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

NACA 66(2)-415 (naca662415-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 66(2)-415 (naca662415-il)
Reynolds number: 500,000
Max Cl/Cd: 93.96 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca662415-il-500000.txt
Download as CSV file: xf-naca662415-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3235   0.08437   0.08188  -0.1054   0.9575   0.0301
 -11.750  -0.3357   0.07236   0.06983  -0.1173   0.9487   0.0308
 -11.500  -0.3687   0.06192   0.05919  -0.1264   0.9353   0.0308
 -11.250  -0.3954   0.05674   0.05381  -0.1280   0.9227   0.0306
  -9.500  -0.5355   0.03235   0.02731  -0.1003   0.8668   0.0266
  -9.250  -0.5285   0.02960   0.02426  -0.0980   0.8631   0.0262
  -9.000  -0.5177   0.02731   0.02167  -0.0959   0.8594   0.0263
  -8.750  -0.5021   0.02569   0.01979  -0.0944   0.8559   0.0267
  -8.500  -0.4846   0.02492   0.01876  -0.0929   0.8528   0.0273
  -8.250  -0.4658   0.02364   0.01721  -0.0918   0.8501   0.0277
  -8.000  -0.4405   0.02117   0.01455  -0.0920   0.8478   0.0281
  -7.750  -0.4147   0.01979   0.01313  -0.0921   0.8452   0.0287
  -7.500  -0.3898   0.01894   0.01224  -0.0920   0.8426   0.0293
  -7.250  -0.3651   0.01829   0.01156  -0.0918   0.8401   0.0302
  -7.000  -0.3402   0.01773   0.01094  -0.0916   0.8378   0.0314
  -6.750  -0.3144   0.01706   0.01019  -0.0915   0.8358   0.0322
  -6.500  -0.2889   0.01649   0.00954  -0.0913   0.8339   0.0329
  -6.250  -0.2643   0.01605   0.00905  -0.0910   0.8318   0.0335
  -6.000  -0.2419   0.01515   0.00814  -0.0904   0.8296   0.0344
  -5.750  -0.2218   0.01448   0.00749  -0.0894   0.8272   0.0358
  -5.500  -0.2000   0.01410   0.00711  -0.0887   0.8249   0.0372
  -5.250  -0.1780   0.01373   0.00672  -0.0879   0.8229   0.0387
  -5.000  -0.1554   0.01339   0.00634  -0.0872   0.8209   0.0401
  -4.750  -0.1320   0.01311   0.00601  -0.0867   0.8191   0.0411
  -4.500  -0.1117   0.01264   0.00550  -0.0857   0.8171   0.0433
  -4.250  -0.0897   0.01235   0.00523  -0.0849   0.8152   0.0463
  -4.000  -0.0662   0.01215   0.00503  -0.0844   0.8132   0.0493
  -3.750  -0.0430   0.01189   0.00477  -0.0838   0.8112   0.0536
  -3.500  -0.0189   0.01167   0.00457  -0.0834   0.8094   0.0617
  -3.250  -0.0042   0.01067   0.00421  -0.0819   0.8074   0.2135
  -3.000   0.0014   0.00877   0.00367  -0.0793   0.8053   0.5556
  -2.750   0.0248   0.00861   0.00391  -0.0784   0.8039   0.6867
  -2.500   0.0530   0.00876   0.00404  -0.0785   0.8027   0.7111
  -2.250   0.0810   0.00901   0.00426  -0.0785   0.8013   0.7321
  -2.000   0.1067   0.00929   0.00460  -0.0779   0.7996   0.7495
  -1.750   0.1329   0.00959   0.00494  -0.0774   0.7979   0.7620
  -1.500   0.1587   0.00989   0.00529  -0.0767   0.7963   0.7718
  -1.250   0.1861   0.01007   0.00544  -0.0767   0.7948   0.7790
  -1.000   0.2124   0.01026   0.00567  -0.0762   0.7933   0.7847
  -0.750   0.2393   0.01047   0.00589  -0.0760   0.7919   0.7905
  -0.500   0.2679   0.01053   0.00591  -0.0764   0.7904   0.7946
  -0.250   0.2968   0.01054   0.00590  -0.0769   0.7891   0.7972
   0.000   0.3251   0.01056   0.00592  -0.0772   0.7880   0.7989
   0.250   0.3543   0.01060   0.00595  -0.0777   0.7866   0.8004
   0.500   0.3815   0.01064   0.00600  -0.0778   0.7845   0.8017
   0.750   0.4077   0.01066   0.00604  -0.0778   0.7818   0.8032
   1.000   0.4351   0.01066   0.00606  -0.0780   0.7791   0.8048
   1.250   0.4637   0.01063   0.00603  -0.0784   0.7766   0.8066
   1.500   0.4931   0.01058   0.00598  -0.0790   0.7745   0.8082
   1.750   0.5234   0.01055   0.00594  -0.0798   0.7727   0.8097
   2.000   0.5544   0.01056   0.00593  -0.0807   0.7708   0.8111
   2.250   0.5803   0.01057   0.00598  -0.0807   0.7673   0.8127
   2.500   0.6072   0.01039   0.00585  -0.0805   0.7620   0.8140
   2.750   0.6393   0.01010   0.00553  -0.0812   0.7566   0.8153
