Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(2)-415 (naca652415-il)
Reynolds number: 200,000
Max Cl/Cd: 67.97 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca652415-il-200000-n5.txt
Download as CSV file: xf-naca652415-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(2)-415                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5620   0.07687   0.07286  -0.0733   1.0000   0.0213
 -12.750  -0.5914   0.06887   0.06474  -0.0784   1.0000   0.0211
 -12.500  -0.6228   0.06217   0.05787  -0.0816   1.0000   0.0211
 -12.250  -0.6488   0.05718   0.05271  -0.0829   1.0000   0.0211
 -12.000  -0.6739   0.05312   0.04849  -0.0826   1.0000   0.0211
 -11.750  -0.6989   0.04996   0.04517  -0.0807   1.0000   0.0212
 -11.500  -0.7180   0.04575   0.04059  -0.0811   0.9879   0.0214
 -11.250  -0.7099   0.04275   0.03739  -0.0835   0.9767   0.0218
 -11.000  -0.6949   0.04075   0.03526  -0.0853   0.9662   0.0223
 -10.750  -0.6776   0.03911   0.03349  -0.0867   0.9563   0.0229
 -10.500  -0.6607   0.03696   0.03108  -0.0879   0.9474   0.0235
 -10.250  -0.6471   0.03468   0.02848  -0.0880   0.9368   0.0241
 -10.000  -0.6311   0.03240   0.02583  -0.0881   0.9278   0.0248
  -9.750  -0.6140   0.03041   0.02349  -0.0877   0.9186   0.0254
  -9.500  -0.5964   0.02889   0.02158  -0.0870   0.9096   0.0261
  -9.250  -0.5751   0.02744   0.02002  -0.0869   0.9020   0.0269
  -9.000  -0.5540   0.02646   0.01895  -0.0866   0.8944   0.0277
  -8.750  -0.5324   0.02544   0.01780  -0.0861   0.8867   0.0284
  -8.500  -0.5099   0.02441   0.01661  -0.0856   0.8799   0.0291
  -8.250  -0.4878   0.02347   0.01554  -0.0851   0.8723   0.0299
  -8.000  -0.4644   0.02264   0.01454  -0.0846   0.8664   0.0309
  -7.750  -0.4424   0.02194   0.01370  -0.0839   0.8590   0.0319
  -7.500  -0.4198   0.02097   0.01268  -0.0834   0.8529   0.0328
  -7.250  -0.3984   0.02020   0.01189  -0.0827   0.8464   0.0336
  -7.000  -0.3773   0.01954   0.01120  -0.0819   0.8396   0.0345
  -6.500  -0.3346   0.01838   0.00992  -0.0803   0.8275   0.0368
  -6.250  -0.3128   0.01789   0.00933  -0.0796   0.8218   0.0384
  -6.000  -0.2916   0.01731   0.00869  -0.0788   0.8166   0.0399
  -5.750  -0.2711   0.01676   0.00814  -0.0780   0.8100   0.0417
  -5.500  -0.2487   0.01630   0.00761  -0.0774   0.8047   0.0438
  -5.250  -0.2254   0.01590   0.00712  -0.0770   0.7999   0.0463
  -5.000  -0.2026   0.01548   0.00668  -0.0764   0.7942   0.0499
  -4.750  -0.1787   0.01511   0.00627  -0.0761   0.7893   0.0560
  -4.500  -0.1544   0.01469   0.00583  -0.0758   0.7850   0.0670
  -4.250  -0.1316   0.01420   0.00547  -0.0754   0.7793   0.0941
  -4.000  -0.1113   0.01329   0.00502  -0.0749   0.7743   0.1943
  -3.750  -0.0932   0.01197   0.00448  -0.0745   0.7703   0.3850
  -3.500  -0.0712   0.01148   0.00457  -0.0738   0.7656   0.5301
  -3.250  -0.0447   0.01147   0.00461  -0.0735   0.7608   0.5738
