  -0.0752   0.6804   0.1376
  -3.250   0.2648   0.03167   0.01982  -0.0765   0.6723   0.1497
  -3.000   0.2843   0.03121   0.01938  -0.0747   0.6581   0.1592
  -2.750   0.3156   0.03034   0.01849  -0.0745   0.6465   0.1775
  -2.500   0.3474   0.02936   0.01760  -0.0745   0.6345   0.2057
  -2.250   0.3679   0.02884   0.01722  -0.0729   0.6190   0.2415
  -2.000   0.3936   0.02811   0.01673  -0.0722   0.6046   0.3012
  -1.500   0.5150   0.02575   0.01605  -0.0819   0.5689   1.0000
  -1.250   0.5356   0.02581   0.01578  -0.0803   0.5525   1.0000
  -1.000   0.5509   0.02607   0.01579  -0.0781   0.5355   1.0000
  -0.750   0.5677   0.02634   0.01581  -0.0761   0.5201   1.0000
  -0.500   0.5873   0.02659   0.01579  -0.0746   0.5070   1.0000
  -0.250   0.6117   0.02673   0.01562  -0.0738   0.4965   1.0000
   0.000   0.6302   0.02711   0.01579  -0.0723   0.4857   1.0000
   0.250   0.6542   0.02737   0.01576  -0.0715   0.4770   1.0000
   0.500   0.6743   0.02779   0.01598  -0.0703   0.4682   1.0000
   0.750   0.7019   0.02804   0.01594  -0.0702   0.4612   1.0000
   1.000   0.7195   0.02862   0.01641  -0.0688   0.4535   1.0000
   1.250   0.7451   0.02903   0.01661  -0.0685   0.4472   1.0000
   1.500   0.7730   0.02945   0.01682  -0.0686   0.4419   1.0000
   1.750   0.7914   0.03014   0.01746  -0.0675   0.4364   1.0000
   2.000   0.8152   0.03071   0.01793  -0.0671   0.4314   1.0000
   2.250   0.8452   0.03117   0.01822  -0.0676   0.4270   1.0000
   2.500   0.8717   0.03175   0.01868  -0.0677   0.4228   1.0000
   2.750   0.8857   0.03263   0.01959  -0.0661   0.4182   1.0000
   3.000   0.9047   0.03340   0.02034  -0.0652   0.4138   1.0000
   3.250   0.9300   0.03405   0.02090  -0.0651   0.4099   1.0000
   3.500   0.9615   0.03461   0.02133  -0.0660   0.4067   1.0000
   3.750   0.9844   0.03544   0.02212  -0.0657   0.4038   1.0000
   4.000   0.9900   0.03669   0.02349  -0.0632   0.4006   1.0000
   4.250   0.9974   0.03795   0.02482  -0.0610   0.3975   1.0000
   4.500   1.0080   0.03916   0.02608  -0.0592   0.3943   1.0000
   4.750   1.0237   0.04023   0.02717  -0.0582   0.3914   1.0000
   5.000   1.0467   0.04110   0.02800  -0.0580   0.3886   1.0000
   5.250   1.0788   0.04174   0.02857  -0.0591   0.3862   1.0000
   5.500   1.0797   0.04342   0.03035  -0.0564   0.3836   1.0000
   5.750   1.0451   0.04679   0.03397  -0.0505   0.3802   1.0000
   6.000   0.9955   0.05205   0.03948  -0.0450   0.3760   1.0000
   6.250   0.9455   0.05879   0.04642  -0.0416   0.3712   1.0000
   6.500   0.9449   0.06181   0.04948  -0.0408   0.3683   1.0000
   6.750   0.9654   0.06285   0.05051  -0.0405   0.3664   1.0000
   7.250   0.7867   0.09220   0.08033  -0.0423   0.3485   1.0000
   7.500   0.8032   0.09378   0.08191  -0.0422   0.3467   1.0000
   7.750   0.8243   0.09481   0.08293  -0.0419   0.3453   1.0000
   8.000   0.7657   0.10610   0.09436  -0.0442   0.3391   1.0000
   8.250   0.7592   0.11062   0.09893  -0.0450   0.3362   1.0000
<< Back to Rhode St. Genese 36 (rhodesg36-il)

Polar data table (+)

Polar graphs


<< Back to Rhode St. Genese 36 (rhodesg36-il)