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


Details Polar file
Airfoil: NACA 66(1)-212 (naca661212-il)
Reynolds number: 1,000,000
Max Cl/Cd: 85.96 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca661212-il-1000000.txt
Download as CSV file: xf-naca661212-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7969   0.04102   0.03857  -0.0662   0.9937   0.0099
 -11.250  -0.8098   0.03401   0.03106  -0.0693   0.9726   0.0102
 -11.000  -0.7770   0.03480   0.03189  -0.0714   0.9629   0.0104
 -10.750  -0.7621   0.03451   0.03151  -0.0706   0.9477   0.0105
 -10.500  -0.7707   0.03148   0.02815  -0.0667   0.9319   0.0107
 -10.250  -0.7447   0.03303   0.02979  -0.0666   0.9248   0.0109
 -10.000  -0.7448   0.03053   0.02700  -0.0634   0.9148   0.0112
  -9.750  -0.7427   0.02765   0.02379  -0.0604   0.9062   0.0115
  -9.250  -0.7211   0.02336   0.01890  -0.0562   0.8932   0.0125
  -9.000  -0.7053   0.02166   0.01694  -0.0547   0.8876   0.0128
  -8.750  -0.6851   0.02100   0.01611  -0.0537   0.8827   0.0130
  -8.500  -0.6699   0.01786   0.01262  -0.0523   0.8777   0.0137
  -8.250  -0.6480   0.01726   0.01195  -0.0517   0.8732   0.0141
  -8.000  -0.6252   0.01667   0.01127  -0.0512   0.8692   0.0145
  -7.750  -0.6016   0.01630   0.01085  -0.0508   0.8652   0.0150
  -7.500  -0.5776   0.01595   0.01046  -0.0504   0.8613   0.0157
  -7.250  -0.5538   0.01523   0.00964  -0.0500   0.8577   0.0161
  -7.000  -0.5297   0.01461   0.00891  -0.0495   0.8542   0.0166
  -6.750  -0.5052   0.01411   0.00835  -0.0492   0.8509   0.0170
  -6.500  -0.4803   0.01370   0.00788  -0.0488   0.8474   0.0173
  -6.250  -0.4613   0.01234   0.00644  -0.0476   0.8439   0.0183
  -6.000  -0.4375   0.01196   0.00602  -0.0471   0.8406   0.0191
  -5.750  -0.4121   0.01173   0.00579  -0.0470   0.8377   0.0200
  -5.500  -0.3877   0.01137   0.00541  -0.0466   0.8346   0.0208
  -5.250  -0.3631   0.01102   0.00502  -0.0462   0.8317   0.0216
  -5.000  -0.3378   0.01077   0.00472  -0.0459   0.8290   0.0224
  -4.750  -0.3134   0.01042   0.00431  -0.0455   0.8263   0.0231
  -4.500  -0.2909   0.00984   0.00370  -0.0447   0.8237   0.0252
  -4.250  -0.2650   0.00961   0.00346  -0.0446   0.8212   0.0268
  -4.000  -0.2387   0.00941   0.00326  -0.0445   0.8187   0.0287
  -3.750  -0.2121   0.00924   0.00307  -0.0445   0.8163   0.0299
  -3.500  -0.1869   0.00891   0.00269  -0.0442   0.8140   0.0332
  -3.250  -0.1606   0.00873   0.00248  -0.0441   0.8117   0.0367
  -3.000  -0.1335   0.00860   0.00234  -0.0441   0.8094   0.0395
  -2.750  -0.1073   0.00835   0.00215  -0.0440   0.8073   0.0542
  -2.500  -0.0880   0.00737   0.00186  -0.0431   0.8048   0.2406
  -2.250  -0.0712   0.00607   0.00150  -0.0419   0.8024   0.5018
  -2.000  -0.0500   0.00538   0.00141  -0.0410   0.8003   0.6793
  -1.750  -0.0222   0.00536   0.00144  -0.0411   0.7985   0.7110
  -1.500   0.0058   0.00538   0.00149  -0.0412   0.7966   0.7324
  -1.250   0.0338   0.00545   0.00158  -0.0413   0.7947   0.7507
  -1.000   0.0621   0.00547   0.00163  -0.0414   0.7929   0.7605
  -0.750   0.0907   0.00553   0.00167  -0.0416   0.7909   0.7687
  -0.500   0.1189   0.00555   0.00173  -0.0418   0.7891   0.7758
  -0.250   0.1474   0.00563   0.00180  -0.0419   0.7872   0.7842
   0.000   0.1758   0.00562   0.00181  -0.0421   0.7846   0.7885
   0.250   0.2044   0.00567   0.00183  -0.0424   0.7811   0.7915
   0.500   0.2329   0.00564   0.00182  -0.0426   0.7776   0.7936
