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NACA 23018 (naca23018-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 23018 (naca23018-il)
Reynolds number: 50,000
Max Cl/Cd: 26.17 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca23018-il-50000-n5.txt
Download as CSV file: xf-naca23018-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 23018                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.6727   0.10450   0.09564  -0.0399   1.0000   0.0922
 -14.250  -0.7432   0.08914   0.08002  -0.0492   1.0000   0.0918
 -14.000  -0.7917   0.07969   0.07029  -0.0540   1.0000   0.0916
 -13.750  -0.8275   0.07303   0.06335  -0.0562   1.0000   0.0917
 -13.500  -0.8560   0.06789   0.05791  -0.0567   1.0000   0.0921
 -13.250  -0.8719   0.06413   0.05394  -0.0562   1.0000   0.0928
 -13.000  -0.8634   0.06205   0.05185  -0.0555   1.0000   0.0943
 -12.750  -0.8635   0.05962   0.04931  -0.0544   1.0000   0.0958
 -12.500  -0.8661   0.05713   0.04667  -0.0530   1.0000   0.0973
 -12.250  -0.8690   0.05472   0.04406  -0.0513   1.0000   0.0988
 -12.000  -0.8714   0.05243   0.04152  -0.0491   1.0000   0.1004
 -11.750  -0.8742   0.05031   0.03910  -0.0465   1.0000   0.1020
 -11.500  -0.8538   0.04886   0.03775  -0.0459   1.0000   0.1044
 -11.250  -0.8416   0.04738   0.03624  -0.0444   1.0000   0.1069
 -11.000  -0.8320   0.04584   0.03456  -0.0425   1.0000   0.1097
 -10.750  -0.8234   0.04432   0.03281  -0.0403   1.0000   0.1124
 -10.500  -0.8019   0.04308   0.03170  -0.0396   1.0000   0.1156
 -10.250  -0.7877   0.04191   0.03051  -0.0379   1.0000   0.1192
 -10.000  -0.7750   0.04073   0.02919  -0.0359   1.0000   0.1232
  -9.750  -0.7585   0.03963   0.02819  -0.0343   1.0000   0.1272
  -9.500  -0.7471   0.03863   0.02720  -0.0321   1.0000   0.1317
  -9.250  -0.7366   0.03766   0.02615  -0.0296   1.0000   0.1370
  -9.000  -0.7285   0.03670   0.02532  -0.0268   1.0000   0.1419
  -8.750  -0.7207   0.03577   0.02438  -0.0239   1.0000   0.1484
  -8.500  -0.7161   0.03482   0.02353  -0.0206   1.0000   0.1548
  -8.250  -0.7117   0.03392   0.02266  -0.0172   1.0000   0.1632
  -8.000  -0.7104   0.03298   0.02187  -0.0134   1.0000   0.1717
  -7.750  -0.7086   0.03208   0.02109  -0.0097   1.0000   0.1830
  -7.500  -0.7074   0.03118   0.02034  -0.0058   1.0000   0.1975
  -7.250  -0.7064   0.03030   0.01965  -0.0019   1.0000   0.2165
  -7.000  -0.7045   0.02948   0.01905   0.0018   1.0000   0.2430
  -6.750  -0.7022   0.02875   0.01857   0.0056   1.0000   0.2760
  -6.500  -0.6979   0.02819   0.01822   0.0091   1.0000   0.3127
  -6.250  -0.6916   0.02778   0.01797   0.0124   1.0000   0.3482
  -6.000  -0.6835   0.02749   0.01777   0.0154   1.0000   0.3806
  -5.750  -0.6518   0.02731   0.01768   0.0142   0.9919   0.4214
  -5.500  -0.6166   0.02722   0.01766   0.0125   0.9814   0.4604
  -5.250  -0.5825   0.02717   0.01764   0.0111   0.9703   0.4953
  -5.000  -0.5472   0.02722   0.01776   0.0099   0.9594   0.5241
  -4.750  -0.5090   0.02730   0.01787   0.0083   0.9495   0.5529
  -4.500  -0.4771   0.02732   0.01791   0.0078   0.9372   0.5815
  -4.250  -0.4420   0.02747   0.01810   0.0071   0.9256   0.6053
  -4.000  -0.3992   0.02743   0.01803   0.0047   0.9163   0.6251
  -3.750  -0.3653   0.02737   0.01793   0.0040   0.9031   0.6401
  -3.500  -0.3213   0.02730   0.01784   0.0015   0.8933   0.6552
  -3.250  -0.2857   0.02716   0.01765   0.0004   0.8805   0.6706
  -3.000  -0.2539   0.02698   0.01742   0.0000   0.8671   0.6871
  -2.750  -0.2081   0.02693   0.01736  -0.0023   0.8570   0.7008
  -2.500  -0.1770   0.02687   0.01727  -0.0023   0.8418   0.7153
  -2.250  -0.1437   0.02671   0.01706  -0.0027   0.8282   0.7312
  -2.000  -0.1023   0.02662   0.01693  -0.0041   0.8159   0.7451
