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

NACA 2418 (naca2418-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 2418 (naca2418-il)
Reynolds number: 500,000
Max Cl/Cd: 83.4 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2418-il-500000.txt
Download as CSV file: xf-naca2418-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2418                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.0986   0.09306   0.08854  -0.0570   1.0000   0.0432
 -19.500  -1.1082   0.08809   0.08344  -0.0597   1.0000   0.0435
 -19.250  -1.1171   0.08326   0.07848  -0.0623   1.0000   0.0438
 -19.000  -1.1177   0.08016   0.07535  -0.0633   1.0000   0.0442
 -18.750  -1.1165   0.07729   0.07246  -0.0643   1.0000   0.0447
 -18.500  -1.1183   0.07387   0.06900  -0.0658   1.0000   0.0451
 -18.250  -1.1202   0.07041   0.06549  -0.0673   1.0000   0.0455
 -18.000  -1.1226   0.06688   0.06191  -0.0689   1.0000   0.0459
 -17.750  -1.1251   0.06338   0.05834  -0.0704   1.0000   0.0463
 -17.500  -1.1277   0.05994   0.05482  -0.0718   1.0000   0.0468
 -17.250  -1.1298   0.05658   0.05137  -0.0732   1.0000   0.0472
 -17.000  -1.1315   0.05334   0.04803  -0.0745   1.0000   0.0478
 -16.750  -1.1324   0.05025   0.04483  -0.0756   1.0000   0.0483
 -16.500  -1.1320   0.04734   0.04179  -0.0767   1.0000   0.0487
 -16.250  -1.1331   0.04459   0.03902  -0.0771   1.0000   0.0493
 -16.000  -1.1333   0.04190   0.03631  -0.0777   1.0000   0.0499
 -15.750  -1.1314   0.03944   0.03379  -0.0781   1.0000   0.0505
 -15.500  -1.1281   0.03718   0.03148  -0.0785   1.0000   0.0511
 -15.250  -1.1240   0.03511   0.02934  -0.0785   1.0000   0.0518
 -15.000  -1.1190   0.03323   0.02739  -0.0784   1.0000   0.0525
 -14.750  -1.1132   0.03154   0.02562  -0.0779   1.0000   0.0533
 -14.500  -1.1064   0.03009   0.02407  -0.0772   1.0000   0.0540
 -14.250  -1.1074   0.02831   0.02227  -0.0757   1.0000   0.0549
 -14.000  -1.1069   0.02693   0.02088  -0.0736   1.0000   0.0557
 -13.750  -1.1060   0.02587   0.01979  -0.0710   1.0000   0.0566
 -13.500  -1.1065   0.02500   0.01888  -0.0678   1.0000   0.0575
 -13.250  -1.1098   0.02430   0.01812  -0.0637   1.0000   0.0585
 -13.000  -1.1165   0.02374   0.01750  -0.0587   1.0000   0.0593
 -12.750  -1.1283   0.02333   0.01702  -0.0525   1.0000   0.0599
 -12.500  -1.1523   0.02289   0.01656  -0.0441   1.0000   0.0604
 -12.250  -1.1405   0.02214   0.01582  -0.0423   0.9986   0.0619
 -12.000  -1.1108   0.02149   0.01514  -0.0436   0.9961   0.0641
 -11.750  -1.0796   0.02089   0.01448  -0.0450   0.9939   0.0664
 -11.500  -1.0501   0.02013   0.01375  -0.0463   0.9917   0.0691
 -11.250  -1.0207   0.01963   0.01321  -0.0472   0.9882   0.0719
 -11.000  -0.9906   0.01898   0.01257  -0.0483   0.9851   0.0751
 -10.750  -0.9572   0.01852   0.01211  -0.0499   0.9829   0.0786
 -10.500  -0.9231   0.01798   0.01156  -0.0517   0.9811   0.0823
 -10.250  -0.8895   0.01754   0.01113  -0.0533   0.9789   0.0861
 -10.000  -0.8610   0.01709   0.01065  -0.0537   0.9739   0.0897
  -9.750  -0.8253   0.01658   0.01017  -0.0557   0.9710   0.0939
  -9.500  -0.7862   0.01614   0.00970  -0.0582   0.9691   0.0982
  -9.250  -0.7489   0.01561   0.00921  -0.0605   0.9675   0.1030
  -9.000  -0.7173   0.01533   0.00888  -0.0613   0.9636   0.1070
  -8.750  -0.6905   0.01481   0.00841  -0.0614   0.9581   0.1116
  -8.500  -0.6580   0.01445   0.00804  -0.0624   0.9547   0.1161
  -8.250  -0.6260   0.01400   0.00760  -0.0634   0.9517   0.1210