   0.750   0.2616   0.00563   0.00182  -0.0430   0.7742   0.7954
   1.000   0.2900   0.00561   0.00176  -0.0431   0.7678   0.7972
   1.250   0.3181   0.00557   0.00172  -0.0433   0.7600   0.7991
   1.500   0.3461   0.00553   0.00167  -0.0434   0.7530   0.8011
   1.750   0.3741   0.00550   0.00168  -0.0435   0.7458   0.8030
   2.000   0.4015   0.00548   0.00165  -0.0434   0.7329   0.8049
   2.250   0.4288   0.00547   0.00163  -0.0434   0.7174   0.8069
   2.500   0.4558   0.00550   0.00163  -0.0433   0.6979   0.8090
   2.750   0.4814   0.00560   0.00164  -0.0429   0.6624   0.8112
   3.000   0.4954   0.00640   0.00185  -0.0404   0.5212   0.8137
   3.250   0.5049   0.00757   0.00231  -0.0373   0.3477   0.8168
   3.500   0.5161   0.00867   0.00276  -0.0347   0.1913   0.8197
   3.750   0.5285   0.00973   0.00323  -0.0323   0.0544   0.8229
   4.000   0.5519   0.01005   0.00347  -0.0317   0.0392   0.8256
   4.250   0.5764   0.01031   0.00373  -0.0312   0.0343   0.8281
   4.500   0.6009   0.01051   0.00397  -0.0308   0.0318   0.8308
   4.750   0.6239   0.01081   0.00428  -0.0300   0.0285   0.8336
   5.000   0.6464   0.01116   0.00468  -0.0292   0.0260   0.8366
   5.250   0.6706   0.01139   0.00493  -0.0287   0.0245   0.8398
   5.500   0.6940   0.01167   0.00521  -0.0281   0.0229   0.8429
   5.750   0.7152   0.01206   0.00563  -0.0271   0.0211   0.8464
   6.000   0.7329   0.01267   0.00633  -0.0254   0.0198   0.8502
   6.250   0.7551   0.01298   0.00668  -0.0246   0.0193   0.8541
   6.500   0.7770   0.01333   0.00705  -0.0237   0.0184   0.8580
   6.750   0.7972   0.01371   0.00750  -0.0225   0.0177   0.8620
   7.000   0.8182   0.01401   0.00783  -0.0215   0.0169   0.8662
   7.250   0.8378   0.01436   0.00819  -0.0203   0.0161   0.8710
   7.500   0.8518   0.01505   0.00894  -0.0180   0.0155   0.8761
   7.750   0.8640   0.01620   0.01020  -0.0155   0.0150   0.8817
   8.000   0.8836   0.01667   0.01073  -0.0143   0.0147   0.8872
   8.250   0.9021   0.01723   0.01138  -0.0129   0.0145   0.8929
   8.500   0.9211   0.01790   0.01213  -0.0117   0.0142   0.8992
   8.750   0.9408   0.01867   0.01298  -0.0106   0.0139   0.9053
   9.000   0.9599   0.01939   0.01380  -0.0094   0.0135   0.9122
   9.250   0.9789   0.02010   0.01460  -0.0082   0.0132   0.9193
   9.500   0.9945   0.02052   0.01509  -0.0064   0.0127   0.9286
   9.750   1.0094   0.02097   0.01562  -0.0045   0.0124   0.9393
  10.000   1.0252   0.02172   0.01648  -0.0028   0.0122   0.9529
  10.250   1.0468   0.02251   0.01736  -0.0027   0.0119   0.9725
  10.500   1.0717   0.02673   0.02193  -0.0036   0.0112   0.9781
  10.750   1.0875   0.02746   0.02280  -0.0025   0.0111   1.0000
  11.000   1.0992   0.02895   0.02446  -0.0008   0.0110   1.0000
  11.250   1.1090   0.03032   0.02599   0.0012   0.0108   1.0000
  11.500   1.1144   0.03230   0.02818   0.0035   0.0107   1.0000
  11.750   1.1153   0.03461   0.03073   0.0062   0.0105   1.0000
  12.000   1.1117   0.03720   0.03355   0.0092   0.0103   1.0000
  12.250   1.1154   0.03848   0.03494   0.0112   0.0100   1.0000
  12.500   1.0975   0.04252   0.03929   0.0147   0.0099   1.0000
  12.750   1.0711   0.04745   0.04455   0.0181   0.0098   1.0000
  13.000   1.0727   0.04887   0.04604   0.0192   0.0095   1.0000
  13.250   1.0507   0.05334   0.05073   0.0210   0.0094   1.0000
  13.500   0.9854   0.06401   0.06182   0.0216   0.0095   1.0000
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