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NACA 66-018 (naca66-018-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 66-018 (naca66-018-il)
Reynolds number: 100,000
Max Cl/Cd: 31.61 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca66-018-il-100000.txt
Download as CSV file: xf-naca66-018-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66-018                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6406   0.09431   0.08930  -0.0734   1.0000   0.1137
 -13.250  -0.7033   0.08888   0.08379  -0.0736   1.0000   0.1134
 -13.000  -0.7630   0.07726   0.07178  -0.0706   1.0000   0.0831
 -12.750  -0.8003   0.07595   0.07044  -0.0650   1.0000   0.0827
 -12.500  -0.8333   0.07430   0.06873  -0.0598   1.0000   0.0818
 -12.250  -0.8685   0.07241   0.06673  -0.0542   1.0000   0.0808
 -12.000  -0.9056   0.07049   0.06467  -0.0482   1.0000   0.0797
 -11.750  -0.9470   0.06864   0.06262  -0.0412   1.0000   0.0782
 -11.500  -1.0139   0.06749   0.06098  -0.0305   0.9968   0.0758
 -11.250  -1.0132   0.06461   0.05779  -0.0284   0.9936   0.0730
 -11.000  -1.0125   0.06109   0.05404  -0.0262   0.9909   0.0717
 -10.750  -1.0136   0.05797   0.05063  -0.0235   0.9881   0.0703
 -10.500  -1.0144   0.05502   0.04732  -0.0205   0.9856   0.0689
 -10.250  -1.0107   0.05226   0.04413  -0.0179   0.9836   0.0678
 -10.000  -1.0067   0.05013   0.04168  -0.0149   0.9818   0.0677
  -9.750  -0.9978   0.04835   0.03967  -0.0126   0.9798   0.0687
  -9.500  -0.9832   0.04649   0.03754  -0.0111   0.9777   0.0694
  -9.250  -0.9628   0.04467   0.03543  -0.0104   0.9760   0.0703
  -9.000  -0.9337   0.04278   0.03327  -0.0110   0.9749   0.0711
  -8.750  -0.8905   0.04084   0.03106  -0.0138   0.9739   0.0727
  -8.500  -0.7891   0.03794   0.02821  -0.0259   0.9737   0.0791
  -8.250  -0.7452   0.03703   0.02724  -0.0284   0.9728   0.0841
  -8.000  -0.7018   0.03604   0.02642  -0.0306   0.9721   0.0906
  -7.750  -0.6868   0.03552   0.02590  -0.0290   0.9710   0.0972
  -7.500  -0.6840   0.03483   0.02531  -0.0254   0.9700   0.1032
  -7.250  -0.6847   0.03428   0.02476  -0.0213   0.9693   0.1097
  -7.000  -0.6888   0.03354   0.02411  -0.0167   0.9683   0.1177
  -6.750  -0.6956   0.03276   0.02343  -0.0117   0.9676   0.1312
  -6.500  -0.7092   0.03188   0.02276  -0.0055   0.9684   0.1525
  -6.250  -0.7315   0.03073   0.02206   0.0021   0.9703   0.1979
  -6.000  -0.7626   0.02970   0.02135   0.0115   0.9728   0.2399
  -5.750  -0.7961   0.02915   0.02073   0.0222   0.9788   0.2390
  -5.500  -0.8326   0.02844   0.01989   0.0338   0.9904   0.2282
  -5.250  -0.8647   0.02736   0.01879   0.0446   1.0000   0.2333
  -5.000  -0.8842   0.02732   0.02164   0.0569   1.0000   0.6416
  -4.750  -0.8940   0.02755   0.02172   0.0642   1.0000   0.6926
  -4.500  -0.4462   0.05036   0.04352   0.0102   0.9670   0.7678
  -4.250  -0.4423   0.05063   0.04371   0.0139   0.9681   0.7828
  -4.000  -0.3798   0.05127   0.04419   0.0082   0.9669   0.7907
  -3.750  -0.3646   0.05137   0.04421   0.0098   0.9672   0.8037
  -3.500  -0.3606   0.05153   0.04431   0.0132   0.9687   0.8182
  -3.250  -0.3128   0.05167   0.04433   0.0093   0.9681   0.8272
  -3.000  -0.2881   0.05172   0.04431   0.0091   0.9678   0.8402
  -2.750  -0.2793   0.05182   0.04436   0.0115   0.9695   0.8538
  -2.500  -0.2480   0.05184   0.04431   0.0099   0.9697   0.8647
  -2.250  -0.0258   0.05213   0.04445  -0.0234   0.9557   0.9504
  -2.000   0.0131   0.05153   0.04381  -0.0275   0.9546   0.9673
  -1.750   0.0535   0.05114   0.04338  -0.0321   0.9526   0.9832
  -1.250   0.1409   0.04942   0.04161  -0.0431   0.9487   1.0000
  -1.000   0.1567   0.04940   0.04158  -0.0429   0.9469   1.0000
