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NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-410 (naca65410-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.39 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65410-il-1000000.txt
Download as CSV file: xf-naca65410-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4383   0.08550   0.08388  -0.0435   1.0000   0.0117
  -9.250  -0.4410   0.08099   0.07940  -0.0456   1.0000   0.0117
  -9.000  -0.4457   0.07644   0.07487  -0.0478   1.0000   0.0117
  -7.500  -0.4181   0.03516   0.03265  -0.0848   0.9661   0.0106
  -7.250  -0.4131   0.02386   0.02047  -0.0851   0.9514   0.0100
  -7.000  -0.3984   0.01790   0.01378  -0.0839   0.9403   0.0104
  -6.750  -0.3765   0.01573   0.01127  -0.0832   0.9309   0.0110
  -6.500  -0.3510   0.01504   0.01041  -0.0829   0.9230   0.0115
  -6.250  -0.3286   0.01314   0.00824  -0.0824   0.9145   0.0126
  -6.000  -0.3028   0.01273   0.00778  -0.0822   0.9065   0.0132
  -5.750  -0.2768   0.01231   0.00726  -0.0820   0.8991   0.0139
  -5.500  -0.2510   0.01173   0.00660  -0.0818   0.8914   0.0147
  -5.000  -0.1982   0.01094   0.00565  -0.0814   0.8765   0.0162
  -4.750  -0.1740   0.00989   0.00447  -0.0810   0.8693   0.0177
  -4.500  -0.1474   0.00953   0.00410  -0.0810   0.8618   0.0188
  -4.250  -0.1207   0.00924   0.00374  -0.0809   0.8552   0.0199
  -4.000  -0.0936   0.00892   0.00339  -0.0809   0.8479   0.0212
  -3.750  -0.0664   0.00876   0.00316  -0.0809   0.8413   0.0224
  -3.500  -0.0394   0.00833   0.00266  -0.0809   0.8340   0.0238
  -3.000   0.0155   0.00776   0.00199  -0.0810   0.8207   0.0287
  -2.750   0.0432   0.00763   0.00180  -0.0811   0.8143   0.0311
  -2.500   0.0711   0.00742   0.00155  -0.0812   0.8077   0.0359
  -2.250   0.0990   0.00727   0.00138  -0.0813   0.8011   0.0430
  -2.000   0.1264   0.00665   0.00118  -0.0817   0.7948   0.1782
  -1.750   0.1527   0.00534   0.00096  -0.0826   0.7883   0.5285
  -1.500   0.1806   0.00515   0.00096  -0.0828   0.7823   0.6072
  -1.250   0.2088   0.00508   0.00095  -0.0829   0.7758   0.6416
  -1.000   0.2365   0.00504   0.00098  -0.0830   0.7699   0.6818
  -0.750   0.2646   0.00501   0.00102  -0.0830   0.7636   0.7088
  -0.500   0.2926   0.00503   0.00104  -0.0831   0.7576   0.7253
  -0.250   0.3207   0.00505   0.00107  -0.0831   0.7516   0.7414
   0.000   0.3489   0.00506   0.00108  -0.0833   0.7455   0.7488
   0.250   0.3771   0.00509   0.00110  -0.0834   0.7398   0.7556
   0.500   0.4055   0.00511   0.00111  -0.0836   0.7336   0.7623
   0.750   0.4335   0.00515   0.00115  -0.0836   0.7279   0.7690
   1.000   0.4619   0.00516   0.00118  -0.0838   0.7207   0.7760
   1.250   0.4894   0.00520   0.00121  -0.0838   0.7110   0.7828
   1.500   0.5170   0.00526   0.00123  -0.0837   0.6986   0.7900
   1.750   0.5446   0.00527   0.00129  -0.0837   0.6882   0.7969
   2.000   0.5716   0.00536   0.00133  -0.0836   0.6708   0.8044
   2.250   0.5983   0.00543   0.00138  -0.0834   0.6480   0.8115
