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RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RG-15 8.9% (rg15-il)
Reynolds number: 50,000
Max Cl/Cd: 34.85 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg15-il-50000.txt
Download as CSV file: xf-rg15-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG-15 8.9%                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4551   0.10813   0.10116  -0.0106   1.0000   0.2451
  -8.750  -0.4522   0.10499   0.09802  -0.0103   1.0000   0.2586
  -8.500  -0.4753   0.10441   0.09767  -0.0119   1.0000   0.2667
  -8.250  -0.4500   0.09899   0.09217  -0.0097   1.0000   0.2843
  -7.750  -0.4457   0.09289   0.08620  -0.0083   1.0000   0.3123
  -7.500  -0.4400   0.08960   0.08297  -0.0071   1.0000   0.3281
  -7.250  -0.4364   0.08663   0.08006  -0.0058   1.0000   0.3437
  -7.000  -0.4371   0.08396   0.07747  -0.0042   1.0000   0.3617
  -6.750  -0.4548   0.08257   0.07627  -0.0019   1.0000   0.3799
  -6.500  -0.4435   0.07936   0.07308   0.0008   1.0000   0.4069
  -5.750  -0.4834   0.05057   0.04338  -0.0388   1.0000   0.1369
  -5.500  -0.4683   0.04515   0.03733  -0.0397   1.0000   0.1238
  -5.250  -0.4508   0.04081   0.03247  -0.0395   1.0000   0.1183
  -5.000  -0.4313   0.03732   0.02846  -0.0390   1.0000   0.1190
  -4.750  -0.4099   0.03442   0.02501  -0.0384   1.0000   0.1239
  -4.500  -0.3860   0.03155   0.02152  -0.0375   1.0000   0.1258
  -4.250  -0.3621   0.02892   0.01862  -0.0366   1.0000   0.1300
  -4.000  -0.3374   0.02700   0.01631  -0.0355   1.0000   0.1403
  -3.750  -0.3146   0.02517   0.01457  -0.0344   1.0000   0.1589
  -3.500  -0.2901   0.02338   0.01273  -0.0328   1.0000   0.1833
  -3.250  -0.2680   0.02154   0.01131  -0.0314   1.0000   0.2443
  -3.000  -0.2517   0.01834   0.00993  -0.0290   1.0000   0.4762
  -2.750  -0.2623   0.01773   0.01067  -0.0168   1.0000   0.7758
  -2.500  -0.1054   0.01826   0.00995  -0.0327   1.0000   1.0000
  -2.250  -0.1096   0.01785   0.00944  -0.0290   1.0000   1.0000
  -2.000  -0.1136   0.01752   0.00899  -0.0251   1.0000   1.0000
  -1.750  -0.1143   0.01727   0.00856  -0.0216   1.0000   1.0000
  -1.500  -0.1065   0.01715   0.00822  -0.0194   1.0000   1.0000
  -1.250  -0.0923   0.01715   0.00799  -0.0183   1.0000   1.0000
  -1.000  -0.0749   0.01724   0.00784  -0.0175   1.0000   1.0000
  -0.750  -0.0561   0.01739   0.00779  -0.0170   1.0000   1.0000
  -0.500  -0.0367   0.01760   0.00778  -0.0166   1.0000   1.0000
  -0.250  -0.0172   0.01787   0.00788  -0.0163   1.0000   1.0000
   0.000   0.0023   0.01818   0.00805  -0.0160   1.0000   1.0000
   0.250   0.0216   0.01856   0.00829  -0.0157   1.0000   1.0000
   0.500   0.0406   0.01899   0.00861  -0.0155   1.0000   1.0000
   0.750   0.0593   0.01947   0.00899  -0.0154   1.0000   1.0000
   1.000   0.0776   0.02002   0.00947  -0.0153   1.0000   1.0000
   1.250   0.0955   0.02063   0.01002  -0.0152   1.0000   1.0000
   1.500   0.1129   0.02132   0.01067  -0.0153   1.0000   1.0000
   1.750   0.1300   0.02208   0.01139  -0.0154   1.0000   1.0000
   2.000   0.1882   0.02352   0.01284  -0.0231   0.9801   1.0000
   2.250   0.2466   0.02471   0.01408  -0.0303   0.9581   1.0000
   2.500   0.2989   0.02560   0.01507  -0.0360   0.9348   1.0000
   2.750   0.3532   0.02634   0.01592  -0.0416   0.9117   1.0000
   3.000   0.4096   0.02682   0.01660  -0.0470   0.8883   1.0000
   3.250   0.4573   0.02712   0.01708  -0.0505   0.8631   1.0000
   3.500   0.5088   0.02717   0.01734  -0.0541   0.8378   1.0000
   3.750   0.5652   0.02685   0.01733  -0.0576   0.8127   1.0000
   4.000   0.6178   0.02627   0.01701  -0.0598   0.7866   1.0000
   4.250   0.6628   0.02567   0.01665  -0.0603   0.7579   1.0000
   4.500   0.7019   0.02512   0.01636  -0.0597   0.7266   1.0000
   4.750   0.7405   0.02445   0.01585  -0.0585   0.6932   1.0000
   5.000   0.7690   0.02426   0.01576  -0.0563   0.6555   1.0000
   5.250   0.7967   0.02411   0.01565  -0.0539   0.6150   1.0000
   5.500   0.8217   0.02414   0.01566  -0.0513   0.5710   1.0000
   5.750   0.8457   0.02431   0.01576  -0.0486   0.5239   1.0000
   6.000   0.8649   0.02482   0.01617  -0.0458   0.4723   1.0000
   6.250   0.8836   0.02552   0.01667  -0.0429   0.4183   1.0000
   6.500   0.9010   0.02650   0.01740  -0.0402   0.3633   1.0000
   6.750   0.9179   0.02778   0.01838  -0.0377   0.3107   1.0000
   7.000   0.9349   0.02940   0.01981  -0.0355   0.2635   1.0000
   7.250   0.9523   0.03118   0.02150  -0.0335   0.2234   1.0000
   7.500   0.9728   0.03341   0.02361  -0.0320   0.1918   1.0000
   7.750   0.9919   0.03589   0.02617  -0.0304   0.1662   1.0000
   8.000   1.0096   0.03853   0.02889  -0.0288   0.1447   1.0000
   8.250   1.0262   0.04175   0.03243  -0.0270   0.1291   1.0000
   8.500   1.0392   0.04471   0.03564  -0.0251   0.1146   1.0000
   8.750   1.0533   0.04876   0.03991  -0.0235   0.1065   1.0000
   9.000   1.0567   0.05244   0.04419  -0.0210   0.1003   1.0000
   9.250   1.0648   0.05618   0.04807  -0.0195   0.0936   1.0000
   9.500   1.0600   0.06079   0.05321  -0.0172   0.0926   1.0000
   9.750   1.0518   0.06554   0.05838  -0.0152   0.0926   1.0000
  10.000   1.0389   0.07037   0.06354  -0.0136   0.0930   1.0000
  10.250   1.0242   0.07515   0.06854  -0.0123   0.0937   1.0000
  10.500   1.0082   0.07980   0.07332  -0.0112   0.0944   1.0000
  10.750   0.9955   0.08493   0.07854  -0.0111   0.0951   1.0000
  11.000   0.9190   0.09507   0.08890  -0.0192   0.1062   1.0000
  11.250   0.9066   0.10230   0.09611  -0.0227   0.1076   1.0000
  11.500   0.9004   0.10925   0.10305  -0.0256   0.1084   1.0000
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