  -0.750   0.1671   0.04948   0.04166  -0.0417   0.9453   1.0000
  -0.500   0.1679   0.04955   0.04175  -0.0385   0.9435   1.0000
  -0.250  -0.0318   0.05143   0.04364   0.0028   0.9696   0.9601
   0.000   0.0018   0.05122   0.04344  -0.0003   0.9666   0.9676
   0.250   0.0326   0.05143   0.04364  -0.0029   0.9599   0.9693
   0.500   0.0570   0.05128   0.04351  -0.0043   0.9548   0.9741
   0.750   0.0864   0.05135   0.04360  -0.0066   0.9484   0.9761
   1.250   0.1377   0.05139   0.04368  -0.0091   0.9256   0.9763
   1.500   0.1846   0.05136   0.04370  -0.0141   0.9101   0.9808
   1.750   0.1228   0.05199   0.04431   0.0002   0.9200   0.9643
   2.000   0.1884   0.05172   0.04409  -0.0072   0.8908   0.9693
   2.250   0.2135   0.05172   0.04413  -0.0078   0.8772   0.9687
   2.500   0.2512   0.05184   0.04431  -0.0105   0.8649   0.9700
   2.750   0.2778   0.05178   0.04432  -0.0112   0.8535   0.9694
   3.000   0.2878   0.05169   0.04428  -0.0091   0.8400   0.9678
   3.250   0.3135   0.05165   0.04431  -0.0094   0.8275   0.9680
   3.500   0.3591   0.05149   0.04426  -0.0129   0.8179   0.9687
   3.750   0.3625   0.05137   0.04420  -0.0095   0.8037   0.9672
   4.000   0.3797   0.05125   0.04417  -0.0082   0.7909   0.9668
   4.250   0.4393   0.05062   0.04371  -0.0134   0.7825   0.9679
   4.500   0.4446   0.05033   0.04349  -0.0099   0.7676   0.9668
   4.750   0.4585   0.05004   0.04330  -0.0078   0.7540   0.9666
   5.000   0.4947   0.04924   0.04266  -0.0088   0.7429   0.9665
   5.250   0.8645   0.02735   0.01878  -0.0446   0.2328   1.0000
   5.500   0.8302   0.02847   0.01991  -0.0333   0.2279   0.9897
   5.750   0.7964   0.02913   0.02071  -0.0223   0.2390   0.9789
   6.000   0.7625   0.02967   0.02133  -0.0115   0.2416   0.9726
   6.250   0.7321   0.03069   0.02203  -0.0022   0.1988   0.9703
   6.500   0.7087   0.03189   0.02276   0.0056   0.1512   0.9684
   6.750   0.6951   0.03277   0.02343   0.0118   0.1304   0.9676
   7.000   0.6888   0.03351   0.02407   0.0168   0.1180   0.9682
   7.250   0.6846   0.03426   0.02474   0.0213   0.1096   0.9693
   7.500   0.6839   0.03483   0.02530   0.0254   0.1028   0.9700
   7.750   0.6868   0.03550   0.02587   0.0290   0.0970   0.9710
   8.000   0.7028   0.03604   0.02641   0.0305   0.0905   0.9721
   8.250   0.7460   0.03702   0.02722   0.0283   0.0840   0.9728
   8.500   0.7932   0.03799   0.02826   0.0253   0.0793   0.9737
   8.750   0.8944   0.04094   0.03114   0.0131   0.0727   0.9740
   9.000   0.9344   0.04277   0.03324   0.0109   0.0711   0.9749
   9.250   0.9632   0.04466   0.03541   0.0104   0.0703   0.9760
   9.500   0.9822   0.04645   0.03747   0.0113   0.0691   0.9777
   9.750   0.9966   0.04814   0.03941   0.0127   0.0678   0.9797
  10.000   1.0062   0.05009   0.04164   0.0150   0.0674   0.9818
  10.250   1.0106   0.05223   0.04411   0.0179   0.0677   0.9837
  10.500   1.0144   0.05504   0.04733   0.0205   0.0688   0.9857
  10.750   1.0141   0.05798   0.05064   0.0234   0.0701   0.9882
  11.000   1.0123   0.06104   0.05399   0.0262   0.0714   0.9910
  11.250   1.0168   0.06462   0.05776   0.0278   0.0728   0.9935
  11.500   1.0134   0.06742   0.06091   0.0306   0.0755   0.9969
  11.750   0.9483   0.06852   0.06248   0.0410   0.0778   1.0000
  12.000   0.9073   0.07032   0.06449   0.0481   0.0793   1.0000
  12.250   0.8687   0.07232   0.06664   0.0543   0.0805   1.0000
  12.500   0.8348   0.07417   0.06858   0.0597   0.0816   1.0000
  12.750   0.8008   0.07564   0.07012   0.0651   0.0821   1.0000
  13.000   0.7641   0.07690   0.07141   0.0707   0.0826   1.0000
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