  -1.750  -0.0695   0.02659   0.01689  -0.0042   0.7997   0.7587
  -1.500  -0.0381   0.02647   0.01671  -0.0042   0.7844   0.7741
  -1.250   0.0020   0.02638   0.01655  -0.0053   0.7701   0.7871
  -1.000   0.0382   0.02632   0.01642  -0.0058   0.7538   0.8000
  -0.750   0.0664   0.02625   0.01629  -0.0052   0.7359   0.8154
  -0.500   0.1052   0.02629   0.01625  -0.0062   0.7178   0.8266
  -0.250   0.1387   0.02626   0.01614  -0.0065   0.6999   0.8399
   0.000   0.1695   0.02622   0.01599  -0.0064   0.6820   0.8543
   0.250   0.2111   0.02627   0.01594  -0.0081   0.6628   0.8641
   0.500   0.2425   0.02626   0.01580  -0.0082   0.6446   0.8780
   0.750   0.2834   0.02632   0.01575  -0.0101   0.6248   0.8882
   1.000   0.3185   0.02639   0.01572  -0.0112   0.6050   0.9003
   1.250   0.3529   0.02648   0.01571  -0.0123   0.5855   0.9128
   1.500   0.3937   0.02656   0.01570  -0.0147   0.5653   0.9227
   1.750   0.4273   0.02668   0.01573  -0.0158   0.5465   0.9352
   2.000   0.4664   0.02680   0.01575  -0.0181   0.5270   0.9457
   2.250   0.5045   0.02693   0.01578  -0.0203   0.5082   0.9563
   2.500   0.5410   0.02709   0.01586  -0.0222   0.4905   0.9673
   2.750   0.5805   0.02723   0.01590  -0.0248   0.4727   0.9773
   3.000   0.6205   0.02737   0.01593  -0.0276   0.4561   0.9865
   3.250   0.6601   0.02756   0.01606  -0.0305   0.4397   0.9959
   3.500   0.6867   0.02783   0.01631  -0.0310   0.4253   1.0000
   3.750   0.7030   0.02807   0.01646  -0.0294   0.4146   1.0000
   4.000   0.7179   0.02840   0.01678  -0.0276   0.4034   1.0000
   4.250   0.7337   0.02874   0.01705  -0.0259   0.3938   1.0000
   4.500   0.7482   0.02913   0.01744  -0.0240   0.3837   1.0000
   4.750   0.7641   0.02952   0.01774  -0.0223   0.3753   1.0000
   5.000   0.7777   0.03002   0.01829  -0.0203   0.3661   1.0000
   5.250   0.7952   0.03039   0.01853  -0.0186   0.3590   1.0000
   5.500   0.8067   0.03104   0.01928  -0.0164   0.3504   1.0000
   5.750   0.8219   0.03152   0.01972  -0.0144   0.3431   1.0000
   6.000   0.8372   0.03209   0.02026  -0.0126   0.3364   1.0000
   6.250   0.8484   0.03281   0.02107  -0.0102   0.3291   1.0000
   6.500   0.8649   0.03333   0.02152  -0.0085   0.3228   1.0000
   6.750   0.8776   0.03407   0.02228  -0.0063   0.3165   1.0000
   7.000   0.8878   0.03490   0.02321  -0.0039   0.3099   1.0000
   7.250   0.9044   0.03547   0.02373  -0.0022   0.3041   1.0000
   7.500   0.9165   0.03630   0.02458   0.0000   0.2983   1.0000
   7.750   0.9233   0.03730   0.02572   0.0028   0.2920   1.0000
   8.000   0.9384   0.03795   0.02634   0.0046   0.2863   1.0000
   8.250   0.9516   0.03876   0.02713   0.0066   0.2808   1.0000
   8.500   0.9526   0.04002   0.02856   0.0099   0.2747   1.0000
   8.750   0.9654   0.04079   0.02933   0.0118   0.2691   1.0000
   9.000   0.9829   0.04147   0.02994   0.0132   0.2639   1.0000
   9.250   0.9754   0.04318   0.03189   0.0171   0.2584   1.0000
   9.500   0.9815   0.04432   0.03309   0.0195   0.2530   1.0000
   9.750   1.0069   0.04470   0.03335   0.0199   0.2481   1.0000
  10.000   0.9903   0.04687   0.03574   0.0244   0.2437   1.0000
  10.250   0.9745   0.04913   0.03818   0.0282   0.2391   1.0000
  10.500   0.9806   0.05047   0.03955   0.0300   0.2345   1.0000
  10.750   1.0095   0.05071   0.03967   0.0301   0.2301   1.0000
  11.000   0.9576   0.05592   0.04524   0.0341   0.2264   1.0000
  11.250   0.8904   0.06433   0.05394   0.0347   0.2217   1.0000
  11.500   0.8927   0.06671   0.05635   0.0350   0.2173   1.0000
  11.750   0.9522   0.06330   0.05280   0.0365   0.2138   1.0000
  12.000   0.7374   0.09584   0.08577   0.0239   0.2006   1.0000
  12.250   0.7665   0.09433   0.08426   0.0257   0.1987   1.0000
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