  -8.000  -0.6036   0.01369   0.00731  -0.0623   0.9438   0.1256
  -7.750  -0.5748   0.01337   0.00696  -0.0624   0.9385   0.1305
  -7.500  -0.5485   0.01298   0.00662  -0.0621   0.9331   0.1365
  -7.000  -0.4975   0.01235   0.00600  -0.0610   0.9189   0.1496
  -6.750  -0.4730   0.01210   0.00575  -0.0603   0.9105   0.1570
  -6.500  -0.4474   0.01179   0.00547  -0.0597   0.9029   0.1663
  -6.250  -0.4220   0.01150   0.00522  -0.0592   0.8948   0.1765
  -6.000  -0.3966   0.01124   0.00498  -0.0586   0.8858   0.1882
  -5.750  -0.3700   0.01101   0.00477  -0.0582   0.8777   0.2013
  -5.500  -0.3442   0.01080   0.00459  -0.0577   0.8678   0.2150
  -5.250  -0.3176   0.01059   0.00441  -0.0573   0.8590   0.2287
  -5.000  -0.2915   0.01040   0.00425  -0.0568   0.8484   0.2414
  -4.750  -0.2641   0.01027   0.00409  -0.0566   0.8390   0.2534
  -4.500  -0.2377   0.01011   0.00395  -0.0561   0.8279   0.2655
  -4.250  -0.2108   0.00997   0.00381  -0.0558   0.8175   0.2768
  -4.000  -0.1836   0.00987   0.00368  -0.0555   0.8063   0.2880
  -3.750  -0.1571   0.00972   0.00356  -0.0551   0.7951   0.2999
  -3.500  -0.1299   0.00964   0.00343  -0.0548   0.7837   0.3115
  -3.250  -0.1033   0.00951   0.00333  -0.0544   0.7717   0.3246
  -3.000  -0.0766   0.00941   0.00322  -0.0541   0.7602   0.3381
  -2.750  -0.0499   0.00931   0.00313  -0.0537   0.7477   0.3529
  -2.500  -0.0232   0.00922   0.00306  -0.0533   0.7357   0.3702
  -2.250   0.0032   0.00914   0.00297  -0.0529   0.7235   0.3894
  -2.000   0.0295   0.00902   0.00292  -0.0525   0.7108   0.4111
  -1.750   0.0555   0.00892   0.00287  -0.0520   0.6988   0.4359
  -1.500   0.0817   0.00883   0.00283  -0.0516   0.6861   0.4624
  -1.250   0.1080   0.00876   0.00281  -0.0511   0.6736   0.4899
  -1.000   0.1336   0.00870   0.00279  -0.0505   0.6610   0.5197
  -0.750   0.1597   0.00863   0.00280  -0.0500   0.6482   0.5509
  -0.500   0.1858   0.00860   0.00281  -0.0496   0.6362   0.5778
  -0.250   0.2118   0.00859   0.00281  -0.0490   0.6237   0.6017
   0.000   0.2382   0.00856   0.00284  -0.0486   0.6112   0.6248
   0.250   0.2641   0.00857   0.00286  -0.0480   0.5985   0.6471
   0.500   0.2899   0.00859   0.00289  -0.0474   0.5850   0.6692
   0.750   0.3162   0.00859   0.00294  -0.0469   0.5736   0.6918
   1.250   0.3685   0.00864   0.00306  -0.0459   0.5532   0.7374
   1.500   0.3941   0.00870   0.00313  -0.0452   0.5435   0.7612
   1.750   0.4206   0.00871   0.00322  -0.0448   0.5348   0.7849
   2.000   0.4463   0.00879   0.00332  -0.0441   0.5256   0.8073
   2.250   0.4724   0.00885   0.00342  -0.0435   0.5168   0.8297
   2.500   0.4979   0.00893   0.00353  -0.0428   0.5076   0.8515
   2.750   0.5233   0.00903   0.00366  -0.0420   0.4994   0.8716
   3.000   0.5490   0.00912   0.00379  -0.0413   0.4907   0.8895
   3.250   0.5740   0.00929   0.00393  -0.0404   0.4821   0.9064
   3.500   0.6003   0.00939   0.00407  -0.0399   0.4730   0.9219
   3.750   0.6261   0.00958   0.00421  -0.0392   0.4640   0.9361
   4.000   0.6534   0.00971   0.00436  -0.0389   0.4548   0.9497
   4.250   0.6846   0.00995   0.00454  -0.0394   0.4430   0.9609
   4.500   0.7213   0.01017   0.00473  -0.0411   0.4298   0.9700
   4.750   0.7586   0.01041   0.00493  -0.0431   0.4181   0.9776
   5.250   0.8392   0.01088   0.00530  -0.0485   0.3934   0.9846
   5.500   0.8772   0.01112   0.00549  -0.0507   0.3809   0.9890
   5.750   0.9139   0.01141   0.00570  -0.0528   0.3680   0.9930
