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NACA 66(2)-215 (naca662215-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 66(2)-215 (naca662215-il)
Reynolds number: 100,000
Max Cl/Cd: 28.42 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca662215-il-100000-n5.txt
Download as CSV file: xf-naca662215-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(2)-215                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.5077   0.10362   0.09826  -0.0650   1.0000   0.0360
 -13.000  -0.5186   0.09675   0.09141  -0.0684   1.0000   0.0357
 -12.750  -0.5359   0.08955   0.08420  -0.0725   1.0000   0.0353
 -12.500  -0.5584   0.08304   0.07767  -0.0758   1.0000   0.0350
 -12.250  -0.5859   0.07763   0.07221  -0.0773   1.0000   0.0348
 -12.000  -0.6145   0.07405   0.06860  -0.0762   1.0000   0.0346
 -11.750  -0.6414   0.07088   0.06536  -0.0747   0.9970   0.0344
 -11.500  -0.6577   0.06577   0.06000  -0.0770   0.9874   0.0343
 -11.250  -0.6705   0.06126   0.05519  -0.0784   0.9797   0.0342
 -11.000  -0.6776   0.05724   0.05085  -0.0793   0.9731   0.0342
 -10.750  -0.6833   0.05378   0.04705  -0.0789   0.9651   0.0342
 -10.500  -0.6870   0.05079   0.04371  -0.0775   0.9570   0.0343
 -10.250  -0.6842   0.04786   0.04039  -0.0764   0.9509   0.0346
 -10.000  -0.6829   0.04553   0.03765  -0.0742   0.9437   0.0351
  -9.750  -0.6773   0.04340   0.03504  -0.0723   0.9378   0.0359
  -9.500  -0.6655   0.04113   0.03240  -0.0711   0.9333   0.0365
  -9.250  -0.6518   0.03916   0.03026  -0.0699   0.9277   0.0372
  -9.000  -0.6316   0.03726   0.02814  -0.0696   0.9238   0.0378
  -8.750  -0.6070   0.03545   0.02609  -0.0699   0.9211   0.0384
  -8.500  -0.5844   0.03394   0.02436  -0.0696   0.9175   0.0392
  -8.250  -0.5620   0.03262   0.02288  -0.0691   0.9135   0.0401
  -8.000  -0.5366   0.03145   0.02155  -0.0692   0.9104   0.0419
  -7.750  -0.5078   0.03031   0.02020  -0.0697   0.9080   0.0438
  -7.500  -0.4746   0.02907   0.01880  -0.0709   0.9063   0.0451
  -7.250  -0.4409   0.02773   0.01751  -0.0725   0.9050   0.0467
  -7.000  -0.4197   0.02699   0.01678  -0.0718   0.9016   0.0485
  -6.750  -0.4034   0.02646   0.01621  -0.0702   0.8971   0.0510
  -6.500  -0.3840   0.02589   0.01556  -0.0691   0.8935   0.0536
  -6.250  -0.3658   0.02519   0.01482  -0.0679   0.8905   0.0558
  -6.000  -0.3485   0.02459   0.01419  -0.0666   0.8879   0.0584
  -5.750  -0.3434   0.02443   0.01401  -0.0630   0.8825   0.0612
  -5.500  -0.3297   0.02415   0.01362  -0.0608   0.8788   0.0655
  -5.250  -0.3146   0.02366   0.01316  -0.0590   0.8759   0.0718
  -5.000  -0.2957   0.02319   0.01268  -0.0577   0.8737   0.0811
  -4.750  -0.2864   0.02282   0.01245  -0.0548   0.8697   0.1015
  -4.500  -0.2881   0.02221   0.01232  -0.0502   0.8644   0.1807
  -4.250  -0.2944   0.02107   0.01202  -0.0449   0.8603   0.3400
  -4.000  -0.2776   0.02110   0.01365  -0.0406   0.8588   0.6255
  -3.750  -0.2666   0.02148   0.01395  -0.0371   0.8565   0.6910
  -3.500  -0.2732   0.02228   0.01474  -0.0303   0.8506   0.7215
  -3.250  -0.2490   0.02395   0.01638  -0.0271   0.8481   0.7573
  -3.000  -0.2295   0.02500   0.01735  -0.0240   0.8456   0.7814
  -2.750  -0.1901   0.02612   0.01837  -0.0244   0.8448   0.7961
  -2.500  -0.1571   0.02645   0.01857  -0.0251   0.8436   0.8016
  -2.250  -0.1291   0.02654   0.01855  -0.0253   0.8421   0.8060
  -2.000  -0.1275   0.02643   0.01836  -0.0212   0.8385   0.8146
  -1.500  -0.1054   0.02690   0.01872  -0.0157   0.8304   0.8241
  -1.250  -0.0941   0.02671   0.01846  -0.0133   0.8274   0.8307
  -1.000  -0.0629   0.02675   0.01843  -0.0141   0.8260   0.8330
  -0.750  -0.0324   0.02676   0.01837  -0.0150   0.8246   0.8356
  -0.500  -0.0616   0.02689   0.01851  -0.0053   0.8156   0.8443
