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NACA 66(2)-415 (naca662415-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 66(2)-415 (naca662415-il)
Reynolds number: 200,000
Max Cl/Cd: 55.4 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca662415-il-200000.txt
Download as CSV file: xf-naca662415-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3838   0.12148   0.11790  -0.0642   0.9891   0.0557
 -12.250  -0.3782   0.11627   0.11269  -0.0691   0.9866   0.0585
 -12.000  -0.4014   0.10507   0.10153  -0.0850   0.9836   0.0610
 -11.500  -0.3747   0.09827   0.09472  -0.0845   0.9781   0.0637
 -11.250  -0.3608   0.09498   0.09141  -0.0868   0.9757   0.0655
 -11.000  -0.3539   0.08983   0.08624  -0.0918   0.9736   0.0680
 -10.750  -0.3677   0.07903   0.07542  -0.1049   0.9711   0.0709
 -10.500  -0.4034   0.07132   0.06753  -0.1129   0.9627   0.0720
 -10.250  -0.4391   0.06759   0.06348  -0.1160   0.9544   0.0729
 -10.000  -0.4659   0.06659   0.06213  -0.1135   0.9449   0.0734
  -9.500  -0.4275   0.05616   0.05191  -0.1173   0.9413   0.0787
  -9.250  -0.4353   0.05464   0.05028  -0.1141   0.9334   0.0810
  -9.000  -0.4653   0.05660   0.05161  -0.1076   0.9246   0.0869
  -8.750  -0.4706   0.05116   0.04617  -0.1055   0.9189   0.0891
  -7.000  -0.4253   0.03152   0.02407  -0.0839   0.8904   0.0540
  -6.750  -0.4102   0.02998   0.02210  -0.0813   0.8868   0.0521
  -6.500  -0.3829   0.02853   0.02044  -0.0813   0.8849   0.0520
  -6.250  -0.3530   0.02716   0.01895  -0.0819   0.8837   0.0524
  -6.000  -0.3229   0.02612   0.01788  -0.0826   0.8826   0.0541
  -5.750  -0.2924   0.02531   0.01702  -0.0834   0.8816   0.0564
  -5.500  -0.3259   0.02627   0.01797  -0.0725   0.8739   0.0562
  -5.250  -0.3141   0.02589   0.01753  -0.0698   0.8708   0.0571
  -5.000  -0.2893   0.02526   0.01686  -0.0694   0.8689   0.0586
  -4.750  -0.2636   0.02475   0.01630  -0.0692   0.8675   0.0602
  -4.500  -0.2391   0.02406   0.01561  -0.0690   0.8663   0.0628
  -4.250  -0.2139   0.02347   0.01509  -0.0690   0.8653   0.0669
  -4.000  -0.2545   0.02453   0.01611  -0.0571   0.8582   0.0660
  -3.750  -0.2447   0.02448   0.01606  -0.0543   0.8557   0.0685
  -3.500  -0.2272   0.02432   0.01587  -0.0529   0.8538   0.0720
  -3.250  -0.2036   0.02388   0.01543  -0.0526   0.8520   0.0789
  -3.000  -0.1768   0.02351   0.01510  -0.0529   0.8507   0.0930
  -2.750  -0.1655   0.02086   0.01437  -0.0520   0.8495   0.4853
  -2.500  -0.1770   0.02131   0.01571  -0.0443   0.8452   0.7026
  -2.250  -0.1717   0.02211   0.01652  -0.0399   0.8415   0.7460
  -2.000  -0.1580   0.02294   0.01738  -0.0363   0.8387   0.7741
  -1.750  -0.1415   0.02382   0.01828  -0.0326   0.8364   0.7996
  -1.500  -0.1259   0.02482   0.01932  -0.0279   0.8344   0.8236
  -1.250  -0.1051   0.02563   0.02010  -0.0247   0.8330   0.8445
  -1.000  -0.1275   0.02621   0.02072  -0.0158   0.8258   0.8520
  -0.750  -0.1130   0.02655   0.02102  -0.0128   0.8225   0.8638
  -0.500  -0.0912   0.02685   0.02127  -0.0108   0.8200   0.8767
  -0.250  -0.0649   0.02714   0.02152  -0.0092   0.8182   0.8866
   0.000  -0.0690   0.02733   0.02170  -0.0044   0.8112   0.8937
   0.250  -0.0474   0.02739   0.02171  -0.0035   0.8072   0.8978
