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NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(1)-212 (naca651212-il)
Reynolds number: 50,000
Max Cl/Cd: 28.4 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca651212-il-50000-n5.txt
Download as CSV file: xf-naca651212-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-212                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4086   0.12586   0.11887  -0.0267   1.0000   0.0709
 -12.250  -0.4087   0.12168   0.11470  -0.0283   1.0000   0.0672
 -11.750  -0.5294   0.11830   0.11085  -0.0289   1.0000   0.0604
 -11.500  -0.5256   0.11400   0.10657  -0.0300   1.0000   0.0592
 -11.250  -0.5250   0.10929   0.10190  -0.0319   1.0000   0.0579
 -11.000  -0.5272   0.10412   0.09677  -0.0344   1.0000   0.0567
 -10.750  -0.5324   0.09824   0.09095  -0.0378   1.0000   0.0555
 -10.500  -0.5420   0.09126   0.08402  -0.0424   1.0000   0.0542
 -10.250  -0.5625   0.08371   0.07648  -0.0479   1.0000   0.0527
 -10.000  -0.5932   0.07715   0.06987  -0.0521   1.0000   0.0513
  -9.500  -0.6523   0.06968   0.06202  -0.0512   1.0000   0.0497
  -9.250  -0.6590   0.06625   0.05842  -0.0500   1.0000   0.0495
  -9.000  -0.6654   0.06302   0.05501  -0.0483   1.0000   0.0495
  -8.750  -0.6718   0.06005   0.05178  -0.0461   1.0000   0.0496
  -8.500  -0.6737   0.05686   0.04848  -0.0441   1.0000   0.0502
  -8.250  -0.6694   0.05427   0.04588  -0.0423   1.0000   0.0515
  -8.000  -0.6675   0.05192   0.04339  -0.0400   1.0000   0.0525
  -7.750  -0.6662   0.04956   0.04081  -0.0373   1.0000   0.0533
  -7.500  -0.6639   0.04717   0.03814  -0.0345   1.0000   0.0537
  -7.250  -0.6594   0.04481   0.03546  -0.0318   1.0000   0.0539
  -7.000  -0.6523   0.04257   0.03289  -0.0293   1.0000   0.0543
  -6.750  -0.6426   0.04046   0.03046  -0.0269   1.0000   0.0548
  -6.500  -0.6305   0.03849   0.02815  -0.0248   1.0000   0.0556
  -6.250  -0.6170   0.03682   0.02618  -0.0229   1.0000   0.0575
  -6.000  -0.6018   0.03531   0.02433  -0.0210   1.0000   0.0599
  -5.750  -0.5849   0.03399   0.02264  -0.0192   1.0000   0.0618
  -5.500  -0.5659   0.03235   0.02102  -0.0178   1.0000   0.0635
  -5.250  -0.5365   0.03099   0.01956  -0.0181   0.9965   0.0661
  -5.000  -0.5035   0.02990   0.01831  -0.0190   0.9912   0.0712
  -4.750  -0.4713   0.02886   0.01716  -0.0200   0.9858   0.0772
  -4.500  -0.4427   0.02784   0.01606  -0.0207   0.9792   0.0835
  -4.250  -0.4137   0.02685   0.01494  -0.0217   0.9730   0.0929
  -4.000  -0.3871   0.02579   0.01392  -0.0225   0.9660   0.1103
  -3.750  -0.3622   0.02427   0.01276  -0.0234   0.9593   0.1585
  -3.500  -0.3566   0.02201   0.01304  -0.0196   0.9522   0.5792
  -3.000  -0.3254   0.02473   0.01594  -0.0072   0.9384   0.7837
  -2.750  -0.2938   0.02609   0.01712  -0.0036   0.9350   0.8340
  -2.500  -0.2644   0.02605   0.01681  -0.0041   0.9283   0.8436
  -2.250  -0.2307   0.02596   0.01643  -0.0058   0.9228   0.8526
  -2.000  -0.2004   0.02585   0.01609  -0.0070   0.9170   0.8617
  -1.750  -0.1697   0.02578   0.01583  -0.0081   0.9107   0.8691
  -1.500  -0.1364   0.02569   0.01554  -0.0100   0.9058   0.8776
  -1.250  -0.1059   0.02566   0.01537  -0.0111   0.8996   0.8845
  -1.000  -0.0779   0.02559   0.01518  -0.0120   0.8935   0.8934
  -0.750  -0.0341   0.02560   0.01504  -0.0156   0.8901   0.8987