  -0.250  -0.0407   0.02687   0.01844  -0.0045   0.8127   0.8476
   0.000  -0.0115   0.02688   0.01841  -0.0052   0.8107   0.8497
   0.250   0.0195   0.02685   0.01835  -0.0061   0.8092   0.8519
   0.750   0.0226   0.02689   0.01836   0.0019   0.7975   0.8618
   1.000   0.0523   0.02691   0.01837   0.0012   0.7951   0.8635
   1.250   0.0848   0.02688   0.01834   0.0000   0.7933   0.8651
   1.750   0.1082   0.02714   0.01862   0.0045   0.7817   0.8716
   2.000   0.1368   0.02706   0.01856   0.0040   0.7789   0.8743
   2.250   0.1689   0.02693   0.01846   0.0029   0.7769   0.8769
   2.500   0.1696   0.02730   0.01886   0.0069   0.7679   0.8806
   2.750   0.1984   0.02729   0.01891   0.0064   0.7643   0.8825
   3.000   0.2322   0.02719   0.01887   0.0051   0.7620   0.8843
   3.500   0.2664   0.02737   0.01918   0.0078   0.7487   0.8916
   3.750   0.3022   0.02713   0.01902   0.0064   0.7461   0.8938
   4.000   0.3116   0.02741   0.01939   0.0090   0.7357   0.8977
   4.500   0.3627   0.02725   0.01944   0.0094   0.7227   0.9038
   4.750   0.3941   0.02690   0.01922   0.0089   0.7172   0.9065
   5.250   0.4564   0.02568   0.01828   0.0089   0.7001   0.9117
   5.500   0.4865   0.02423   0.01695   0.0102   0.6821   0.9146
   5.750   0.4970   0.02350   0.01631   0.0138   0.6546   0.9208
   6.000   0.4976   0.02369   0.01660   0.0178   0.6157   0.9280
   6.250   0.5689   0.02002   0.01213   0.0163   0.4568   0.9259
   6.500   0.5700   0.02103   0.01241   0.0203   0.3334   0.9322
   6.750   0.5682   0.02245   0.01312   0.0238   0.2122   0.9395
   7.000   0.5767   0.02394   0.01389   0.0256   0.1025   0.9452
   7.250   0.5926   0.02488   0.01466   0.0266   0.0767   0.9515
   7.500   0.6139   0.02578   0.01554   0.0266   0.0657   0.9564
   7.750   0.6335   0.02670   0.01647   0.0267   0.0593   0.9630
   8.000   0.6568   0.02765   0.01755   0.0261   0.0550   0.9685
   8.250   0.6779   0.02873   0.01866   0.0257   0.0513   0.9753
   8.500   0.7010   0.02977   0.01979   0.0250   0.0480   0.9825
   8.750   0.7234   0.03073   0.02084   0.0246   0.0455   0.9940
   9.000   0.7394   0.03166   0.02178   0.0255   0.0439   1.0000
   9.250   0.7559   0.03267   0.02273   0.0264   0.0420   1.0000
   9.500   0.7787   0.03372   0.02383   0.0267   0.0403   1.0000
   9.750   0.8029   0.03478   0.02503   0.0267   0.0383   1.0000
  10.000   0.8306   0.03606   0.02641   0.0264   0.0371   1.0000
  10.250   0.8589   0.03752   0.02798   0.0259   0.0360   1.0000
  10.500   0.8861   0.03912   0.02969   0.0254   0.0350   1.0000
  10.750   0.9131   0.04102   0.03165   0.0246   0.0338   1.0000
  11.000   0.9327   0.04315   0.03401   0.0249   0.0328   1.0000
  11.250   0.9431   0.04507   0.03628   0.0262   0.0318   1.0000
  11.500   0.9537   0.04735   0.03886   0.0273   0.0314   1.0000
  11.750   0.9595   0.04983   0.04165   0.0288   0.0310   1.0000
  12.000   0.9611   0.05247   0.04459   0.0305   0.0307   1.0000
  12.250   0.9586   0.05529   0.04770   0.0323   0.0305   1.0000
  12.500   0.9526   0.05827   0.05098   0.0341   0.0304   1.0000
  12.750   0.9426   0.06153   0.05452   0.0358   0.0303   1.0000
  13.000   0.9289   0.06513   0.05839   0.0372   0.0302   1.0000
  13.250   0.9133   0.06901   0.06253   0.0382   0.0303   1.0000
  13.500   0.8945   0.07337   0.06714   0.0386   0.0303   1.0000
  13.750   0.8724   0.07836   0.07236   0.0382   0.0304   1.0000
  14.000   0.8484   0.08400   0.07822   0.0370   0.0305   1.0000
  14.250   0.8222   0.09053   0.08493   0.0344   0.0307   1.0000
  14.500   0.7917   0.09881   0.09340   0.0301   0.0310   1.0000
  14.750   0.7598   0.10909   0.10383   0.0238   0.0314   1.0000
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