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NACA 66(1)-212 (naca661212-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 66(1)-212 (naca661212-il)
Reynolds number: 100,000
Max Cl/Cd: 32.69 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca661212-il-100000-n5.txt
Download as CSV file: xf-naca661212-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5682   0.07481   0.06948  -0.0649   1.0000   0.0301
 -10.250  -0.5833   0.07121   0.06588  -0.0644   1.0000   0.0299
 -10.000  -0.6028   0.06849   0.06314  -0.0622   1.0000   0.0297
  -9.750  -0.6277   0.06689   0.06156  -0.0577   1.0000   0.0296
  -9.500  -0.6581   0.06619   0.06087  -0.0511   1.0000   0.0296
  -9.250  -0.6667   0.06261   0.05712  -0.0502   0.9937   0.0294
  -9.000  -0.6659   0.05811   0.05229  -0.0511   0.9859   0.0294
  -8.750  -0.6636   0.05422   0.04793  -0.0510   0.9781   0.0298
  -8.500  -0.6590   0.05008   0.04339  -0.0509   0.9715   0.0306
  -8.250  -0.6462   0.04675   0.03986  -0.0513   0.9664   0.0316
  -8.000  -0.6280   0.04385   0.03668  -0.0519   0.9627   0.0324
  -7.750  -0.6161   0.04098   0.03341  -0.0507   0.9565   0.0325
  -7.500  -0.5962   0.03817   0.03018  -0.0506   0.9528   0.0329
  -7.250  -0.5718   0.03560   0.02717  -0.0511   0.9502   0.0335
  -7.000  -0.5558   0.03383   0.02510  -0.0496   0.9443   0.0342
  -6.750  -0.5318   0.03221   0.02317  -0.0495   0.9406   0.0362
  -6.500  -0.5039   0.03048   0.02108  -0.0499   0.9379   0.0379
  -6.250  -0.4730   0.02872   0.01900  -0.0507   0.9361   0.0388
  -6.000  -0.4527   0.02754   0.01760  -0.0493   0.9313   0.0396
  -5.750  -0.4266   0.02644   0.01630  -0.0491   0.9280   0.0405
  -5.500  -0.3994   0.02497   0.01487  -0.0495   0.9256   0.0429
  -5.250  -0.3717   0.02406   0.01395  -0.0499   0.9233   0.0462
  -5.000  -0.3431   0.02315   0.01297  -0.0504   0.9213   0.0487
  -4.750  -0.3293   0.02262   0.01237  -0.0480   0.9155   0.0506
  -4.500  -0.3090   0.02201   0.01169  -0.0469   0.9117   0.0535
  -4.250  -0.2861   0.02140   0.01107  -0.0465   0.9089   0.0591
  -4.000  -0.2601   0.02091   0.01044  -0.0465   0.9068   0.0648
  -3.750  -0.2461   0.02054   0.01009  -0.0442   0.9021   0.0717
  -3.500  -0.2281   0.02009   0.00972  -0.0427   0.8979   0.0913
  -3.000  -0.2113   0.01749   0.01005  -0.0352   0.8917   0.6785
  -2.750  -0.2042   0.01814   0.01072  -0.0302   0.8867   0.7512
  -2.500  -0.1899   0.01914   0.01173  -0.0254   0.8832   0.7991
  -2.250  -0.1659   0.02005   0.01257  -0.0226   0.8809   0.8292
  -2.000  -0.1380   0.02067   0.01309  -0.0211   0.8790   0.8512
  -1.750  -0.1040   0.02093   0.01320  -0.0218   0.8777   0.8606
  -1.500  -0.0848   0.02096   0.01313  -0.0205   0.8746   0.8668
  -1.250  -0.0680   0.02108   0.01318  -0.0188   0.8702   0.8721
  -1.000  -0.0506   0.02103   0.01305  -0.0172   0.8664   0.8788
  -0.750  -0.0206   0.02106   0.01299  -0.0180   0.8644   0.8821
  -0.500   0.0110   0.02107   0.01293  -0.0191   0.8627   0.8852
  -0.250   0.0230   0.02114   0.01297  -0.0166   0.8578   0.8909
   0.000   0.0381   0.02116   0.01296  -0.0148   0.8530   0.8957
   0.250   0.0688   0.02117   0.01294  -0.0157   0.8504   0.8982
