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NACA 66(2)-415 (naca662415-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 66(2)-415 (naca662415-il)
Reynolds number: 100,000
Max Cl/Cd: 32.73 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca662415-il-100000-n5.txt
Download as CSV file: xf-naca662415-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(2)-415                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.4008   0.13983   0.13465  -0.0538   1.0000   0.0625
 -13.250  -0.4045   0.13722   0.13208  -0.0539   0.9987   0.0643
 -13.000  -0.4159   0.13100   0.12592  -0.0625   0.9927   0.0681
 -12.500  -0.4180   0.11069   0.10553  -0.0718   0.9862   0.0385
 -12.250  -0.4121   0.10595   0.10077  -0.0748   0.9825   0.0381
 -12.000  -0.4095   0.10043   0.09525  -0.0787   0.9786   0.0377
 -11.750  -0.4105   0.09335   0.08816  -0.0842   0.9754   0.0373
 -11.500  -0.4218   0.08380   0.07857  -0.0922   0.9707   0.0369
 -11.250  -0.4404   0.07519   0.06984  -0.0998   0.9655   0.0366
 -11.000  -0.4579   0.06849   0.06295  -0.1052   0.9605   0.0362
 -10.750  -0.4762   0.06350   0.05773  -0.1075   0.9528   0.0363
 -10.500  -0.4909   0.05923   0.05320  -0.1086   0.9461   0.0363
 -10.250  -0.5071   0.05616   0.04987  -0.1069   0.9373   0.0366
 -10.000  -0.5193   0.05350   0.04693  -0.1044   0.9299   0.0368
  -9.750  -0.5273   0.05098   0.04411  -0.1017   0.9227   0.0370
  -9.500  -0.5261   0.04800   0.04074  -0.1002   0.9185   0.0371
  -9.250  -0.5311   0.04606   0.03852  -0.0964   0.9110   0.0372
  -9.000  -0.5265   0.04369   0.03577  -0.0942   0.9060   0.0374
  -8.750  -0.5150   0.04123   0.03288  -0.0929   0.9028   0.0378
  -8.500  -0.5113   0.03968   0.03095  -0.0896   0.8974   0.0382
  -8.250  -0.5031   0.03817   0.02910  -0.0870   0.8926   0.0390
  -8.000  -0.4842   0.03643   0.02725  -0.0866   0.8899   0.0401
  -7.750  -0.4619   0.03500   0.02565  -0.0864   0.8877   0.0412
  -7.500  -0.4365   0.03344   0.02387  -0.0865   0.8861   0.0422
  -7.250  -0.4267   0.03261   0.02286  -0.0836   0.8808   0.0427
  -7.000  -0.4072   0.03152   0.02160  -0.0824   0.8773   0.0437
  -6.750  -0.3829   0.03050   0.02040  -0.0821   0.8748   0.0453
  -6.500  -0.3566   0.02962   0.01929  -0.0820   0.8729   0.0471
  -6.250  -0.3282   0.02845   0.01813  -0.0824   0.8715   0.0488
  -6.000  -0.3007   0.02755   0.01723  -0.0827   0.8702   0.0503
  -5.750  -0.2945   0.02733   0.01701  -0.0792   0.8655   0.0514
  -5.500  -0.2828   0.02700   0.01665  -0.0766   0.8616   0.0531
  -5.250  -0.2644   0.02656   0.01614  -0.0753   0.8588   0.0559
  -5.000  -0.2443   0.02597   0.01552  -0.0743   0.8565   0.0587
  -4.750  -0.2227   0.02541   0.01494  -0.0736   0.8547   0.0615
  -4.500  -0.2128   0.02527   0.01475  -0.0707   0.8513   0.0642
  -4.250  -0.2122   0.02540   0.01482  -0.0662   0.8463   0.0671
  -4.000  -0.1978   0.02514   0.01458  -0.0642   0.8434   0.0729
  -3.750  -0.1773   0.02483   0.01424  -0.0632   0.8413   0.0823
  -3.500  -0.1557   0.02428   0.01384  -0.0625   0.8395   0.1076
  -3.250  -0.1463   0.02261   0.01335  -0.0604   0.8377   0.3322
  -3.000  -0.1701   0.02246   0.01387  -0.0520   0.8305   0.4608
  -2.750  -0.1664   0.02300   0.01538  -0.0454   0.8273   0.6896
  -2.500  -0.1490   0.02378   0.01613  -0.0422   0.8250   0.7464
  -2.250  -0.1314   0.02476   0.01706  -0.0384   0.8232   0.7833
  -2.000  -0.1099   0.02588   0.01815  -0.0346   0.8221   0.8078
  -1.750  -0.1202   0.02654   0.01881  -0.0276   0.8156   0.8214
  -1.500  -0.1073   0.02712   0.01933  -0.0239   0.8124   0.8371
  -1.250  -0.0872   0.02731   0.01941  -0.0224   0.8099   0.8475
  -1.000  -0.0601   0.02733   0.01932  -0.0225   0.8080   0.8516
  -0.750  -0.0304   0.02733   0.01922  -0.0231   0.8066   0.8546
  -0.500  -0.0285   0.02760   0.01944  -0.0192   0.8010   0.8604
  -0.250  -0.0146   0.02766   0.01942  -0.0175   0.7968   0.8652
   0.000   0.0108   0.02770   0.01940  -0.0175   0.7942   0.8675
