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NACA 65(1)-212 a=0.6 (naca651212a06-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(1)-212 a=0.6 (naca651212a06-il)
Reynolds number: 1,000,000
Max Cl/Cd: 94.13 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca651212a06-il-1000000.txt
Download as CSV file: xf-naca651212a06-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-212 a=0.6                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5460   0.08259   0.08104  -0.0385   1.0000   0.0143
 -10.500  -0.7796   0.03908   0.03646  -0.0547   0.9252   0.0102
 -10.250  -0.8005   0.03423   0.03119  -0.0504   0.9061   0.0105
 -10.000  -0.7956   0.03221   0.02893  -0.0482   0.8943   0.0109
  -9.750  -0.7974   0.02843   0.02470  -0.0452   0.8833   0.0114
  -9.500  -0.7908   0.02535   0.02122  -0.0430   0.8739   0.0117
  -9.250  -0.7744   0.02393   0.01955  -0.0417   0.8662   0.0120
  -9.000  -0.7553   0.02289   0.01831  -0.0407   0.8586   0.0123
  -8.750  -0.7447   0.01938   0.01436  -0.0388   0.8518   0.0128
  -8.500  -0.7226   0.01863   0.01354  -0.0383   0.8453   0.0132
  -8.250  -0.6994   0.01823   0.01305  -0.0378   0.8392   0.0136
  -8.000  -0.6757   0.01761   0.01234  -0.0374   0.8332   0.0140
  -7.750  -0.6516   0.01711   0.01175  -0.0371   0.8273   0.0145
  -7.500  -0.6273   0.01656   0.01110  -0.0367   0.8221   0.0151
  -7.250  -0.6027   0.01586   0.01030  -0.0363   0.8167   0.0156
  -7.000  -0.5780   0.01529   0.00962  -0.0359   0.8114   0.0160
  -6.750  -0.5526   0.01486   0.00910  -0.0356   0.8065   0.0162
  -6.500  -0.5322   0.01321   0.00734  -0.0347   0.8014   0.0171
  -6.250  -0.5078   0.01267   0.00676  -0.0343   0.7966   0.0177
  -6.000  -0.4822   0.01235   0.00640  -0.0341   0.7922   0.0184
  -5.750  -0.4561   0.01202   0.00605  -0.0339   0.7877   0.0193
  -5.500  -0.4305   0.01164   0.00562  -0.0337   0.7831   0.0200
  -5.250  -0.4051   0.01127   0.00518  -0.0334   0.7787   0.0206
  -5.000  -0.3787   0.01098   0.00485  -0.0332   0.7745   0.0211
  -4.750  -0.3546   0.01033   0.00413  -0.0327   0.7702   0.0222
  -4.500  -0.3292   0.00991   0.00366  -0.0324   0.7662   0.0236
  -4.250  -0.3026   0.00970   0.00342  -0.0323   0.7623   0.0250
  -4.000  -0.2754   0.00947   0.00317  -0.0323   0.7584   0.0266
  -3.750  -0.2481   0.00928   0.00295  -0.0323   0.7543   0.0277
  -3.500  -0.2218   0.00895   0.00256  -0.0321   0.7505   0.0305
  -3.250  -0.1946   0.00875   0.00234  -0.0321   0.7469   0.0340
  -3.000  -0.1669   0.00858   0.00216  -0.0322   0.7434   0.0373
  -2.750  -0.1400   0.00830   0.00195  -0.0322   0.7396   0.0551
  -2.500  -0.1167   0.00751   0.00167  -0.0318   0.7358   0.1974
  -2.250  -0.0956   0.00646   0.00137  -0.0312   0.7322   0.4154
  -2.000  -0.0713   0.00590   0.00129  -0.0308   0.7288   0.5518
  -1.750  -0.0439   0.00577   0.00127  -0.0308   0.7252   0.5908
  -1.500  -0.0160   0.00571   0.00124  -0.0309   0.7217   0.6151
  -1.250   0.0117   0.00567   0.00123  -0.0309   0.7181   0.6397
  -1.000   0.0395   0.00561   0.00124  -0.0309   0.7149   0.6636
  -0.750   0.0675   0.00557   0.00126  -0.0310   0.7113   0.6849
  -0.500   0.0956   0.00554   0.00126  -0.0310   0.7078   0.7002
  -0.250   0.1237   0.00554   0.00126  -0.0311   0.7044   0.7106
   0.000   0.1523   0.00556   0.00126  -0.0314   0.7011   0.7178
   0.250   0.1808   0.00553   0.00128  -0.0316   0.6976   0.7247
   0.500   0.2095   0.00554   0.00130  -0.0318   0.6942   0.7322
   0.750   0.2379   0.00556   0.00132  -0.0320   0.6907   0.7392
   1.000   0.2665   0.00562   0.00136  -0.0322   0.6872   0.7470
   1.250   0.2951   0.00562   0.00141  -0.0324   0.6838   0.7536
   1.500   0.3239   0.00564   0.00144  -0.0327   0.6797   0.7610
   1.750   0.3522   0.00567   0.00147  -0.0329   0.6748   0.7670