  -0.500  -0.0148   0.02559   0.01497  -0.0150   0.8823   0.9085
  -0.250   0.0258   0.02562   0.01491  -0.0181   0.8779   0.9143
   0.000   0.0556   0.02564   0.01487  -0.0193   0.8725   0.9229
   0.250   0.0903   0.02572   0.01493  -0.0215   0.8666   0.9296
   0.500   0.1255   0.02576   0.01494  -0.0237   0.8618   0.9375
   0.750   0.1644   0.02587   0.01506  -0.0267   0.8568   0.9437
   1.000   0.1965   0.02600   0.01521  -0.0286   0.8506   0.9521
   1.250   0.2415   0.02608   0.01535  -0.0327   0.8466   0.9575
   1.500   0.2761   0.02626   0.01559  -0.0351   0.8407   0.9655
   1.750   0.3140   0.02643   0.01584  -0.0380   0.8348   0.9731
   2.000   0.3577   0.02652   0.01606  -0.0418   0.8306   0.9794
   2.250   0.3899   0.02681   0.01647  -0.0440   0.8233   0.9892
   2.500   0.4295   0.02697   0.01679  -0.0472   0.8177   0.9980
   2.750   0.4405   0.02731   0.01723  -0.0452   0.8092   1.0000
   3.000   0.4557   0.02751   0.01754  -0.0437   0.8015   1.0000
   3.250   0.4558   0.02791   0.01800  -0.0397   0.7910   1.0000
   3.500   0.4817   0.02801   0.01824  -0.0396   0.7847   1.0000
   3.750   0.4825   0.02844   0.01874  -0.0357   0.7731   1.0000
   4.000   0.4959   0.02878   0.01922  -0.0337   0.7630   1.0000
   4.250   0.5269   0.02882   0.01946  -0.0340   0.7553   1.0000
   4.500   0.5425   0.02916   0.01996  -0.0322   0.7430   1.0000
   4.750   0.5651   0.02928   0.02029  -0.0312   0.7304   1.0000
   5.000   0.6068   0.02771   0.01906  -0.0302   0.7052   1.0000
   5.250   0.6406   0.02342   0.01475  -0.0231   0.6118   1.0000
   5.500   0.6514   0.02294   0.01428  -0.0189   0.5360   1.0000
   5.750   0.6590   0.02350   0.01317  -0.0133   0.2732   1.0000
   6.000   0.6509   0.02596   0.01461  -0.0093   0.1524   1.0000
   6.250   0.6546   0.02779   0.01605  -0.0067   0.1134   1.0000
   6.500   0.6629   0.02927   0.01740  -0.0044   0.0981   1.0000
   6.750   0.6738   0.03063   0.01873  -0.0025   0.0874   1.0000
   7.000   0.6868   0.03203   0.02006  -0.0010   0.0793   1.0000
   7.250   0.7073   0.03328   0.02148   0.0001   0.0737   1.0000
   7.500   0.7337   0.03467   0.02289   0.0004   0.0680   1.0000
   7.750   0.7735   0.03617   0.02460  -0.0007   0.0619   1.0000
   8.000   0.8142   0.03804   0.02663  -0.0019   0.0584   1.0000
   8.250   0.8502   0.04035   0.02906  -0.0030   0.0558   1.0000
   8.500   0.8782   0.04288   0.03186  -0.0032   0.0534   1.0000
   8.750   0.8991   0.04526   0.03469  -0.0025   0.0513   1.0000
   9.000   0.9169   0.04800   0.03783  -0.0016   0.0498   1.0000
   9.250   0.9308   0.05103   0.04126  -0.0004   0.0491   1.0000
   9.500   0.9399   0.05417   0.04479   0.0011   0.0487   1.0000
   9.750   0.9441   0.05743   0.04843   0.0028   0.0484   1.0000
  10.000   0.9435   0.06081   0.05221   0.0048   0.0483   1.0000
  10.250   0.9381   0.06420   0.05592   0.0068   0.0483   1.0000
  10.500   0.9268   0.06748   0.05947   0.0090   0.0482   1.0000
  10.750   0.9122   0.07101   0.06323   0.0107   0.0481   1.0000
  11.000   0.8945   0.07496   0.06740   0.0116   0.0483   1.0000
  11.250   0.8742   0.07947   0.07211   0.0114   0.0486   1.0000
  11.500   0.8518   0.08470   0.07751   0.0100   0.0490   1.0000
  11.750   0.8273   0.09093   0.08384   0.0072   0.0495   1.0000
  12.000   0.8028   0.09825   0.09126   0.0030   0.0502   1.0000
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