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NACA 2415 (naca2415-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 2415 (naca2415-il)
Reynolds number: 50,000
Max Cl/Cd: 27.36 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2415-il-50000.txt
Download as CSV file: xf-naca2415-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2415                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3609   0.10637   0.09836  -0.0166   1.0000   0.3628
  -9.000  -0.5860   0.07654   0.06889  -0.0420   1.0000   0.1974
  -8.750  -0.6048   0.07186   0.06423  -0.0407   1.0000   0.1962
  -8.500  -0.6294   0.06702   0.05936  -0.0390   1.0000   0.1949
  -8.250  -0.6550   0.06216   0.05438  -0.0367   1.0000   0.1939
  -8.000  -0.6766   0.05749   0.04949  -0.0342   1.0000   0.1938
  -7.750  -0.6920   0.05310   0.04477  -0.0316   1.0000   0.1948
  -7.500  -0.7028   0.04894   0.04011  -0.0290   1.0000   0.1971
  -7.250  -0.6893   0.04724   0.03851  -0.0271   1.0000   0.2028
  -7.000  -0.6822   0.04498   0.03606  -0.0251   1.0000   0.2090
  -6.750  -0.6796   0.04185   0.03238  -0.0231   1.0000   0.2155
  -6.500  -0.6623   0.04082   0.03153  -0.0214   1.0000   0.2243
  -6.250  -0.6519   0.03855   0.02887  -0.0198   1.0000   0.2339
  -6.000  -0.6358   0.03738   0.02767  -0.0182   1.0000   0.2454
  -5.750  -0.6195   0.03606   0.02633  -0.0168   1.0000   0.2573
  -5.500  -0.6031   0.03470   0.02481  -0.0155   1.0000   0.2714
  -5.250  -0.5857   0.03355   0.02352  -0.0143   1.0000   0.2871
  -5.000  -0.5672   0.03256   0.02245  -0.0132   1.0000   0.3042
  -4.750  -0.5480   0.03171   0.02158  -0.0122   1.0000   0.3225
  -4.500  -0.5286   0.03094   0.02086  -0.0112   1.0000   0.3419
  -4.250  -0.5091   0.03025   0.02024  -0.0101   1.0000   0.3626
  -4.000  -0.4897   0.02964   0.01973  -0.0091   1.0000   0.3853
  -3.750  -0.4700   0.02906   0.01915  -0.0082   1.0000   0.4113
  -3.500  -0.4507   0.02858   0.01881  -0.0071   1.0000   0.4376
  -3.250  -0.4314   0.02820   0.01850  -0.0061   1.0000   0.4687
  -3.000  -0.4128   0.02794   0.01846  -0.0048   1.0000   0.4994
  -2.750  -0.3949   0.02776   0.01843  -0.0035   1.0000   0.5341
  -2.500  -0.3774   0.02765   0.01850  -0.0020   1.0000   0.5721
  -2.250  -0.3604   0.02760   0.01862  -0.0003   1.0000   0.6147
  -2.000  -0.3444   0.02759   0.01883   0.0017   1.0000   0.6616
  -1.750  -0.3304   0.02764   0.01912   0.0043   1.0000   0.7157
  -1.500  -0.3199   0.02778   0.01956   0.0083   1.0000   0.7754
  -1.250  -0.2914   0.02846   0.02047   0.0099   0.9934   0.8635
  -1.000  -0.1424   0.03109   0.02284  -0.0113   0.9825   0.9781
  -0.750  -0.0571   0.03151   0.02294  -0.0262   0.9673   1.0000
  -0.500  -0.0301   0.03152   0.02274  -0.0295   0.9494   1.0000
  -0.250   0.0017   0.03183   0.02286  -0.0326   0.9329   1.0000
   0.000   0.0358   0.03230   0.02314  -0.0355   0.9173   1.0000
   0.250   0.0725   0.03282   0.02350  -0.0385   0.9023   1.0000
   0.500   0.1165   0.03338   0.02391  -0.0424   0.8885   1.0000
   0.750   0.1449   0.03389   0.02431  -0.0436   0.8729   1.0000
   1.000   0.1703   0.03447   0.02480  -0.0442   0.8577   1.0000