   2.500   0.6250   0.00555   0.00145  -0.0832   0.6261   0.8192
   2.750   0.6509   0.00569   0.00154  -0.0828   0.5967   0.8268
   3.000   0.6760   0.00594   0.00165  -0.0824   0.5527   0.8347
   3.250   0.6952   0.00672   0.00194  -0.0810   0.4300   0.8431
   3.500   0.7103   0.00802   0.00250  -0.0791   0.2552   0.8520
   3.750   0.7272   0.00918   0.00304  -0.0776   0.1120   0.8618
   4.000   0.7477   0.00991   0.00347  -0.0765   0.0414   0.8713
   4.250   0.7717   0.01026   0.00381  -0.0758   0.0312   0.8806
   4.500   0.7968   0.01048   0.00408  -0.0754   0.0281   0.8905
   4.750   0.8191   0.01093   0.00458  -0.0744   0.0228   0.9012
   5.000   0.8426   0.01117   0.00488  -0.0736   0.0214   0.9123
   5.250   0.8654   0.01144   0.00520  -0.0727   0.0199   0.9243
   5.500   0.8869   0.01172   0.00554  -0.0715   0.0185   0.9379
   5.750   0.9057   0.01208   0.00596  -0.0697   0.0173   0.9568
   6.000   0.9242   0.01313   0.00717  -0.0682   0.0158   1.0000
   6.250   0.9506   0.01339   0.00744  -0.0682   0.0154   1.0000
   6.500   0.9753   0.01381   0.00788  -0.0679   0.0147   1.0000
   6.750   0.9984   0.01437   0.00849  -0.0673   0.0141   1.0000
   7.000   1.0208   0.01498   0.00915  -0.0666   0.0135   1.0000
   7.250   1.0430   0.01561   0.00983  -0.0659   0.0130   1.0000
   7.500   1.0648   0.01628   0.01053  -0.0651   0.0126   1.0000
   7.750   1.0861   0.01700   0.01129  -0.0643   0.0122   1.0000
   8.000   1.1046   0.01821   0.01255  -0.0631   0.0115   1.0000
   8.250   1.1228   0.02006   0.01455  -0.0618   0.0109   1.0000
   8.500   1.1451   0.02071   0.01529  -0.0611   0.0107   1.0000
   8.750   1.1666   0.02160   0.01627  -0.0604   0.0103   1.0000
   9.000   1.1874   0.02272   0.01750  -0.0595   0.0099   1.0000
   9.250   1.2075   0.02390   0.01881  -0.0586   0.0096   1.0000
   9.500   1.2268   0.02494   0.01995  -0.0577   0.0092   1.0000
   9.750   1.2452   0.02567   0.02076  -0.0566   0.0088   1.0000
  10.000   1.2627   0.02622   0.02136  -0.0554   0.0085   1.0000
  10.250   1.2790   0.02674   0.02193  -0.0541   0.0082   1.0000
  10.500   1.2883   0.02920   0.02459  -0.0521   0.0078   1.0000
  10.750   1.2873   0.03310   0.02892  -0.0487   0.0075   1.0000
  11.000   1.2938   0.03430   0.03026  -0.0460   0.0074   1.0000
  11.250   1.2966   0.03601   0.03217  -0.0431   0.0072   1.0000
  11.500   1.2947   0.03831   0.03469  -0.0400   0.0070   1.0000
  11.750   1.2866   0.04130   0.03794  -0.0367   0.0069   1.0000
  12.000   1.2712   0.04520   0.04212  -0.0335   0.0067   1.0000
  12.250   1.2496   0.04990   0.04711  -0.0307   0.0066   1.0000
  12.500   1.2165   0.05639   0.05393  -0.0288   0.0066   1.0000
  12.750   1.1748   0.06462   0.06248  -0.0286   0.0067   1.0000
  13.000   1.1370   0.07318   0.07128  -0.0305   0.0067   1.0000
  13.250   1.1059   0.08164   0.07993  -0.0342   0.0067   1.0000
  13.500   1.0738   0.09166   0.09011  -0.0400   0.0069   1.0000
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