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NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-410 (naca65410-il)
Reynolds number: 500,000
Max Cl/Cd: 97.84 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65410-il-500000.txt
Download as CSV file: xf-naca65410-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-410                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4435   0.09342   0.09111  -0.0427   1.0000   0.0168
  -9.750  -0.4428   0.09010   0.08781  -0.0432   1.0000   0.0170
  -9.500  -0.4429   0.08650   0.08423  -0.0445   1.0000   0.0171
  -9.250  -0.4432   0.08326   0.08102  -0.0453   1.0000   0.0174
  -9.000  -0.4457   0.07969   0.07748  -0.0465   1.0000   0.0175
  -8.750  -0.4518   0.07588   0.07372  -0.0479   1.0000   0.0177
  -8.500  -0.4695   0.07146   0.06937  -0.0498   1.0000   0.0176
  -8.250  -0.4973   0.06720   0.06513  -0.0516   0.9983   0.0174
  -8.000  -0.4807   0.06106   0.05887  -0.0599   0.9930   0.0177
  -7.750  -0.4634   0.05580   0.05347  -0.0661   0.9874   0.0182
  -7.500  -0.4415   0.05057   0.04806  -0.0719   0.9837   0.0190
  -7.250  -0.4213   0.04564   0.04289  -0.0757   0.9772   0.0205
  -7.000  -0.3866   0.04247   0.03923  -0.0786   0.9733   0.0227
  -6.750  -0.3592   0.03812   0.03449  -0.0820   0.9705   0.0228
  -6.500  -0.3479   0.02991   0.02587  -0.0841   0.9622   0.0241
  -6.250  -0.3193   0.02832   0.02426  -0.0860   0.9582   0.0257
  -6.000  -0.2922   0.02650   0.02223  -0.0869   0.9524   0.0281
  -5.750  -0.2672   0.02052   0.01545  -0.0857   0.9449   0.0215
  -5.500  -0.2406   0.01807   0.01264  -0.0856   0.9387   0.0215
  -5.250  -0.2146   0.01655   0.01088  -0.0852   0.9313   0.0220
  -5.000  -0.1882   0.01498   0.00905  -0.0850   0.9250   0.0237
  -4.750  -0.1635   0.01362   0.00761  -0.0845   0.9173   0.0250
  -4.500  -0.1371   0.01280   0.00672  -0.0843   0.9110   0.0260
  -4.250  -0.1117   0.01214   0.00600  -0.0839   0.9032   0.0274
  -4.000  -0.0852   0.01166   0.00545  -0.0836   0.8967   0.0296
  -3.750  -0.0592   0.01122   0.00494  -0.0833   0.8889   0.0311
  -3.500  -0.0330   0.01068   0.00432  -0.0830   0.8825   0.0323
  -3.250  -0.0078   0.00986   0.00344  -0.0828   0.8749   0.0355
  -3.000   0.0194   0.00955   0.00309  -0.0828   0.8688   0.0397
  -2.750   0.0464   0.00930   0.00277  -0.0827   0.8613   0.0431
  -2.500   0.0740   0.00894   0.00236  -0.0827   0.8553   0.0524
  -2.250   0.0995   0.00778   0.00198  -0.0832   0.8479   0.2792
  -2.000   0.1244   0.00659   0.00188  -0.0835   0.8420   0.6186
  -1.750   0.1515   0.00651   0.00189  -0.0833   0.8350   0.6646
  -1.500   0.1785   0.00650   0.00193  -0.0830   0.8289   0.7054
  -1.250   0.2049   0.00654   0.00204  -0.0825   0.8224   0.7418
  -1.000   0.2320   0.00658   0.00207  -0.0822   0.8161   0.7611
  -0.750   0.2591   0.00663   0.00211  -0.0819   0.8102   0.7762
  -0.500   0.2863   0.00665   0.00213  -0.0818   0.8036   0.7869
  -0.250   0.3143   0.00667   0.00212  -0.0818   0.7982   0.7933
   0.000   0.3420   0.00668   0.00213  -0.0818   0.7915   0.8004
   0.250   0.3699   0.00671   0.00213  -0.0818   0.7859   0.8071
