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RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RG-15 8.9% (rg15-il)
Reynolds number: 500,000
Max Cl/Cd: 79.01 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg15-il-500000-n5.txt
Download as CSV file: xf-rg15-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5275   0.08066   0.07842  -0.0290   1.0000   0.0053
  -9.250  -0.5460   0.07314   0.07095  -0.0330   1.0000   0.0052
  -9.000  -0.5609   0.06696   0.06484  -0.0370   1.0000   0.0053
  -8.750  -0.7166   0.03110   0.02781  -0.0460   1.0000   0.0045
  -8.500  -0.7080   0.02861   0.02504  -0.0446   1.0000   0.0047
  -8.250  -0.6939   0.02712   0.02338  -0.0433   1.0000   0.0049
  -8.000  -0.6743   0.02554   0.02158  -0.0430   0.9994   0.0051
  -7.750  -0.6466   0.02332   0.01900  -0.0445   0.9973   0.0055
  -7.500  -0.6185   0.02084   0.01612  -0.0459   0.9952   0.0058
  -7.250  -0.5903   0.01879   0.01371  -0.0468   0.9931   0.0060
  -7.000  -0.5622   0.01709   0.01172  -0.0475   0.9905   0.0063
  -6.750  -0.5324   0.01584   0.01025  -0.0483   0.9879   0.0066
  -6.500  -0.5012   0.01488   0.00912  -0.0494   0.9856   0.0069
  -6.250  -0.4696   0.01375   0.00785  -0.0507   0.9836   0.0077
  -6.000  -0.4396   0.01323   0.00727  -0.0514   0.9804   0.0084
  -5.750  -0.4099   0.01268   0.00666  -0.0519   0.9765   0.0095
  -5.500  -0.3780   0.01218   0.00607  -0.0530   0.9733   0.0106
  -5.250  -0.3451   0.01159   0.00543  -0.0543   0.9709   0.0123
  -5.000  -0.3158   0.01122   0.00502  -0.0547   0.9663   0.0144
  -4.750  -0.2854   0.01084   0.00458  -0.0553   0.9615   0.0161
  -4.500  -0.2524   0.01041   0.00408  -0.0565   0.9581   0.0177
  -4.250  -0.2222   0.01000   0.00365  -0.0571   0.9526   0.0209
  -4.000  -0.1905   0.00968   0.00329  -0.0579   0.9467   0.0235
  -3.750  -0.1570   0.00933   0.00293  -0.0592   0.9417   0.0290
  -3.500  -0.1257   0.00900   0.00262  -0.0599   0.9340   0.0417
  -3.250  -0.0925   0.00867   0.00235  -0.0611   0.9268   0.0647
  -3.000  -0.0603   0.00837   0.00213  -0.0621   0.9172   0.0929
  -2.750  -0.0293   0.00808   0.00193  -0.0629   0.9056   0.1282
  -2.500   0.0004   0.00771   0.00173  -0.0634   0.8923   0.1894
  -2.250   0.0286   0.00727   0.00156  -0.0637   0.8773   0.2792
  -2.000   0.0559   0.00689   0.00142  -0.0638   0.8610   0.3693
  -1.750   0.0829   0.00664   0.00131  -0.0637   0.8436   0.4368
  -1.500   0.1085   0.00629   0.00123  -0.0633   0.8254   0.5396
  -1.250   0.1341   0.00611   0.00124  -0.0627   0.8065   0.6240
  -1.000   0.1605   0.00610   0.00122  -0.0623   0.7873   0.6600
  -0.750   0.1869   0.00612   0.00120  -0.0618   0.7673   0.6846
  -0.500   0.2132   0.00616   0.00120  -0.0613   0.7471   0.7058
  -0.250   0.2395   0.00620   0.00120  -0.0608   0.7260   0.7247
   0.000   0.2656   0.00627   0.00121  -0.0603   0.7046   0.7415
   0.250   0.2918   0.00634   0.00123  -0.0599   0.6825   0.7568
   0.500   0.3178   0.00642   0.00126  -0.0594   0.6604   0.7715
   0.750   0.3437   0.00651   0.00129  -0.0588   0.6377   0.7864
   1.000   0.3695   0.00660   0.00134  -0.0583   0.6146   0.8014
   1.500   0.4202   0.00680   0.00146  -0.0571   0.5671   0.8327
   1.750   0.4452   0.00691   0.00153  -0.0564   0.5422   0.8488
   2.000   0.4701   0.00704   0.00162  -0.0557   0.5172   0.8636
   2.250   0.4948   0.00718   0.00171  -0.0550   0.4909   0.8777
   2.500   0.5192   0.00733   0.00180  -0.0542   0.4650   0.8931