   2.000   0.3807   0.00569   0.00151  -0.0330   0.6688   0.7734
   2.250   0.4086   0.00571   0.00149  -0.0331   0.6579   0.7793
   2.500   0.4364   0.00568   0.00148  -0.0331   0.6451   0.7850
   2.750   0.4644   0.00571   0.00150  -0.0332   0.6312   0.7908
   3.000   0.4914   0.00571   0.00149  -0.0331   0.6120   0.7966
   3.250   0.5188   0.00575   0.00152  -0.0331   0.5922   0.8028
   3.500   0.5451   0.00583   0.00156  -0.0329   0.5641   0.8095
   3.750   0.5695   0.00605   0.00166  -0.0324   0.5126   0.8173
   4.000   0.5862   0.00685   0.00206  -0.0307   0.3867   0.8300
   4.250   0.5973   0.00806   0.00283  -0.0278   0.2532   0.8467
   4.500   0.6154   0.00924   0.00339  -0.0268   0.1264   0.8944
   4.750   0.6333   0.01009   0.00388  -0.0254   0.0494   0.9016
   5.000   0.6563   0.01048   0.00420  -0.0247   0.0349   0.9064
   5.250   0.6784   0.01084   0.00455  -0.0237   0.0287   0.9115
   5.500   0.7022   0.01111   0.00484  -0.0231   0.0263   0.9157
   5.750   0.7245   0.01135   0.00512  -0.0222   0.0240   0.9199
   6.000   0.7434   0.01188   0.00570  -0.0207   0.0212   0.9243
   6.250   0.7660   0.01216   0.00600  -0.0199   0.0206   0.9278
   6.500   0.7879   0.01242   0.00629  -0.0189   0.0196   0.9313
   6.750   0.8090   0.01269   0.00661  -0.0179   0.0186   0.9349
   7.000   0.8296   0.01302   0.00696  -0.0168   0.0177   0.9384
   7.250   0.8471   0.01356   0.00752  -0.0152   0.0168   0.9414
   7.500   0.8576   0.01453   0.00859  -0.0125   0.0160   0.9455
   7.750   0.8769   0.01489   0.00900  -0.0112   0.0157   0.9487
   8.000   0.8951   0.01528   0.00945  -0.0097   0.0154   0.9517
   8.250   0.9097   0.01579   0.01001  -0.0077   0.0151   0.9548
   8.500   0.9242   0.01644   0.01073  -0.0057   0.0148   0.9587
   8.750   0.9426   0.01699   0.01134  -0.0046   0.0144   0.9631
   9.000   0.9628   0.01774   0.01216  -0.0040   0.0140   0.9675
   9.250   0.9867   0.01845   0.01293  -0.0043   0.0136   0.9725
   9.500   1.0139   0.01902   0.01352  -0.0052   0.0130   0.9800
   9.750   1.0324   0.01993   0.01446  -0.0046   0.0126   1.0000
  10.000   1.0457   0.02118   0.01578  -0.0030   0.0123   1.0000
  10.250   1.0626   0.02344   0.01820  -0.0019   0.0119   1.0000
  10.500   1.0781   0.02424   0.01909  -0.0006   0.0118   1.0000
  10.750   1.0929   0.02507   0.02002   0.0008   0.0116   1.0000
  11.000   1.1076   0.02626   0.02132   0.0020   0.0115   1.0000
  11.250   1.1210   0.02763   0.02282   0.0034   0.0114   1.0000
  11.500   1.1327   0.02896   0.02428   0.0049   0.0111   1.0000
  11.750   1.1431   0.03010   0.02553   0.0063   0.0109   1.0000
  12.000   1.1512   0.03172   0.02730   0.0079   0.0107   1.0000
  12.250   1.1587   0.03309   0.02880   0.0094   0.0105   1.0000
  12.500   1.1665   0.03414   0.02991   0.0108   0.0101   1.0000
  12.750   1.1713   0.03580   0.03169   0.0122   0.0100   1.0000
  13.000   1.1741   0.03769   0.03371   0.0136   0.0099   1.0000
  13.250   1.1765   0.03948   0.03561   0.0148   0.0097   1.0000
  13.500   1.1807   0.04096   0.03716   0.0156   0.0096   1.0000
  13.750   1.1801   0.04323   0.03956   0.0166   0.0095   1.0000
  14.000   1.1771   0.04582   0.04227   0.0174   0.0094   1.0000
  14.250   1.1668   0.04949   0.04614   0.0181   0.0094   1.0000
  14.500   1.1655   0.05188   0.04858   0.0182   0.0091   1.0000
  14.750   1.1503   0.05633   0.05322   0.0181   0.0091   1.0000
  15.000   1.1341   0.06112   0.05819   0.0174   0.0090   1.0000
  15.250   1.1160   0.06666   0.06394   0.0161   0.0091   1.0000
  15.500   1.0969   0.07264   0.07008   0.0139   0.0090   1.0000
  15.750   1.0693   0.08068   0.07832   0.0102   0.0090   1.0000
  16.000   1.0554   0.08717   0.08495   0.0067   0.0091   1.0000
  16.250   1.0238   0.09786   0.09583   0.0003   0.0090   1.0000
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