   0.500   0.3975   0.00673   0.00217  -0.0818   0.7797   0.8142
   0.750   0.4252   0.00675   0.00220  -0.0818   0.7737   0.8211
   1.000   0.4529   0.00680   0.00225  -0.0818   0.7682   0.8284
   1.250   0.4803   0.00682   0.00230  -0.0817   0.7619   0.8356
   1.500   0.5079   0.00687   0.00235  -0.0817   0.7564   0.8431
   1.750   0.5347   0.00688   0.00242  -0.0814   0.7481   0.8505
   2.000   0.5611   0.00690   0.00244  -0.0811   0.7368   0.8588
   2.250   0.5867   0.00690   0.00246  -0.0805   0.7241   0.8663
   2.500   0.6126   0.00692   0.00247  -0.0800   0.7085   0.8751
   2.750   0.6364   0.00694   0.00249  -0.0789   0.6870   0.8831
   3.000   0.6603   0.00700   0.00251  -0.0780   0.6606   0.8923
   3.250   0.6843   0.00709   0.00259  -0.0771   0.6374   0.9019
   3.500   0.7064   0.00722   0.00267  -0.0758   0.6034   0.9114
   3.750   0.7255   0.00751   0.00278  -0.0739   0.5420   0.9228
   4.000   0.7311   0.00875   0.00320  -0.0699   0.3594   0.9387
   4.250   0.7326   0.01052   0.00393  -0.0656   0.1381   0.9619
   4.500   0.7552   0.01166   0.00459  -0.0653   0.0452   1.0000
   4.750   0.7817   0.01216   0.00511  -0.0655   0.0373   1.0000
   5.000   0.8044   0.01302   0.00601  -0.0649   0.0313   1.0000
   5.250   0.8303   0.01343   0.00646  -0.0648   0.0290   1.0000
   5.500   0.8543   0.01400   0.00706  -0.0644   0.0266   1.0000
   5.750   0.8766   0.01471   0.00779  -0.0637   0.0247   1.0000
   6.000   0.8946   0.01590   0.00904  -0.0623   0.0232   1.0000
   6.250   0.9125   0.01740   0.01063  -0.0608   0.0222   1.0000
   6.500   0.9361   0.01813   0.01141  -0.0603   0.0216   1.0000
   6.750   0.9598   0.01887   0.01222  -0.0597   0.0206   1.0000
   7.000   0.9833   0.01983   0.01324  -0.0592   0.0196   1.0000
   7.250   1.0073   0.02101   0.01450  -0.0587   0.0190   1.0000
   7.500   1.0318   0.02234   0.01593  -0.0584   0.0184   1.0000
   7.750   1.0562   0.02378   0.01747  -0.0580   0.0178   1.0000
   8.000   1.0798   0.02533   0.01914  -0.0576   0.0173   1.0000
   8.250   1.1020   0.02728   0.02118  -0.0572   0.0164   1.0000
   8.500   1.1203   0.03266   0.02697  -0.0563   0.0159   1.0000
   8.750   1.1355   0.03597   0.03059  -0.0548   0.0159   1.0000
   9.000   1.1498   0.03862   0.03352  -0.0531   0.0160   1.0000
   9.250   1.1634   0.04083   0.03598  -0.0513   0.0161   1.0000
   9.500   1.0633   0.05164   0.04820  -0.0388   0.0223   1.0000
   9.750   1.0524   0.05559   0.05237  -0.0355   0.0223   1.0000
  10.000   1.0341   0.05875   0.05570  -0.0314   0.0223   1.0000
  10.250   1.0126   0.06211   0.05922  -0.0280   0.0223   1.0000
  10.500   0.9891   0.06592   0.06319  -0.0256   0.0222   1.0000
  10.750   0.9655   0.07055   0.06796  -0.0244   0.0223   1.0000
  11.000   0.9396   0.07589   0.07345  -0.0242   0.0223   1.0000
  11.250   0.9150   0.08154   0.07923  -0.0251   0.0223   1.0000
  11.500   0.8896   0.08789   0.08570  -0.0271   0.0223   1.0000
  11.750   0.8633   0.09473   0.09266  -0.0302   0.0223   1.0000
  12.000   0.8371   0.10198   0.10002  -0.0343   0.0223   1.0000
  12.250   0.8118   0.10944   0.10758  -0.0393   0.0224   1.0000
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