   0.500   0.1006   0.02116   0.01291  -0.0169   0.8482   0.9007
   0.750   0.1168   0.02123   0.01298  -0.0152   0.8434   0.9053
   1.000   0.1316   0.02130   0.01304  -0.0133   0.8379   0.9103
   1.250   0.1640   0.02132   0.01309  -0.0145   0.8351   0.9126
   1.500   0.1980   0.02130   0.01310  -0.0160   0.8329   0.9149
   1.750   0.2090   0.02146   0.01330  -0.0135   0.8258   0.9205
   2.000   0.2334   0.02148   0.01336  -0.0132   0.8214   0.9245
   2.250   0.2701   0.02145   0.01341  -0.0152   0.8188   0.9264
   2.750   0.3168   0.02164   0.01377  -0.0144   0.8072   0.9351
   3.000   0.3495   0.02152   0.01375  -0.0153   0.8038   0.9382
   3.250   0.3747   0.02164   0.01401  -0.0153   0.7964   0.9418
   3.500   0.4096   0.02147   0.01399  -0.0166   0.7907   0.9443
   3.750   0.4426   0.02098   0.01365  -0.0170   0.7796   0.9475
   4.000   0.4996   0.01889   0.01171  -0.0192   0.7570   0.9457
   4.250   0.5187   0.01784   0.01074  -0.0160   0.7222   0.9516
   4.500   0.5379   0.01700   0.00993  -0.0132   0.6497   0.9567
   4.750   0.5626   0.01721   0.00848  -0.0105   0.3550   0.9585
   5.000   0.5654   0.01905   0.00921  -0.0074   0.1515   0.9662
   5.250   0.5853   0.02035   0.00999  -0.0070   0.0774   0.9715
   5.500   0.6105   0.02117   0.01077  -0.0072   0.0632   0.9768
   5.750   0.6367   0.02206   0.01171  -0.0078   0.0566   0.9821
   6.000   0.6632   0.02288   0.01264  -0.0084   0.0504   0.9877
   6.250   0.6864   0.02400   0.01377  -0.0087   0.0468   0.9948
   6.500   0.7011   0.02476   0.01464  -0.0069   0.0449   1.0000
   6.750   0.7040   0.02528   0.01522  -0.0028   0.0431   1.0000
   7.000   0.7160   0.02603   0.01599  -0.0005   0.0407   1.0000
   7.250   0.7342   0.02702   0.01699   0.0006   0.0381   1.0000
   7.500   0.7657   0.02892   0.01886  -0.0006   0.0363   1.0000
   7.750   0.7962   0.03057   0.02066  -0.0012   0.0354   1.0000
   8.000   0.8249   0.03231   0.02263  -0.0015   0.0345   1.0000
   8.250   0.8504   0.03419   0.02481  -0.0014   0.0335   1.0000
   8.500   0.8714   0.03597   0.02686  -0.0007   0.0320   1.0000
   8.750   0.8899   0.03781   0.02896   0.0002   0.0305   1.0000
   9.000   0.9067   0.04001   0.03146   0.0013   0.0298   1.0000
   9.250   0.9204   0.04241   0.03418   0.0028   0.0294   1.0000
   9.500   0.9306   0.04498   0.03708   0.0046   0.0291   1.0000
   9.750   0.9372   0.04770   0.04012   0.0067   0.0288   1.0000
  10.000   0.9394   0.05057   0.04335   0.0092   0.0287   1.0000
  10.250   0.9367   0.05351   0.04661   0.0121   0.0286   1.0000
  10.500   0.9281   0.05644   0.04983   0.0154   0.0286   1.0000
  10.750   0.9169   0.05946   0.05311   0.0185   0.0286   1.0000
  11.000   0.9066   0.06238   0.05623   0.0208   0.0284   1.0000
  11.250   0.8914   0.06578   0.05985   0.0228   0.0283   1.0000
  11.500   0.8765   0.06930   0.06356   0.0241   0.0282   1.0000
  11.750   0.8487   0.07439   0.06891   0.0246   0.0286   1.0000
  12.000   0.8221   0.08005   0.07477   0.0236   0.0288   1.0000
  12.250   0.7847   0.08860   0.08351   0.0198   0.0298   1.0000
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