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Rhode St. Genese 32 (rhodesg32-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Rhode St. Genese 32 (rhodesg32-il)
Reynolds number: 50,000
Max Cl/Cd: 24.3 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rhodesg32-il-50000.txt
Download as CSV file: xf-rhodesg32-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Rhode St. Genese 32                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3400   0.10574   0.09908  -0.0248   1.0000   0.2625
  -9.750  -0.3057   0.09997   0.09326  -0.0229   1.0000   0.2744
  -9.500  -0.3461   0.10127   0.09478  -0.0204   1.0000   0.2795
  -9.250  -0.3182   0.09641   0.08990  -0.0186   1.0000   0.2920
  -9.000  -0.3630   0.09778   0.09150  -0.0147   1.0000   0.2966
  -8.750  -0.3374   0.09333   0.08704  -0.0129   1.0000   0.3095
  -8.500  -0.3875   0.09474   0.08868  -0.0080   1.0000   0.3138
  -8.250  -0.3645   0.09068   0.08461  -0.0062   1.0000   0.3274
  -8.000  -0.4248   0.09232   0.08649  -0.0023   1.0000   0.3318
  -7.750  -0.4020   0.08850   0.08268   0.0011   1.0000   0.3466
  -7.500  -0.3994   0.08597   0.08021   0.0041   1.0000   0.3591
  -7.250  -0.4108   0.08428   0.07861   0.0073   1.0000   0.3729
  -7.000  -0.4180   0.08252   0.07693   0.0107   1.0000   0.3905
  -6.750  -0.4228   0.08080   0.07528   0.0144   1.0000   0.4116
  -6.500  -0.4467   0.08001   0.07460   0.0178   1.0000   0.4350
  -6.250  -0.4286   0.07724   0.07187   0.0227   1.0000   0.4635
  -6.000  -0.4270   0.07543   0.07012   0.0277   1.0000   0.4982
  -5.750  -0.4332   0.07414   0.06892   0.0333   1.0000   0.5378
  -5.500  -0.3735   0.07075   0.06548   0.0368   1.0000   0.6196
  -5.250  -0.0609   0.05692   0.05103   0.0047   1.0000   0.9297
  -5.000  -0.1051   0.05782   0.05210   0.0138   1.0000   0.9066
  -4.750  -0.3498   0.04892   0.04150  -0.0230   1.0000   0.2303
  -4.500  -0.3233   0.04573   0.03772  -0.0249   1.0000   0.2097
  -4.250  -0.3034   0.04339   0.03518  -0.0251   1.0000   0.2022
  -4.000  -0.2498   0.04103   0.03198  -0.0309   0.9885   0.1922
  -3.750  -0.1967   0.03951   0.02992  -0.0362   0.9737   0.1929
  -3.500  -0.1454   0.03820   0.02815  -0.0408   0.9585   0.1934
  -3.250  -0.0939   0.03708   0.02664  -0.0451   0.9424   0.1951
  -3.000  -0.0433   0.03608   0.02562  -0.0493   0.9256   0.2037
  -2.750   0.0115   0.03526   0.02447  -0.0536   0.9081   0.2123
  -2.500   0.0567   0.03439   0.02361  -0.0561   0.8885   0.2233
  -2.250   0.1088   0.03355   0.02274  -0.0596   0.8677   0.2464
  -2.000   0.1644   0.03214   0.02166  -0.0632   0.8475   0.2932
  -1.750   0.2687   0.02839   0.01993  -0.0737   0.8303   1.0000
  -1.500   0.3380   0.02764   0.01878  -0.0792   0.8098   1.0000
  -1.250   0.3787   0.02718   0.01809  -0.0799   0.7821   1.0000
  -1.000   0.4345   0.02624   0.01691  -0.0827   0.7608   1.0000
  -0.750   0.4675   0.02591   0.01638  -0.0822   0.7336   1.0000
  -0.500   0.5091   0.02536   0.01561  -0.0829   0.7132   1.0000
  -0.250   0.5463   0.02504   0.01506  -0.0833   0.6946   1.0000
   0.000   0.5700   0.02537   0.01522  -0.0821   0.6750   1.0000
   0.250   0.6004   0.02553   0.01519  -0.0819   0.6606   1.0000
   0.500   0.6242   0.02607   0.01561  -0.0812   0.6470   1.0000
   0.750   0.6428   0.02695   0.01642  -0.0800   0.6347   1.0000
   1.000   0.6689   0.02753   0.01689  -0.0797   0.6258   1.0000
   1.250   0.6877   0.02851   0.01783  -0.0786   0.6165   1.0000
   1.500   0.7103   0.02936   0.01861  -0.0781   0.6093   1.0000
   1.750   0.7241   0.03068   0.01995  -0.0767   0.6014   1.0000
   2.000   0.7543   0.03117   0.02035  -0.0769   0.5962   1.0000
   2.250   0.7524   0.03353   0.02280  -0.0742   0.5889   1.0000
   2.500   0.7654   0.03516   0.02444  -0.0731   0.5840   1.0000
   2.750   0.7888   0.03624   0.02553  -0.0730   0.5806   1.0000
   3.000   0.7779   0.03962   0.02898  -0.0702   0.5763   1.0000
   3.250   0.7254   0.04610   0.03550  -0.0654   0.5721   1.0000
   3.500   0.6745   0.05276   0.04213  -0.0619   0.5702   1.0000
   3.750   0.6546   0.05733   0.04667  -0.0606   0.5700   1.0000
   4.000   0.6398   0.06161   0.05094  -0.0599   0.5728   1.0000
   4.250   0.6407   0.06497   0.05431  -0.0600   0.5763   1.0000
   4.500   0.6510   0.06789   0.05725  -0.0604   0.5796   1.0000
   4.750   0.6194   0.07333   0.06269  -0.0601   0.5941   1.0000
   5.000   0.4709   0.08341   0.07286  -0.0591   0.7503   1.0000
   5.250   0.4983   0.08643   0.07591  -0.0608   0.7447   1.0000
   5.500   0.4998   0.08754   0.07703  -0.0593   0.7346   1.0000
   5.750   0.5193   0.08996   0.07947  -0.0598   0.7233   1.0000
   6.000   0.5405   0.09227   0.08181  -0.0603   0.7082   1.0000
   6.250   0.5651   0.09493   0.08453  -0.0612   0.6934   1.0000
   6.500   0.5913   0.09778   0.08744  -0.0622   0.6780   1.0000
   6.750   0.5997   0.09940   0.08912  -0.0614   0.6628   1.0000
   7.000   0.6107   0.10152   0.09130  -0.0611   0.6471   1.0000
   7.250   0.6221   0.10394   0.09380  -0.0609   0.6313   1.0000
   7.500   0.6376   0.10677   0.09671  -0.0611   0.6143   1.0000
   7.750   0.6551   0.10989   0.09991  -0.0614   0.5970   1.0000
   8.000   0.6636   0.11268   0.10276  -0.0613   0.5809   1.0000
   8.250   0.6618   0.11523   0.10535  -0.0608   0.5678   1.0000
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