   0.250   0.0394   0.02770   0.01933  -0.0181   0.7922   0.8695
   0.500   0.0703   0.02767   0.01924  -0.0190   0.7906   0.8718
   0.750   0.0727   0.02801   0.01957  -0.0155   0.7838   0.8765
   1.000   0.0948   0.02808   0.01959  -0.0153   0.7799   0.8794
   1.250   0.1231   0.02808   0.01956  -0.0159   0.7773   0.8815
   1.500   0.1547   0.02806   0.01953  -0.0168   0.7753   0.8834
   2.000   0.1868   0.02852   0.01999  -0.0141   0.7642   0.8900
   2.250   0.2164   0.02852   0.02000  -0.0148   0.7614   0.8924
   2.500   0.2497   0.02846   0.01994  -0.0162   0.7593   0.8946
   2.750   0.2578   0.02888   0.02040  -0.0137   0.7511   0.8984
   3.000   0.2844   0.02895   0.02051  -0.0139   0.7471   0.9011
   3.250   0.3170   0.02886   0.02047  -0.0149   0.7445   0.9037
   3.500   0.3520   0.02873   0.02039  -0.0163   0.7427   0.9062
   3.750   0.3562   0.02925   0.02096  -0.0134   0.7319   0.9117
   4.000   0.3898   0.02910   0.02088  -0.0145   0.7291   0.9138
   4.500   0.4336   0.02928   0.02124  -0.0133   0.7155   0.9214
   4.750   0.4702   0.02892   0.02098  -0.0147   0.7126   0.9242
   5.000   0.4817   0.02927   0.02143  -0.0127   0.7015   0.9297
   5.250   0.5175   0.02885   0.02115  -0.0138   0.6980   0.9330
   5.500   0.5317   0.02911   0.02152  -0.0123   0.6868   0.9397
   5.750   0.5702   0.02844   0.02101  -0.0136   0.6826   0.9427
   6.000   0.5898   0.02842   0.02114  -0.0126   0.6699   0.9487
   6.250   0.6174   0.02769   0.02057  -0.0122   0.6557   0.9541
   6.500   0.6502   0.02626   0.01926  -0.0118   0.6360   0.9591
   6.750   0.6620   0.02643   0.01956  -0.0102   0.5962   0.9682
   7.000   0.7286   0.02226   0.01488  -0.0109   0.4883   0.9677
   7.500   0.7514   0.02425   0.01543  -0.0076   0.2517   0.9976
   7.750   0.7525   0.02592   0.01640  -0.0051   0.1470   1.0000
   8.000   0.7605   0.02741   0.01741  -0.0035   0.0875   1.0000
   8.250   0.7736   0.02861   0.01844  -0.0025   0.0702   1.0000
   8.500   0.7885   0.02969   0.01954  -0.0017   0.0623   1.0000
   8.750   0.8028   0.03082   0.02071  -0.0009   0.0566   1.0000
   9.000   0.8174   0.03195   0.02188  -0.0002   0.0525   1.0000
   9.250   0.8296   0.03328   0.02321   0.0008   0.0498   1.0000
   9.500   0.8445   0.03444   0.02448   0.0015   0.0471   1.0000
   9.750   0.8593   0.03565   0.02575   0.0022   0.0444   1.0000
  10.000   0.8735   0.03698   0.02706   0.0029   0.0423   1.0000
  10.250   0.8912   0.03827   0.02838   0.0035   0.0407   1.0000
  10.500   0.9122   0.03943   0.02965   0.0038   0.0390   1.0000
  10.750   0.9334   0.04064   0.03095   0.0040   0.0371   1.0000
  11.000   0.9548   0.04193   0.03226   0.0041   0.0355   1.0000
  11.250   0.9831   0.04348   0.03373   0.0036   0.0339   1.0000
  11.500   1.0086   0.04504   0.03552   0.0035   0.0331   1.0000
  11.750   1.0330   0.04686   0.03760   0.0035   0.0323   1.0000
  12.000   1.0537   0.04896   0.03996   0.0037   0.0315   1.0000
  12.250   1.0684   0.05115   0.04241   0.0043   0.0307   1.0000
  12.500   1.0792   0.05346   0.04496   0.0051   0.0300   1.0000
  12.750   1.0871   0.05563   0.04731   0.0060   0.0292   1.0000
  13.000   1.0928   0.05796   0.04980   0.0069   0.0285   1.0000
  13.250   1.0969   0.06058   0.05261   0.0078   0.0281   1.0000
  13.500   1.0986   0.06348   0.05571   0.0087   0.0277   1.0000
  13.750   1.0966   0.06672   0.05917   0.0096   0.0275   1.0000
  14.000   1.0906   0.07030   0.06299   0.0105   0.0274   1.0000
  14.250   1.0797   0.07416   0.06709   0.0113   0.0273   1.0000
  14.500   1.0647   0.07834   0.07155   0.0119   0.0272   1.0000
  14.750   1.0485   0.08280   0.07628   0.0119   0.0272   1.0000
  15.000   1.0295   0.08779   0.08152   0.0114   0.0272   1.0000
  15.250   1.0105   0.09314   0.08709   0.0102   0.0273   1.0000
  15.500   0.9906   0.09903   0.09320   0.0082   0.0273   1.0000
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