   3.000   0.6647   0.00995   0.00542  -0.0807   0.7493   0.8169
   3.250   0.6943   0.00970   0.00517  -0.0810   0.7422   0.8184
   3.500   0.7204   0.00958   0.00509  -0.0807   0.7350   0.8200
   3.750   0.7488   0.00934   0.00483  -0.0807   0.7252   0.8217
   4.000   0.7720   0.00915   0.00467  -0.0797   0.7117   0.8237
   4.250   0.7955   0.00900   0.00452  -0.0788   0.6952   0.8258
   4.500   0.8188   0.00895   0.00447  -0.0780   0.6785   0.8279
   4.750   0.8381   0.00892   0.00444  -0.0763   0.6496   0.8298
   5.000   0.8418   0.00924   0.00444  -0.0714   0.5692   0.8322
   5.250   0.8284   0.01010   0.00487  -0.0634   0.4880   0.8358
   5.500   0.8129   0.01106   0.00548  -0.0554   0.4141   0.8402
   5.750   0.8017   0.01227   0.00627  -0.0488   0.3337   0.8444
   6.000   0.7915   0.01356   0.00716  -0.0428   0.2476   0.8480
   6.250   0.7820   0.01509   0.00817  -0.0372   0.1474   0.8519
   6.500   0.7783   0.01657   0.00919  -0.0329   0.0649   0.8560
   6.750   0.7914   0.01732   0.00984  -0.0310   0.0487   0.8595
   7.000   0.8052   0.01797   0.01049  -0.0292   0.0428   0.8626
   7.250   0.8214   0.01850   0.01107  -0.0277   0.0397   0.8659
   7.500   0.8357   0.01916   0.01176  -0.0261   0.0371   0.8697
   7.750   0.8486   0.01998   0.01261  -0.0243   0.0346   0.8739
   8.000   0.8640   0.02060   0.01330  -0.0229   0.0332   0.8779
   8.250   0.8777   0.02128   0.01404  -0.0212   0.0318   0.8822
   8.500   0.8906   0.02209   0.01488  -0.0195   0.0302   0.8871
   8.750   0.8967   0.02341   0.01624  -0.0171   0.0286   0.8922
   9.000   0.9126   0.02396   0.01688  -0.0158   0.0277   0.8969
   9.250   0.9270   0.02471   0.01769  -0.0144   0.0266   0.9025
   9.500   0.9406   0.02554   0.01859  -0.0129   0.0258   0.9082
   9.750   0.9532   0.02636   0.01946  -0.0112   0.0250   0.9146
  10.000   0.9660   0.02731   0.02043  -0.0098   0.0241   0.9216
  10.250   0.9782   0.02869   0.02184  -0.0080   0.0231   0.9280
  10.500   0.9939   0.02939   0.02264  -0.0068   0.0228   0.9370
  10.750   1.0102   0.03015   0.02351  -0.0055   0.0224   0.9484
  11.000   1.0306   0.03097   0.02444  -0.0053   0.0217   0.9639
  11.250   1.0550   0.03192   0.02547  -0.0060   0.0211   1.0000
  11.500   1.0757   0.03294   0.02653  -0.0060   0.0205   1.0000
  11.750   1.0937   0.03397   0.02761  -0.0058   0.0198   1.0000
  12.000   1.1151   0.03513   0.02881  -0.0058   0.0195   1.0000
  12.250   1.1412   0.03651   0.03020  -0.0062   0.0190   1.0000
  12.500   1.1762   0.03888   0.03272  -0.0074   0.0186   1.0000
  12.750   1.1848   0.04038   0.03441  -0.0061   0.0184   1.0000
  13.000   1.1972   0.04232   0.03653  -0.0052   0.0183   1.0000
  13.250   1.2042   0.04439   0.03882  -0.0039   0.0181   1.0000
  13.500   1.2093   0.04679   0.04143  -0.0026   0.0179   1.0000
  13.750   1.2110   0.04950   0.04437  -0.0011   0.0179   1.0000
  14.000   1.2082   0.05258   0.04769   0.0005   0.0178   1.0000
  14.250   1.2009   0.05576   0.05111   0.0022   0.0177   1.0000
  14.500   1.1918   0.05912   0.05468   0.0037   0.0176   1.0000
  14.750   1.1766   0.06319   0.05901   0.0051   0.0175   1.0000
  15.000   1.1610   0.06756   0.06360   0.0059   0.0175   1.0000
  15.250   1.1424   0.07232   0.06859   0.0063   0.0174   1.0000
  15.500   1.1207   0.07790   0.07440   0.0061   0.0175   1.0000
  15.750   1.0974   0.08403   0.08073   0.0051   0.0176   1.0000
  16.000   1.0764   0.09029   0.08716   0.0033   0.0179   1.0000
  16.250   1.0514   0.09762   0.09469   0.0004   0.0179   1.0000
  16.500   1.0261   0.10574   0.10297  -0.0035   0.0181   1.0000
  16.750   1.0017   0.11443   0.11179  -0.0082   0.0183   1.0000
  17.000   0.9928   0.12093   0.11842  -0.0117   0.0192   1.0000
<< Back to NACA 66(2)-415 (naca662415-il)

Polar data table (+)

Polar graphs


<< Back to NACA 66(2)-415 (naca662415-il)