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Rhode St. Genese 30 (rhodesg30-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Rhode St. Genese 30 (rhodesg30-il)
Reynolds number: 50,000
Max Cl/Cd: 34.66 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rhodesg30-il-50000.txt
Download as CSV file: xf-rhodesg30-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Rhode St. Genese 30                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3989   0.10672   0.09981  -0.0206   1.0000   0.2136
 -10.250  -0.3899   0.10244   0.09557  -0.0201   1.0000   0.2219
 -10.000  -0.4050   0.10127   0.09454  -0.0214   1.0000   0.2299
  -9.750  -0.3933   0.09684   0.09014  -0.0201   1.0000   0.2431
  -9.500  -0.3908   0.09344   0.08681  -0.0192   1.0000   0.2570
  -9.250  -0.3940   0.09067   0.08412  -0.0181   1.0000   0.2734
  -9.000  -0.4020   0.08833   0.08190  -0.0166   1.0000   0.2902
  -8.750  -0.3900   0.08443   0.07803  -0.0127   1.0000   0.3333
  -8.500  -0.4311   0.08455   0.07846  -0.0131   1.0000   0.3233
  -8.250  -0.3761   0.07929   0.07289  -0.0054   1.0000   0.4111
  -8.000  -0.3723   0.07734   0.07096  -0.0019   1.0000   0.4436
  -7.750  -0.3575   0.07529   0.06888   0.0022   1.0000   0.4909
  -7.500  -0.3611   0.07403   0.06770   0.0066   1.0000   0.5234
  -7.250  -0.3136   0.06992   0.06339   0.0066   1.0000   0.5616
  -7.000  -0.3190   0.06907   0.06263   0.0117   1.0000   0.6004
  -6.750  -0.2730   0.06517   0.05859   0.0108   1.0000   0.6391
  -6.500  -0.2559   0.06342   0.05684   0.0141   1.0000   0.6935
  -5.500  -0.3865   0.04604   0.03884  -0.0216   1.0000   0.2755
  -5.250  -0.3609   0.04245   0.03468  -0.0244   1.0000   0.2432
  -5.000  -0.3384   0.03988   0.03168  -0.0254   1.0000   0.2265
  -4.750  -0.3151   0.03779   0.02902  -0.0260   1.0000   0.2135
  -4.500  -0.2950   0.03615   0.02719  -0.0256   1.0000   0.2085
  -4.250  -0.2716   0.03469   0.02515  -0.0258   1.0000   0.2015
  -4.000  -0.2500   0.03362   0.02377  -0.0253   1.0000   0.1988
  -3.750  -0.2291   0.03254   0.02250  -0.0248   1.0000   0.1974
  -3.500  -0.2079   0.03159   0.02135  -0.0243   1.0000   0.1953
  -3.250  -0.1866   0.03075   0.02030  -0.0238   1.0000   0.1933
  -3.000  -0.1653   0.03004   0.01936  -0.0232   1.0000   0.1914
  -2.750  -0.1441   0.02945   0.01853  -0.0226   1.0000   0.1895
  -2.500  -0.1230   0.02898   0.01787  -0.0221   1.0000   0.1885
  -2.250  -0.1020   0.02862   0.01737  -0.0216   1.0000   0.1881
  -2.000  -0.0826   0.02837   0.01703  -0.0209   1.0000   0.1885
  -1.750  -0.0499   0.02832   0.01692  -0.0226   0.9948   0.1901
  -1.500   0.0126   0.02849   0.01699  -0.0294   0.9764   0.1951
  -1.250   0.0750   0.02851   0.01701  -0.0360   0.9574   0.2048
  -1.000   0.1293   0.02835   0.01699  -0.0411   0.9365   0.2227
  -0.750   0.2048   0.02536   0.01671  -0.0492   0.9184   1.0000
  -0.500   0.2712   0.02575   0.01650  -0.0554   0.8953   1.0000
  -0.250   0.3267   0.02588   0.01642  -0.0599   0.8688   1.0000
   0.000   0.3835   0.02577   0.01618  -0.0642   0.8418   1.0000
   0.250   0.4372   0.02549   0.01583  -0.0676   0.8160   1.0000