   6.000   0.9532   0.01164   0.00589  -0.0554   0.3541   0.9959
   6.250   0.9914   0.01190   0.00611  -0.0578   0.3402   0.9991
   6.500   1.0116   0.01213   0.00628  -0.0566   0.3283   1.0000
   6.750   1.0231   0.01233   0.00643  -0.0535   0.3168   1.0000
   7.000   1.0351   0.01251   0.00658  -0.0506   0.3061   1.0000
   7.250   1.0446   0.01277   0.00677  -0.0471   0.2954   1.0000
   7.500   1.0570   0.01297   0.00695  -0.0442   0.2845   1.0000
   7.750   1.0682   0.01324   0.00717  -0.0411   0.2741   1.0000
   8.000   1.0773   0.01353   0.00740  -0.0375   0.2633   1.0000
   8.250   1.0889   0.01380   0.00764  -0.0345   0.2529   1.0000
   8.500   1.1010   0.01418   0.00796  -0.0317   0.2428   1.0000
   8.750   1.1163   0.01454   0.00830  -0.0296   0.2330   1.0000
   9.000   1.1321   0.01495   0.00868  -0.0277   0.2240   1.0000
   9.250   1.1475   0.01542   0.00910  -0.0258   0.2148   1.0000
   9.500   1.1647   0.01585   0.00953  -0.0242   0.2061   1.0000
   9.750   1.1790   0.01644   0.01006  -0.0223   0.1969   1.0000
  10.000   1.1969   0.01689   0.01052  -0.0210   0.1882   1.0000
  10.250   1.2118   0.01750   0.01109  -0.0193   0.1794   1.0000
  10.500   1.2270   0.01813   0.01169  -0.0177   0.1699   1.0000
  10.750   1.2421   0.01878   0.01232  -0.0162   0.1609   1.0000
  11.000   1.2550   0.01957   0.01307  -0.0146   0.1521   1.0000
  11.250   1.2680   0.02039   0.01387  -0.0130   0.1435   1.0000
  11.500   1.2810   0.02124   0.01471  -0.0115   0.1360   1.0000
  11.750   1.2910   0.02229   0.01572  -0.0099   0.1290   1.0000
  12.000   1.3039   0.02322   0.01666  -0.0086   0.1228   1.0000
  12.250   1.3128   0.02442   0.01785  -0.0070   0.1172   1.0000
  12.500   1.3247   0.02548   0.01893  -0.0058   0.1120   1.0000
  12.750   1.3315   0.02693   0.02036  -0.0044   0.1070   1.0000
  13.000   1.3429   0.02809   0.02157  -0.0034   0.1024   1.0000
  13.250   1.3485   0.02973   0.02321  -0.0021   0.0980   1.0000
  13.500   1.3582   0.03111   0.02463  -0.0012   0.0938   1.0000
  13.750   1.3636   0.03288   0.02641  -0.0002   0.0897   1.0000
  14.000   1.3702   0.03461   0.02818   0.0006   0.0861   1.0000
  14.250   1.3756   0.03649   0.03009   0.0014   0.0825   1.0000
  14.500   1.3774   0.03876   0.03238   0.0021   0.0795   1.0000
  14.750   1.3835   0.04072   0.03440   0.0025   0.0765   1.0000
  15.000   1.3848   0.04318   0.03689   0.0030   0.0740   1.0000
  15.250   1.3846   0.04586   0.03961   0.0033   0.0718   1.0000
  15.500   1.3882   0.04823   0.04205   0.0035   0.0696   1.0000
  15.750   1.3881   0.05105   0.04492   0.0035   0.0676   1.0000
  16.000   1.3834   0.05441   0.04831   0.0035   0.0660   1.0000
  16.250   1.3836   0.05730   0.05128   0.0034   0.0644   1.0000
  16.500   1.3845   0.06018   0.05424   0.0031   0.0629   1.0000
  16.750   1.3828   0.06339   0.05751   0.0028   0.0615   1.0000
  17.000   1.3781   0.06696   0.06112   0.0023   0.0603   1.0000
  17.250   1.3705   0.07091   0.06511   0.0018   0.0591   1.0000
  17.500   1.3706   0.07405   0.06835   0.0012   0.0581   1.0000
  17.750   1.3694   0.07735   0.07173   0.0006   0.0571   1.0000
  18.000   1.3671   0.08080   0.07524  -0.0001   0.0562   1.0000
  18.250   1.3635   0.08444   0.07894  -0.0009   0.0553   1.0000
  18.500   1.3596   0.08812   0.08267  -0.0018   0.0545   1.0000
<< Back to NACA 2418 (naca2418-il)

Polar data table (+)

Polar graphs


<< Back to NACA 2418 (naca2418-il)