  -3.000  -0.0181   0.01156   0.00474  -0.0731   0.7567   0.6183
  -2.750   0.0077   0.01186   0.00510  -0.0722   0.7531   0.6567
  -2.500   0.0339   0.01203   0.00528  -0.0716   0.7484   0.6729
  -2.250   0.0620   0.01204   0.00520  -0.0718   0.7443   0.6793
  -2.000   0.0905   0.01201   0.00507  -0.0721   0.7406   0.6837
  -1.750   0.1191   0.01200   0.00499  -0.0722   0.7374   0.6870
  -1.500   0.1464   0.01201   0.00497  -0.0723   0.7327   0.6909
  -1.250   0.1746   0.01200   0.00491  -0.0725   0.7286   0.6951
  -1.000   0.2034   0.01199   0.00482  -0.0729   0.7252   0.6995
  -0.750   0.2318   0.01200   0.00479  -0.0731   0.7223   0.7025
  -0.500   0.2594   0.01203   0.00482  -0.0732   0.7183   0.7060
  -0.250   0.2871   0.01205   0.00483  -0.0734   0.7141   0.7100
   0.000   0.3157   0.01207   0.00481  -0.0737   0.7104   0.7146
   0.250   0.3441   0.01210   0.00482  -0.0739   0.7075   0.7180
   0.500   0.3723   0.01214   0.00486  -0.0741   0.7045   0.7213
   0.750   0.3994   0.01220   0.00495  -0.0741   0.7003   0.7253
   1.000   0.4274   0.01225   0.00501  -0.0744   0.6965   0.7300
   1.250   0.4556   0.01229   0.00506  -0.0746   0.6933   0.7340
   1.500   0.4840   0.01234   0.00513  -0.0748   0.6905   0.7374
   1.750   0.5112   0.01242   0.00526  -0.0749   0.6869   0.7415
   2.000   0.5385   0.01251   0.00539  -0.0750   0.6828   0.7463
   2.250   0.5662   0.01258   0.00551  -0.0751   0.6793   0.7507
   2.500   0.5939   0.01265   0.00563  -0.0752   0.6761   0.7546
   2.750   0.6224   0.01273   0.00574  -0.0754   0.6732   0.7591
   3.000   0.6488   0.01285   0.00595  -0.0754   0.6689   0.7642
   3.250   0.6753   0.01294   0.00613  -0.0753   0.6647   0.7685
   3.500   0.7027   0.01300   0.00627  -0.0753   0.6605   0.7732
   3.750   0.7299   0.01307   0.00639  -0.0753   0.6553   0.7787
   4.000   0.7556   0.01314   0.00656  -0.0750   0.6486   0.7837
   4.250   0.7831   0.01314   0.00661  -0.0748   0.6425   0.7882
   4.500   0.8068   0.01317   0.00675  -0.0741   0.6318   0.7938
   4.750   0.8309   0.01308   0.00669  -0.0732   0.6154   0.7998
   5.000   0.8516   0.01298   0.00659  -0.0716   0.5897   0.8053
   5.250   0.8716   0.01300   0.00658  -0.0700   0.5575   0.8120
   5.500   0.8918   0.01312   0.00669  -0.0685   0.5274   0.8179
   5.750   0.9084   0.01338   0.00682  -0.0664   0.4819   0.8244
   6.000   0.9140   0.01410   0.00714  -0.0625   0.4015   0.8324
   6.250   0.9108   0.01518   0.00782  -0.0574   0.3240   0.8411
   6.500   0.9052   0.01628   0.00859  -0.0520   0.2563   0.8510
   6.750   0.9008   0.01744   0.00945  -0.0471   0.1968   0.8624
   7.000   0.8989   0.01858   0.01036  -0.0429   0.1462   0.8738
   7.250   0.8992   0.01973   0.01131  -0.0391   0.1037   0.8869
   7.500   0.9024   0.02078   0.01224  -0.0359   0.0755   0.9024
   7.750   0.9084   0.02171   0.01313  -0.0332   0.0592   0.9221