   2.750   0.5433   0.00748   0.00190  -0.0533   0.4390   0.9106
   3.250   0.5961   0.00785   0.00214  -0.0527   0.3823   0.9557
   3.500   0.6293   0.00811   0.00228  -0.0540   0.3479   0.9847
   3.750   0.6572   0.00837   0.00244  -0.0542   0.3203   1.0000
   4.000   0.6825   0.00866   0.00263  -0.0539   0.2926   1.0000
   4.250   0.7079   0.00896   0.00285  -0.0535   0.2654   1.0000
   4.500   0.7328   0.00932   0.00307  -0.0531   0.2340   1.0000
   4.750   0.7573   0.00972   0.00333  -0.0527   0.2010   1.0000
   5.000   0.7821   0.01009   0.00360  -0.0523   0.1741   1.0000
   5.250   0.8066   0.01051   0.00389  -0.0518   0.1464   1.0000
   5.500   0.8312   0.01090   0.00422  -0.0514   0.1240   1.0000
   5.750   0.8554   0.01135   0.00457  -0.0509   0.1000   1.0000
   6.000   0.8790   0.01186   0.00495  -0.0503   0.0752   1.0000
   6.500   0.9267   0.01280   0.00576  -0.0493   0.0445   1.0000
   6.750   0.9505   0.01327   0.00618  -0.0487   0.0339   1.0000
   7.000   0.9744   0.01372   0.00665  -0.0482   0.0270   1.0000
   7.250   0.9977   0.01422   0.00715  -0.0475   0.0191   1.0000
   7.500   1.0199   0.01485   0.00774  -0.0468   0.0115   1.0000
   7.750   1.0420   0.01550   0.00839  -0.0459   0.0079   1.0000
   8.000   1.0648   0.01604   0.00901  -0.0452   0.0070   1.0000
   8.250   1.0870   0.01664   0.00969  -0.0444   0.0063   1.0000
   8.500   1.1086   0.01728   0.01044  -0.0435   0.0058   1.0000
   8.750   1.1291   0.01804   0.01129  -0.0424   0.0052   1.0000
   9.000   1.1484   0.01891   0.01228  -0.0412   0.0049   1.0000
   9.250   1.1645   0.02010   0.01361  -0.0395   0.0045   1.0000
   9.500   1.1811   0.02115   0.01479  -0.0380   0.0044   1.0000
   9.750   1.1979   0.02212   0.01588  -0.0365   0.0043   1.0000
  10.000   1.2139   0.02311   0.01700  -0.0350   0.0042   1.0000
  10.250   1.2297   0.02406   0.01807  -0.0334   0.0040   1.0000
  10.500   1.2437   0.02512   0.01928  -0.0317   0.0038   1.0000
  10.750   1.2560   0.02620   0.02049  -0.0297   0.0036   1.0000
  11.000   1.2638   0.02741   0.02184  -0.0271   0.0035   1.0000
  11.250   1.2693   0.02875   0.02332  -0.0243   0.0034   1.0000
  11.500   1.2737   0.03017   0.02489  -0.0217   0.0033   1.0000
  11.750   1.2761   0.03177   0.02665  -0.0191   0.0032   1.0000
  12.000   1.2759   0.03366   0.02871  -0.0166   0.0032   1.0000
  12.250   1.2778   0.03543   0.03062  -0.0148   0.0031   1.0000
  12.500   1.2761   0.03764   0.03299  -0.0131   0.0030   1.0000
  12.750   1.2713   0.04037   0.03589  -0.0118   0.0030   1.0000
  13.000   1.2687   0.04303   0.03869  -0.0113   0.0029   1.0000
  13.250   1.2611   0.04656   0.04240  -0.0112   0.0029   1.0000
  13.500   1.2516   0.05066   0.04669  -0.0119   0.0029   1.0000
  13.750   1.2432   0.05500   0.05119  -0.0134   0.0028   1.0000
  14.000   1.2292   0.06059   0.05698  -0.0158   0.0028   1.0000
  14.250   1.2194   0.06598   0.06250  -0.0186   0.0028   1.0000
  14.500   1.1990   0.07365   0.07040  -0.0227   0.0029   1.0000
  14.750   1.1858   0.08051   0.07739  -0.0268   0.0028   1.0000
  15.000   1.1652   0.08920   0.08627  -0.0320   0.0029   1.0000
  15.250   1.1442   0.09850   0.09573  -0.0375   0.0029   1.0000
  15.500   1.1215   0.10859   0.10597  -0.0434   0.0029   1.0000
  15.750   1.0975   0.11953   0.11706  -0.0498   0.0029   1.0000
  16.000   1.0677   0.13247   0.13017  -0.0572   0.0031   1.0000
  16.250   1.0351   0.14710   0.14495  -0.0654   0.0032   1.0000
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