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Rhode St. Genese 34 (rhodesg34-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Rhode St. Genese 34 (rhodesg34-il)
Reynolds number: 50,000
Max Cl/Cd: 20.37 at α=0.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rhodesg34-il-50000.txt
Download as CSV file: xf-rhodesg34-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Rhode St. Genese 34                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3015   0.11569   0.10939  -0.0175   1.0000   0.2347
 -10.000  -0.3334   0.11657   0.11041  -0.0157   1.0000   0.2396
  -9.750  -0.3804   0.11853   0.11255  -0.0135   1.0000   0.2409
  -9.500  -0.3265   0.11096   0.10492  -0.0117   1.0000   0.2493
  -9.250  -0.3443   0.11037   0.10444  -0.0096   1.0000   0.2562
  -9.000  -0.3909   0.11177   0.10599  -0.0070   1.0000   0.2591
  -8.750  -0.3593   0.10658   0.10081  -0.0053   1.0000   0.2668
  -8.500  -0.3749   0.10564   0.09996  -0.0028   1.0000   0.2742
  -8.250  -0.4225   0.10648   0.10095   0.0003   1.0000   0.2778
  -8.000  -0.4023   0.10239   0.09689   0.0022   1.0000   0.2853
  -7.750  -0.4192   0.10131   0.09590   0.0050   1.0000   0.2933
  -7.500  -0.4549   0.10023   0.09493   0.0052   1.0000   0.2997
  -7.250  -0.4362   0.09724   0.09197   0.0090   1.0000   0.3089
  -7.000  -0.4646   0.09571   0.09053   0.0090   1.0000   0.3194
  -6.750  -0.4539   0.09322   0.08808   0.0125   1.0000   0.3294
  -6.500  -0.4647   0.09099   0.08592   0.0138   1.0000   0.3418
  -6.250  -0.4759   0.08907   0.08405   0.0147   1.0000   0.3584
  -6.000  -0.4565   0.08632   0.08134   0.0150   0.9945   0.3798
  -5.750  -0.4183   0.08342   0.07844   0.0125   0.9800   0.4192
  -5.250  -0.3357   0.07870   0.07377   0.0159   0.9527   0.5396
  -5.000  -0.1065   0.07146   0.06627   0.0040   0.9423   0.7806
  -4.750  -0.2300   0.05658   0.04914  -0.0477   0.9250   0.2011
  -4.500  -0.1870   0.05293   0.04474  -0.0519   0.9100   0.1846
  -4.250  -0.1471   0.05051   0.04198  -0.0547   0.8937   0.1829
  -4.000  -0.1059   0.04833   0.03940  -0.0573   0.8771   0.1805
  -3.750  -0.0630   0.04649   0.03711  -0.0597   0.8595   0.1807
  -3.500  -0.0189   0.04510   0.03518  -0.0618   0.8411   0.1854
  -3.250   0.0247   0.04344   0.03342  -0.0639   0.8224   0.1913
  -3.000   0.0709   0.04220   0.03189  -0.0658   0.8031   0.2020
  -2.750   0.1190   0.04072   0.03035  -0.0680   0.7840   0.2167
  -2.500   0.1689   0.03929   0.02880  -0.0700   0.7653   0.2414
  -2.250   0.2222   0.03749   0.02725  -0.0725   0.7474   0.2902
  -2.000   0.3451   0.03280   0.02478  -0.0853   0.7332   1.0000
  -1.750   0.3863   0.03227   0.02382  -0.0860   0.7149   1.0000
  -1.500   0.4235   0.03181   0.02303  -0.0862   0.6978   1.0000
  -1.250   0.4565   0.03150   0.02244  -0.0859   0.6817   1.0000
  -1.000   0.4876   0.03133   0.02201  -0.0855   0.6671   1.0000
  -0.750   0.5410   0.03028   0.02066  -0.0879   0.6587   1.0000
  -0.500   0.5561   0.03097   0.02118  -0.0859   0.6441   1.0000
  -0.250   0.5702   0.03187   0.02194  -0.0839   0.6314   1.0000
   0.000   0.6164   0.03127   0.02109  -0.0856   0.6245   1.0000
   0.250   0.6156   0.03302   0.02278  -0.0822   0.6119   1.0000
   0.500   0.6619   0.03249   0.02202  -0.0840   0.6062   1.0000
   0.750   0.6452   0.03522   0.02478  -0.0791   0.5946   1.0000
   1.000   0.6841   0.03515   0.02454  -0.0801   0.5895   1.0000
   1.250   0.6446   0.03960   0.02906  -0.0737   0.5797   1.0000
   1.500   0.6525   0.04149   0.03088  -0.0721   0.5742   1.0000
   1.750   0.6907   0.04162   0.03090  -0.0731   0.5711   1.0000
   2.000   0.5508   0.05429   0.04371  -0.0630   0.5628   1.0000
   2.250   0.5370   0.05823   0.04762  -0.0616   0.5602   1.0000
   2.500   0.5293   0.06182   0.05118  -0.0606   0.5592   1.0000
   2.750   0.5157   0.06598   0.05531  -0.0598   0.5618   1.0000
   3.000   0.5138   0.06944   0.05875  -0.0596   0.5654   1.0000
   3.250   0.5246   0.07226   0.06153  -0.0599   0.5684   1.0000
   3.500   0.3585   0.08537   0.07504  -0.0590   0.7214   1.0000
   3.750   0.3702   0.08711   0.07673  -0.0587   0.7165   1.0000
   4.000   0.3895   0.08945   0.07899  -0.0592   0.7127   1.0000
   4.250   0.4169   0.09280   0.08227  -0.0608   0.7099   1.0000
   4.500   0.4091   0.09317   0.08262  -0.0584   0.7033   1.0000
   4.750   0.4284   0.09536   0.08477  -0.0589   0.6962   1.0000
   5.000   0.4593   0.09917   0.08853  -0.0608   0.6927   1.0000
   5.250   0.4485   0.09918   0.08853  -0.0582   0.6846   1.0000
   5.500   0.4713   0.10184   0.09118  -0.0591   0.6783   1.0000
   5.750   0.4815   0.10408   0.09340  -0.0590   0.6729   1.0000
   6.000   0.4926   0.10571   0.09502  -0.0586   0.6631   1.0000
   6.250   0.5283   0.11034   0.09964  -0.0610   0.6585   1.0000
   6.500   0.5176   0.11003   0.09935  -0.0586   0.6466   1.0000
   6.750   0.5445   0.11387   0.10319  -0.0600   0.6403   1.0000
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