   8.000   0.9185   0.02259   0.01402  -0.0313   0.0496   0.9500
   8.250   0.9330   0.02350   0.01496  -0.0305   0.0435   1.0000
   8.500   0.9456   0.02463   0.01607  -0.0296   0.0391   1.0000
   8.750   0.9597   0.02567   0.01718  -0.0287   0.0364   1.0000
   9.000   0.9724   0.02680   0.01835  -0.0277   0.0342   1.0000
   9.250   0.9818   0.02819   0.01973  -0.0265   0.0323   1.0000
   9.500   0.9947   0.02935   0.02097  -0.0256   0.0306   1.0000
   9.750   1.0071   0.03055   0.02223  -0.0247   0.0292   1.0000
  10.000   1.0184   0.03186   0.02359  -0.0238   0.0280   1.0000
  10.250   1.0281   0.03332   0.02508  -0.0228   0.0270   1.0000
  10.500   1.0362   0.03495   0.02673  -0.0217   0.0261   1.0000
  10.750   1.0481   0.03632   0.02818  -0.0209   0.0254   1.0000
  11.000   1.0599   0.03773   0.02967  -0.0201   0.0248   1.0000
  11.250   1.0718   0.03917   0.03119  -0.0193   0.0241   1.0000
  11.500   1.0841   0.04060   0.03269  -0.0186   0.0235   1.0000
  11.750   1.0963   0.04206   0.03420  -0.0179   0.0228   1.0000
  12.000   1.1087   0.04354   0.03573  -0.0173   0.0223   1.0000
  12.250   1.1204   0.04509   0.03729  -0.0168   0.0216   1.0000
  12.500   1.1338   0.04668   0.03892  -0.0162   0.0211   1.0000
  12.750   1.1463   0.04827   0.04069  -0.0156   0.0206   1.0000
  13.000   1.1591   0.04995   0.04250  -0.0151   0.0202   1.0000
  13.250   1.1710   0.05175   0.04445  -0.0146   0.0198   1.0000
  13.500   1.1819   0.05368   0.04653  -0.0141   0.0194   1.0000
  13.750   1.1913   0.05578   0.04878  -0.0136   0.0191   1.0000
  14.000   1.1989   0.05805   0.05123  -0.0132   0.0188   1.0000
  14.250   1.2049   0.06049   0.05384  -0.0129   0.0186   1.0000
  14.500   1.2090   0.06314   0.05665  -0.0127   0.0183   1.0000
  14.750   1.2114   0.06600   0.05968  -0.0126   0.0181   1.0000
  15.000   1.2121   0.06910   0.06295  -0.0127   0.0180   1.0000
  15.250   1.2112   0.07240   0.06642  -0.0130   0.0178   1.0000
  15.500   1.2093   0.07587   0.07004  -0.0134   0.0176   1.0000
  15.750   1.2062   0.07958   0.07390  -0.0141   0.0175   1.0000
  16.000   1.2020   0.08356   0.07803  -0.0150   0.0173   1.0000
  16.250   1.1953   0.08801   0.08264  -0.0162   0.0172   1.0000
  16.500   1.1814   0.09362   0.08849  -0.0181   0.0170   1.0000
  16.750   1.1655   0.09987   0.09499  -0.0207   0.0170   1.0000
  17.000   1.1483   0.10668   0.10205  -0.0239   0.0170   1.0000
  17.250   1.1277   0.11449   0.11012  -0.0281   0.0169   1.0000
  17.500   1.1063   0.12306   0.11892  -0.0332   0.0169   1.0000
  17.750   1.0836   0.13253   0.12861  -0.0391   0.0169   1.0000
  18.000   1.0584   0.14342   0.13970  -0.0463   0.0170   1.0000
  18.250   1.0289   0.15650   0.15297  -0.0551   0.0171   1.0000
<< Back to NACA 65(2)-415 (naca652415-il)

Polar data table (+)

Polar graphs


<< Back to NACA 65(2)-415 (naca652415-il)