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NACA 66(1)-212 (naca661212-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 66(1)-212 (naca661212-il)
Reynolds number: 500,000
Max Cl/Cd: 62.81 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca661212-il-500000-n5.txt
Download as CSV file: xf-naca661212-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(1)-212                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5439   0.10670   0.10431  -0.0407   1.0000   0.0097
 -12.500  -0.5490   0.10130   0.09893  -0.0433   1.0000   0.0098
 -12.000  -0.8189   0.04237   0.03918  -0.0682   1.0000   0.0094
 -11.500  -0.7949   0.04023   0.03691  -0.0693   0.9749   0.0097
 -11.250  -0.7794   0.03834   0.03486  -0.0712   0.9615   0.0099
 -11.000  -0.7712   0.03627   0.03257  -0.0711   0.9468   0.0101
 -10.750  -0.7743   0.03393   0.02994  -0.0682   0.9316   0.0103
 -10.500  -0.7710   0.03205   0.02781  -0.0657   0.9206   0.0106
 -10.250  -0.7695   0.02942   0.02483  -0.0628   0.9106   0.0109
 -10.000  -0.7624   0.02710   0.02217  -0.0605   0.9030   0.0113
  -9.750  -0.7509   0.02507   0.01979  -0.0587   0.8962   0.0118
  -9.500  -0.7348   0.02369   0.01812  -0.0573   0.8908   0.0123
  -9.250  -0.7170   0.02242   0.01662  -0.0562   0.8853   0.0127
  -9.000  -0.6989   0.02126   0.01531  -0.0552   0.8802   0.0131
  -8.750  -0.6785   0.02061   0.01456  -0.0544   0.8758   0.0134
  -8.500  -0.6572   0.01992   0.01378  -0.0537   0.8710   0.0138
  -8.250  -0.6355   0.01922   0.01296  -0.0531   0.8665   0.0141
  -8.000  -0.6132   0.01850   0.01212  -0.0524   0.8625   0.0146
  -7.750  -0.5904   0.01781   0.01131  -0.0519   0.8588   0.0152
  -7.500  -0.5672   0.01718   0.01058  -0.0514   0.8548   0.0158
  -7.250  -0.5439   0.01658   0.00987  -0.0509   0.8512   0.0163
  -7.000  -0.5206   0.01600   0.00917  -0.0504   0.8480   0.0166
  -6.750  -0.4989   0.01517   0.00826  -0.0496   0.8448   0.0172
  -6.500  -0.4764   0.01457   0.00763  -0.0490   0.8413   0.0177
  -6.250  -0.4533   0.01412   0.00715  -0.0485   0.8380   0.0183
  -6.000  -0.4298   0.01372   0.00670  -0.0480   0.8348   0.0189
  -5.750  -0.4060   0.01336   0.00628  -0.0475   0.8321   0.0198
  -5.500  -0.3817   0.01303   0.00592  -0.0471   0.8289   0.0208
  -5.250  -0.3577   0.01267   0.00552  -0.0466   0.8258   0.0217
  -5.000  -0.3332   0.01236   0.00514  -0.0462   0.8230   0.0223
  -4.750  -0.3108   0.01183   0.00458  -0.0455   0.8203   0.0238
  -4.500  -0.2862   0.01153   0.00425  -0.0452   0.8180   0.0251
  -4.250  -0.2610   0.01127   0.00396  -0.0449   0.8157   0.0268
  -4.000  -0.2353   0.01105   0.00371  -0.0447   0.8132   0.0286
  -3.750  -0.2093   0.01087   0.00351  -0.0446   0.8107   0.0301
  -3.500  -0.1841   0.01058   0.00321  -0.0443   0.8083   0.0338
  -3.250  -0.1581   0.01038   0.00299  -0.0442   0.8059   0.0370
  -3.000  -0.1317   0.01022   0.00280  -0.0441   0.8038   0.0416
  -2.750  -0.1060   0.00998   0.00262  -0.0439   0.8018   0.0580
  -2.500  -0.0832   0.00942   0.00241  -0.0434   0.7994   0.1498
  -2.250  -0.0644   0.00845   0.00213  -0.0426   0.7969   0.3345
  -2.000  -0.0519   0.00699   0.00186  -0.0405   0.7943   0.6375
  -1.750  -0.0265   0.00691   0.00198  -0.0400   0.7923   0.7080
  -1.500   0.0007   0.00695   0.00206  -0.0398   0.7905   0.7357
  -1.250   0.0286   0.00699   0.00209  -0.0398   0.7889   0.7493
  -1.000   0.0566   0.00705   0.00212  -0.0399   0.7872   0.7610
  -0.750   0.0842   0.00710   0.00220  -0.0399   0.7850   0.7716
  -0.500   0.1120   0.00714   0.00227  -0.0399   0.7830   0.7790
  -0.250   0.1405   0.00716   0.00228  -0.0402   0.7811   0.7818
   0.000   0.1692   0.00716   0.00228  -0.0405   0.7792   0.7838
