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NACA 66(1)-212 (naca661212-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 66(1)-212 (naca661212-il)
Reynolds number: 500,000
Max Cl/Cd: 71.09 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca661212-il-500000.txt
Download as CSV file: xf-naca661212-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4064   0.08722   0.08510  -0.0517   1.0000   0.0246
 -11.000  -0.4132   0.08219   0.08010  -0.0534   1.0000   0.0248
 -10.750  -0.4238   0.07664   0.07458  -0.0555   0.9992   0.0251
 -10.500  -0.4496   0.06426   0.06219  -0.0649   0.9930   0.0248
 -10.250  -0.4907   0.05279   0.05054  -0.0732   0.9861   0.0244
 -10.000  -0.5094   0.04662   0.04421  -0.0768   0.9783   0.0244
  -9.750  -0.5197   0.04179   0.03921  -0.0790   0.9693   0.0245
  -9.500  -0.5285   0.03847   0.03574  -0.0785   0.9560   0.0248
  -8.000  -0.5849   0.02941   0.02428  -0.0602   0.9139   0.0235
  -7.750  -0.5665   0.02832   0.02294  -0.0586   0.9082   0.0230
  -7.500  -0.5520   0.02502   0.01930  -0.0569   0.9033   0.0233
  -7.250  -0.5312   0.02332   0.01734  -0.0558   0.8996   0.0232
  -7.000  -0.5091   0.02112   0.01492  -0.0551   0.8956   0.0233
  -6.750  -0.4849   0.01918   0.01283  -0.0548   0.8919   0.0238
  -6.500  -0.4601   0.01794   0.01151  -0.0545   0.8886   0.0243
  -6.250  -0.4357   0.01722   0.01073  -0.0542   0.8856   0.0255
  -6.000  -0.4108   0.01659   0.01005  -0.0539   0.8825   0.0267
  -5.750  -0.3857   0.01582   0.00922  -0.0536   0.8790   0.0277
  -5.500  -0.3609   0.01507   0.00841  -0.0531   0.8756   0.0284
  -5.250  -0.3364   0.01450   0.00776  -0.0526   0.8726   0.0293
  -5.000  -0.3113   0.01417   0.00736  -0.0522   0.8700   0.0301
  -4.750  -0.2931   0.01293   0.00609  -0.0508   0.8666   0.0323
  -4.500  -0.2702   0.01248   0.00565  -0.0502   0.8634   0.0345
  -4.250  -0.2467   0.01208   0.00521  -0.0496   0.8605   0.0365
  -4.000  -0.2224   0.01175   0.00483  -0.0491   0.8580   0.0385
  -3.750  -0.1988   0.01135   0.00437  -0.0485   0.8557   0.0412
  -3.500  -0.1747   0.01102   0.00404  -0.0480   0.8533   0.0466
  -3.250  -0.1496   0.01078   0.00378  -0.0477   0.8504   0.0525
  -3.000  -0.1268   0.01029   0.00349  -0.0471   0.8475   0.0974
  -2.750  -0.1211   0.00817   0.00291  -0.0444   0.8442   0.4896
  -2.500  -0.1044   0.00747   0.00298  -0.0423   0.8419   0.7001
  -2.250  -0.0774   0.00755   0.00307  -0.0420   0.8402   0.7311
  -2.000  -0.0513   0.00772   0.00328  -0.0415   0.8380   0.7584
  -1.750  -0.0253   0.00793   0.00353  -0.0409   0.8357   0.7783
  -1.500   0.0012   0.00812   0.00374  -0.0404   0.8334   0.7917
  -1.250   0.0281   0.00825   0.00387  -0.0401   0.8311   0.8017
  -1.000   0.0553   0.00839   0.00401  -0.0398   0.8292   0.8095
  -0.750   0.0824   0.00852   0.00413  -0.0396   0.8276   0.8173
  -0.500   0.1102   0.00862   0.00423  -0.0395   0.8261   0.8221
  -0.250   0.1382   0.00869   0.00428  -0.0397   0.8242   0.8264
   0.000   0.1659   0.00871   0.00430  -0.0400   0.8218   0.8294
   0.250   0.1935   0.00870   0.00431  -0.0402   0.8190   0.8311
   0.500   0.2215   0.00867   0.00429  -0.0403   0.8157   0.8330