   0.500   0.4876   0.02507   0.01533  -0.0700   0.7921   1.0000
   0.750   0.5224   0.02496   0.01516  -0.0700   0.7656   1.0000
   1.000   0.5604   0.02474   0.01488  -0.0704   0.7442   1.0000
   1.250   0.5878   0.02496   0.01504  -0.0696   0.7219   1.0000
   1.500   0.6181   0.02517   0.01519  -0.0693   0.7045   1.0000
   1.750   0.6459   0.02554   0.01554  -0.0688   0.6885   1.0000
   2.000   0.6712   0.02607   0.01606  -0.0682   0.6737   1.0000
   2.250   0.6943   0.02679   0.01678  -0.0674   0.6601   1.0000
   2.500   0.7159   0.02770   0.01771  -0.0667   0.6481   1.0000
   2.750   0.7413   0.02846   0.01853  -0.0664   0.6387   1.0000
   3.000   0.7624   0.02949   0.01963  -0.0657   0.6287   1.0000
   3.250   0.7781   0.03092   0.02116  -0.0648   0.6188   1.0000
   3.500   0.8067   0.03157   0.02187  -0.0647   0.6116   1.0000
   3.750   0.8125   0.03384   0.02431  -0.0634   0.6025   1.0000
   4.000   0.8443   0.03431   0.02487  -0.0634   0.5960   1.0000
   4.250   0.8443   0.03696   0.02767  -0.0617   0.5859   1.0000
   4.500   0.8624   0.03807   0.02890  -0.0605   0.5747   1.0000
   4.750   0.8893   0.03826   0.02923  -0.0593   0.5615   1.0000
   5.000   0.9182   0.03830   0.02939  -0.0582   0.5482   1.0000
   5.250   0.9433   0.03840   0.02964  -0.0566   0.5327   1.0000
   5.500   0.9922   0.03546   0.02668  -0.0548   0.5059   1.0000
   5.750   1.0094   0.03564   0.02702  -0.0524   0.4848   1.0000
   6.000   1.0439   0.03422   0.02559  -0.0506   0.4594   1.0000
   6.250   1.0657   0.03400   0.02550  -0.0484   0.4359   1.0000
   6.500   1.0885   0.03330   0.02483  -0.0459   0.4058   1.0000
   6.750   1.1058   0.03255   0.02405  -0.0425   0.3676   1.0000
   7.000   1.1078   0.03196   0.02340  -0.0371   0.3133   1.0000
   7.250   1.0968   0.03240   0.02369  -0.0308   0.2481   1.0000
   7.500   1.0927   0.03371   0.02451  -0.0262   0.2010   1.0000
   7.750   1.0983   0.03566   0.02604  -0.0232   0.1760   1.0000
   8.000   1.1117   0.03791   0.02794  -0.0215   0.1573   1.0000
   8.250   1.1389   0.04059   0.03044  -0.0212   0.1426   1.0000
   8.500   1.1597   0.04327   0.03336  -0.0203   0.1327   1.0000
   8.750   1.1818   0.04632   0.03654  -0.0198   0.1241   1.0000
   9.000   1.1996   0.04942   0.03991  -0.0187   0.1185   1.0000
   9.250   1.2177   0.05311   0.04369  -0.0181   0.1129   1.0000
   9.500   1.2137   0.05621   0.04730  -0.0152   0.1103   1.0000
   9.750   1.2096   0.05973   0.05122  -0.0127   0.1086   1.0000
  10.000   1.1997   0.06338   0.05522  -0.0100   0.1080   1.0000
  10.250   1.1826   0.06711   0.05925  -0.0072   0.1077   1.0000
  10.500   1.1598   0.07126   0.06367  -0.0053   0.1081   1.0000
  10.750   1.1326   0.07613   0.06878  -0.0046   0.1091   1.0000
  11.000   1.1022   0.08193   0.07478  -0.0054   0.1102   1.0000
  11.250   1.0715   0.08882   0.08182  -0.0077   0.1116   1.0000
  11.500   1.0431   0.09662   0.08970  -0.0112   0.1129   1.0000
  11.750   1.0219   0.10470   0.09783  -0.0147   0.1140   1.0000
  12.000   0.8784   0.14281   0.13560  -0.0421   0.1444   1.0000
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