   0.500  -0.0144   0.02738   0.02164  -0.0049   0.8046   0.8999
   0.750   0.0239   0.02735   0.02155  -0.0072   0.8028   0.9015
   1.000   0.0623   0.02737   0.02152  -0.0095   0.8011   0.9026
   1.250   0.0563   0.02760   0.02175  -0.0051   0.7911   0.9072
   1.500   0.0922   0.02752   0.02164  -0.0068   0.7886   0.9085
   1.750   0.1311   0.02746   0.02156  -0.0090   0.7869   0.9095
   2.000   0.1332   0.02777   0.02188  -0.0056   0.7774   0.9131
   2.250   0.1667   0.02773   0.02183  -0.0070   0.7743   0.9148
   2.500   0.2053   0.02762   0.02172  -0.0091   0.7722   0.9165
   2.750   0.2464   0.02748   0.02159  -0.0116   0.7708   0.9180
   3.000   0.2492   0.02782   0.02195  -0.0085   0.7596   0.9220
   3.250   0.2871   0.02760   0.02176  -0.0103   0.7573   0.9234
   3.500   0.3285   0.02732   0.02151  -0.0125   0.7558   0.9246
   3.750   0.3347   0.02761   0.02185  -0.0097   0.7445   0.9290
   4.000   0.3750   0.02724   0.02153  -0.0118   0.7422   0.9307
   4.250   0.4182   0.02676   0.02110  -0.0142   0.7406   0.9323
   4.500   0.4265   0.02703   0.02143  -0.0116   0.7293   0.9372
   4.750   0.4673   0.02644   0.02092  -0.0135   0.7270   0.9392
   5.000   0.5156   0.02545   0.02003  -0.0161   0.7256   0.9406
   5.250   0.5802   0.02316   0.01784  -0.0202   0.7234   0.9400
   5.500   0.6124   0.02187   0.01665  -0.0199   0.7130   0.9432
   5.750   0.7135   0.01730   0.01217  -0.0284   0.7055   0.9385
   6.000   0.7392   0.01622   0.01116  -0.0271   0.6897   0.9423
   6.250   0.7480   0.01589   0.01091  -0.0235   0.6716   0.9487
   6.500   0.7599   0.01558   0.01069  -0.0205   0.6441   0.9550
   6.750   0.7950   0.01435   0.00879  -0.0198   0.5150   0.9578
   7.000   0.7812   0.01582   0.00952  -0.0137   0.3923   0.9682
   7.250   0.7642   0.01852   0.01132  -0.0094   0.2375   0.9798
   7.500   0.7570   0.02140   0.01321  -0.0071   0.0927   0.9918
   7.750   0.7647   0.02264   0.01432  -0.0054   0.0733   1.0000
   8.000   0.7768   0.02362   0.01529  -0.0043   0.0655   1.0000
   8.250   0.7901   0.02472   0.01641  -0.0035   0.0603   1.0000
   8.500   0.8058   0.02577   0.01748  -0.0029   0.0563   1.0000
   8.750   0.8183   0.02716   0.01882  -0.0021   0.0530   1.0000
   9.000   0.8374   0.02817   0.01989  -0.0018   0.0502   1.0000
   9.250   0.8578   0.02916   0.02090  -0.0016   0.0474   1.0000
   9.500   0.8801   0.03020   0.02192  -0.0016   0.0455   1.0000
   9.750   0.9207   0.03164   0.02322  -0.0029   0.0432   1.0000
  10.000   0.9482   0.03260   0.02432  -0.0033   0.0419   1.0000
  10.250   0.9762   0.03368   0.02553  -0.0039   0.0399   1.0000
  10.500   1.0120   0.03509   0.02704  -0.0051   0.0388   1.0000
  10.750   1.0509   0.03691   0.02900  -0.0068   0.0380   1.0000
  11.000   1.0876   0.03915   0.03144  -0.0083   0.0375   1.0000
  11.250   1.1164   0.04196   0.03459  -0.0089   0.0377   1.0000
  11.500   1.1339   0.04534   0.03841  -0.0081   0.0383   1.0000
  11.750   1.1434   0.04827   0.04166  -0.0066   0.0383   1.0000
  12.000   1.1436   0.05205   0.04584  -0.0041   0.0393   1.0000
  12.250   1.1413   0.05636   0.05049  -0.0017   0.0409   1.0000
  12.500   1.0426   0.06010   0.05521   0.0085   0.0519   1.0000
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