   0.750   0.2502   0.00862   0.00423  -0.0405   0.8127   0.8348
   1.000   0.2791   0.00863   0.00422  -0.0409   0.8101   0.8367
   1.250   0.3063   0.00862   0.00426  -0.0410   0.8064   0.8390
   1.500   0.3342   0.00853   0.00418  -0.0411   0.8009   0.8415
   1.750   0.3633   0.00840   0.00400  -0.0412   0.7943   0.8438
   2.000   0.3899   0.00823   0.00386  -0.0409   0.7854   0.8455
   2.250   0.4168   0.00806   0.00371  -0.0405   0.7750   0.8474
   2.500   0.4440   0.00792   0.00355  -0.0402   0.7639   0.8494
   2.750   0.4698   0.00776   0.00341  -0.0396   0.7475   0.8517
   3.000   0.4953   0.00763   0.00326  -0.0390   0.7256   0.8543
   3.250   0.5208   0.00759   0.00321  -0.0385   0.7005   0.8572
   3.500   0.5431   0.00764   0.00312  -0.0373   0.6433   0.8599
   3.750   0.5418   0.00893   0.00348  -0.0318   0.4390   0.8635
   4.000   0.5399   0.01059   0.00414  -0.0269   0.2210   0.8679
   4.250   0.5456   0.01199   0.00475  -0.0235   0.0610   0.8723
   4.500   0.5654   0.01243   0.00514  -0.0222   0.0460   0.8754
   4.750   0.5870   0.01272   0.00548  -0.0212   0.0416   0.8784
   5.000   0.6068   0.01315   0.00594  -0.0198   0.0374   0.8822
   5.250   0.6246   0.01375   0.00659  -0.0182   0.0346   0.8867
   5.500   0.6446   0.01411   0.00701  -0.0169   0.0327   0.8905
   5.750   0.6631   0.01453   0.00747  -0.0153   0.0304   0.8946
   6.000   0.6805   0.01505   0.00801  -0.0137   0.0284   0.8994
   6.250   0.6919   0.01602   0.00905  -0.0110   0.0270   0.9047
   6.500   0.7084   0.01671   0.00982  -0.0091   0.0260   0.9096
   6.750   0.7282   0.01729   0.01046  -0.0078   0.0252   0.9151
   7.000   0.7487   0.01799   0.01123  -0.0067   0.0244   0.9201
   7.250   0.7702   0.01874   0.01205  -0.0057   0.0235   0.9257
   7.500   0.7933   0.01949   0.01285  -0.0052   0.0226   0.9317
   7.750   0.8127   0.02011   0.01352  -0.0039   0.0217   0.9386
   8.000   0.8395   0.02127   0.01471  -0.0042   0.0209   0.9445
   8.250   0.8757   0.02391   0.01747  -0.0062   0.0203   0.9467
   8.500   0.9047   0.02723   0.02106  -0.0068   0.0200   0.9509
   8.750   0.9213   0.02846   0.02252  -0.0051   0.0198   0.9611
   9.000   0.9415   0.03019   0.02453  -0.0043   0.0197   0.9722
   9.250   0.9657   0.03241   0.02706  -0.0046   0.0193   0.9836
   9.500   0.9838   0.03468   0.02967  -0.0040   0.0188   1.0000
   9.750   0.9908   0.03837   0.03370  -0.0020   0.0191   1.0000
  10.000   0.9558   0.05426   0.05041   0.0040   0.0264   1.0000
  10.250   0.9502   0.05679   0.05317   0.0071   0.0264   1.0000
  10.500   0.9387   0.05844   0.05502   0.0112   0.0262   1.0000
  10.750   0.9279   0.05778   0.05466   0.0164   0.0243   1.0000
  11.000   0.9103   0.06098   0.05803   0.0193   0.0243   1.0000
  11.250   0.8913   0.06440   0.06161   0.0215   0.0238   1.0000
  11.500   0.8704   0.06839   0.06574   0.0226   0.0236   1.0000
  11.750   0.8468   0.07313   0.07061   0.0227   0.0236   1.0000
  12.000   0.8210   0.07882   0.07642   0.0213   0.0238   1.0000
  12.250   0.7925   0.08603   0.08375   0.0178   0.0238   1.0000
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