   0.250   0.1978   0.00718   0.00228  -0.0409   0.7774   0.7857
   0.500   0.2266   0.00719   0.00228  -0.0412   0.7755   0.7877
   0.750   0.2554   0.00720   0.00227  -0.0416   0.7728   0.7897
   1.000   0.2832   0.00719   0.00230  -0.0417   0.7680   0.7915
   1.250   0.3108   0.00715   0.00227  -0.0417   0.7605   0.7933
   1.500   0.3384   0.00713   0.00226  -0.0417   0.7523   0.7952
   1.750   0.3661   0.00712   0.00225  -0.0417   0.7443   0.7971
   2.000   0.3932   0.00710   0.00224  -0.0416   0.7317   0.7992
   2.250   0.4198   0.00709   0.00220  -0.0413   0.7145   0.8015
   2.500   0.4455   0.00711   0.00216  -0.0409   0.6858   0.8037
   2.750   0.4648   0.00740   0.00213  -0.0392   0.5917   0.8060
   3.000   0.4710   0.00859   0.00256  -0.0353   0.4268   0.8088
   3.250   0.4800   0.00976   0.00304  -0.0323   0.2680   0.8120
   3.500   0.4943   0.01065   0.00344  -0.0303   0.1524   0.8151
   3.750   0.5116   0.01137   0.00381  -0.0288   0.0713   0.8181
   4.000   0.5333   0.01178   0.00409  -0.0279   0.0433   0.8206
   4.250   0.5563   0.01206   0.00436  -0.0272   0.0356   0.8230
   4.500   0.5799   0.01230   0.00463  -0.0266   0.0324   0.8257
   4.750   0.6028   0.01259   0.00494  -0.0259   0.0293   0.8287
   5.000   0.6248   0.01296   0.00533  -0.0251   0.0265   0.8319
   5.250   0.6482   0.01322   0.00563  -0.0245   0.0254   0.8351
   5.500   0.6703   0.01351   0.00598  -0.0236   0.0238   0.8382
   5.750   0.6918   0.01384   0.00636  -0.0227   0.0223   0.8417
   6.000   0.7125   0.01423   0.00677  -0.0216   0.0208   0.8455
   6.250   0.7312   0.01477   0.00734  -0.0203   0.0195   0.8495
   6.500   0.7513   0.01510   0.00773  -0.0191   0.0187   0.8529
   6.750   0.7701   0.01546   0.00817  -0.0177   0.0177   0.8570
   7.000   0.7881   0.01589   0.00865  -0.0161   0.0170   0.8617
   7.250   0.8061   0.01635   0.00916  -0.0146   0.0164   0.8662
   7.500   0.8238   0.01680   0.00967  -0.0131   0.0159   0.8710
   7.750   0.8411   0.01733   0.01024  -0.0116   0.0154   0.8768
   8.000   0.8567   0.01801   0.01099  -0.0098   0.0149   0.8825
   8.250   0.8714   0.01885   0.01191  -0.0079   0.0145   0.8889
   8.500   0.8891   0.01949   0.01264  -0.0066   0.0142   0.8952
   8.750   0.9059   0.02020   0.01346  -0.0050   0.0140   0.9019
   9.250   0.9407   0.02175   0.01524  -0.0023   0.0134   0.9168
   9.500   0.9581   0.02248   0.01608  -0.0010   0.0130   0.9255
   9.750   0.9745   0.02310   0.01681   0.0005   0.0125   0.9363
  10.000   0.9921   0.02393   0.01776   0.0016   0.0122   0.9493
  10.500   1.0363   0.02583   0.01989   0.0014   0.0117   1.0000
  10.750   1.0524   0.02686   0.02103   0.0024   0.0115   1.0000
  11.000   1.0672   0.02792   0.02217   0.0035   0.0113   1.0000
  11.250   1.0804   0.02925   0.02363   0.0048   0.0110   1.0000
  11.500   1.0902   0.03131   0.02588   0.0063   0.0108   1.0000
  11.750   1.1008   0.03261   0.02736   0.0077   0.0106   1.0000
  12.000   1.1083   0.03442   0.02939   0.0094   0.0104   1.0000
  12.250   1.1129   0.03643   0.03163   0.0112   0.0102   1.0000
  12.500   1.1145   0.03864   0.03407   0.0131   0.0100   1.0000
  12.750   1.1118   0.04128   0.03696   0.0151   0.0097   1.0000
  13.000   1.1048   0.04432   0.04025   0.0171   0.0095   1.0000
  13.250   1.0927   0.04794   0.04413   0.0189   0.0094   1.0000
  13.500   1.0800   0.05163   0.04807   0.0201   0.0093   1.0000
  13.750   1.0620   0.05611   0.05279   0.0209   0.0092   1.0000
  14.000   1.0440   0.06081   0.05770   0.0209   0.0090   1.0000
  14.250   1.0118   0.06803   0.06517   0.0194   0.0091   1.0000
  14.500   0.9560   0.08060   0.07807   0.0139   0.0092   1.0000
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