   1.250   0.1971   0.03509   0.02533  -0.0449   0.8430   1.0000
   1.500   0.2278   0.03572   0.02589  -0.0461   0.8292   1.0000
   1.750   0.2781   0.03609   0.02621  -0.0500   0.8176   1.0000
   2.000   0.2956   0.03684   0.02691  -0.0490   0.8024   1.0000
   2.250   0.3140   0.03769   0.02771  -0.0483   0.7880   1.0000
   2.500   0.3408   0.03840   0.02840  -0.0486   0.7744   1.0000
   2.750   0.3954   0.03841   0.02842  -0.0523   0.7636   1.0000
   3.000   0.4065   0.03941   0.02940  -0.0504   0.7481   1.0000
   3.250   0.4242   0.04031   0.03028  -0.0493   0.7331   1.0000
   3.500   0.4503   0.04093   0.03091  -0.0491   0.7188   1.0000
   3.750   0.5061   0.04037   0.03040  -0.0518   0.7073   1.0000
   4.000   0.5302   0.04092   0.03097  -0.0511   0.6928   1.0000
   4.250   0.5402   0.04216   0.03222  -0.0490   0.6774   1.0000
   4.500   0.5571   0.04317   0.03326  -0.0477   0.6631   1.0000
   4.750   0.6063   0.04248   0.03263  -0.0489   0.6516   1.0000
   5.000   0.6394   0.04249   0.03271  -0.0486   0.6384   1.0000
   5.250   0.6503   0.04379   0.03404  -0.0466   0.6227   1.0000
   5.500   0.6643   0.04496   0.03526  -0.0449   0.6074   1.0000
   5.750   0.6919   0.04523   0.03560  -0.0440   0.5931   1.0000
   6.000   0.7732   0.04174   0.03222  -0.0462   0.5824   1.0000
   6.250   0.7915   0.04234   0.03287  -0.0442   0.5655   1.0000
   6.500   0.8143   0.04261   0.03320  -0.0425   0.5486   1.0000
   6.750   0.8428   0.04242   0.03308  -0.0411   0.5313   1.0000
   7.000   0.8748   0.04199   0.03269  -0.0399   0.5137   1.0000
   7.250   0.9081   0.04146   0.03220  -0.0388   0.4957   1.0000
   7.500   0.9418   0.04092   0.03168  -0.0377   0.4771   1.0000
   7.750   0.9800   0.04009   0.03081  -0.0371   0.4575   1.0000
   8.000   1.0079   0.03996   0.03065  -0.0357   0.4373   1.0000
   8.250   1.0226   0.04064   0.03139  -0.0332   0.4172   1.0000
   8.500   1.0408   0.04105   0.03181  -0.0310   0.3962   1.0000
   8.750   1.0660   0.04096   0.03166  -0.0293   0.3740   1.0000
   9.000   1.1027   0.04030   0.03072  -0.0288   0.3504   1.0000
   9.250   1.1118   0.04137   0.03185  -0.0259   0.3304   1.0000
   9.500   1.1233   0.04238   0.03286  -0.0233   0.3108   1.0000
   9.750   1.1361   0.04338   0.03385  -0.0210   0.2919   1.0000
  10.000   1.1490   0.04451   0.03494  -0.0187   0.2745   1.0000
  10.250   1.1609   0.04585   0.03626  -0.0165   0.2586   1.0000
  10.500   1.1731   0.04735   0.03773  -0.0145   0.2442   1.0000
  10.750   1.1890   0.04891   0.03922  -0.0129   0.2309   1.0000
  11.000   1.2135   0.05038   0.04049  -0.0124   0.2176   1.0000
  11.250   1.1898   0.05379   0.04437  -0.0076   0.2126   1.0000
  11.500   1.2207   0.05537   0.04575  -0.0077   0.2013   1.0000
  11.750   1.1894   0.05909   0.04988  -0.0027   0.1990   1.0000
  12.000   1.1535   0.06350   0.05460   0.0014   0.1974   1.0000
  12.250   1.1064   0.06963   0.06102   0.0039   0.1975   1.0000
  12.500   1.0421   0.07918   0.07080   0.0032   0.1996   1.0000
  12.750   0.9696   0.09312   0.08485  -0.0018   0.2018   1.0000
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