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NACA 0012-64 (naca001264-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 0012-64 (naca001264-il)
Reynolds number: 100,000
Max Cl/Cd: 32.2 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001264-il-100000-n5.txt
Download as CSV file: xf-naca001264-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0012-64                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7594   0.08725   0.08155  -0.0367   1.0000   0.0445
 -12.500  -0.8158   0.07417   0.06826  -0.0454   1.0000   0.0436
 -12.250  -0.8538   0.06691   0.06076  -0.0479   1.0000   0.0433
 -12.000  -0.8824   0.06190   0.05553  -0.0476   1.0000   0.0433
 -11.750  -0.9053   0.05803   0.05140  -0.0456   1.0000   0.0435
 -11.500  -0.9245   0.05480   0.04793  -0.0425   1.0000   0.0439
 -11.250  -0.9408   0.05201   0.04487  -0.0384   1.0000   0.0443
 -11.000  -0.9520   0.04924   0.04179  -0.0345   1.0000   0.0448
 -10.750  -0.9583   0.04654   0.03873  -0.0309   1.0000   0.0455
 -10.500  -0.9616   0.04409   0.03587  -0.0272   1.0000   0.0465
 -10.250  -0.9618   0.04190   0.03326  -0.0236   1.0000   0.0475
 -10.000  -0.9504   0.04017   0.03149  -0.0218   1.0000   0.0485
  -9.750  -0.9395   0.03872   0.02993  -0.0197   1.0000   0.0495
  -9.500  -0.9281   0.03720   0.02823  -0.0175   1.0000   0.0505
  -9.250  -0.9156   0.03569   0.02653  -0.0153   1.0000   0.0515
  -9.000  -0.9024   0.03434   0.02497  -0.0131   1.0000   0.0531
  -8.750  -0.8881   0.03303   0.02342  -0.0111   1.0000   0.0548
  -8.500  -0.8723   0.03174   0.02186  -0.0091   1.0000   0.0562
  -8.250  -0.8545   0.03037   0.02037  -0.0076   1.0000   0.0574
  -8.000  -0.8370   0.02919   0.01918  -0.0061   1.0000   0.0587
  -7.750  -0.8198   0.02821   0.01814  -0.0044   1.0000   0.0601
  -7.500  -0.8029   0.02734   0.01722  -0.0026   1.0000   0.0621
  -7.250  -0.7859   0.02653   0.01631  -0.0008   1.0000   0.0646
  -7.000  -0.7685   0.02574   0.01539   0.0010   1.0000   0.0670
  -6.750  -0.7522   0.02483   0.01446   0.0029   1.0000   0.0691
  -6.500  -0.7368   0.02405   0.01370   0.0049   1.0000   0.0715
  -6.250  -0.7212   0.02336   0.01299   0.0070   1.0000   0.0745
  -6.000  -0.7054   0.02272   0.01228   0.0091   1.0000   0.0781
  -5.750  -0.6906   0.02204   0.01161   0.0113   1.0000   0.0826
  -5.500  -0.6751   0.02146   0.01103   0.0133   1.0000   0.0890
  -5.250  -0.6594   0.02087   0.01046   0.0153   1.0000   0.0966
  -5.000  -0.6430   0.02035   0.00993   0.0172   1.0000   0.1067
  -4.750  -0.6265   0.01980   0.00946   0.0191   1.0000   0.1195
  -4.500  -0.6094   0.01930   0.00904   0.0208   1.0000   0.1381
  -4.250  -0.5921   0.01879   0.00868   0.0224   1.0000   0.1659
  -4.000  -0.5694   0.01818   0.00832   0.0227   0.9983   0.2109
  -3.750  -0.5415   0.01729   0.00794   0.0218   0.9946   0.2987
  -3.500  -0.5188   0.01612   0.00769   0.0221   0.9904   0.4614
  -3.250  -0.4930   0.01553   0.00784   0.0228   0.9866   0.6114
  -3.000  -0.4604   0.01552   0.00808   0.0224   0.9833   0.6925
  -2.750  -0.4296   0.01562   0.00826   0.0223   0.9786   0.7419
  -2.500  -0.3952   0.01583   0.00849   0.0215   0.9746   0.7803
  -2.250  -0.3603   0.01614   0.00879   0.0207   0.9710   0.8151
  -2.000  -0.3272   0.01647   0.00910   0.0203   0.9661   0.8422
  -1.750  -0.2910   0.01679   0.00935   0.0191   0.9621   0.8641
  -1.500  -0.2484   0.01729   0.00982   0.0169   0.9598   0.8850
  -1.250  -0.2077   0.01770   0.01017   0.0148   0.9562   0.9009
  -1.000  -0.1691   0.01786   0.01027   0.0126   0.9512   0.9107
  -0.750  -0.1256   0.01795   0.01031   0.0093   0.9476   0.9166
  -0.500  -0.0789   0.01803   0.01035   0.0052   0.9448   0.9216
  -0.250  -0.0476   0.01805   0.01035   0.0043   0.9372   0.9300
   0.000   0.0000   0.01807   0.01037   0.0000   0.9333   0.9333
   0.250   0.0475   0.01805   0.01035  -0.0043   0.9300   0.9372
   0.500   0.0789   0.01803   0.01035  -0.0052   0.9216   0.9448
   0.750   0.1256   0.01795   0.01031  -0.0093   0.9166   0.9476
   1.000   0.1691   0.01786   0.01027  -0.0127   0.9107   0.9512
   1.250   0.2076   0.01770   0.01016  -0.0148   0.9009   0.9562
   1.500   0.2483   0.01729   0.00982  -0.0169   0.8850   0.9598
   1.750   0.2910   0.01679   0.00935  -0.0191   0.8642   0.9621
   2.000   0.3272   0.01647   0.00909  -0.0203   0.8422   0.9661
   2.250   0.3603   0.01614   0.00878  -0.0207   0.8152   0.9711
   2.500   0.3952   0.01583   0.00849  -0.0215   0.7804   0.9746
   2.750   0.4296   0.01562   0.00826  -0.0223   0.7421   0.9786
   3.000   0.4603   0.01552   0.00807  -0.0224   0.6925   0.9833
   3.250   0.4930   0.01553   0.00784  -0.0228   0.6115   0.9866
   3.500   0.5188   0.01611   0.00769  -0.0221   0.4615   0.9905
   3.750   0.5415   0.01729   0.00794  -0.0219   0.2985   0.9946
   4.000   0.5694   0.01817   0.00832  -0.0228   0.2109   0.9984
   4.250   0.5920   0.01878   0.00868  -0.0223   0.1660   1.0000
   4.500   0.6093   0.01929   0.00904  -0.0207   0.1381   1.0000
   4.750   0.6264   0.01979   0.00946  -0.0190   0.1195   1.0000
   5.000   0.6429   0.02034   0.00992  -0.0172   0.1068   1.0000
   5.250   0.6593   0.02087   0.01045  -0.0153   0.0967   1.0000
   5.500   0.6750   0.02146   0.01103  -0.0133   0.0890   1.0000
   5.750   0.6905   0.02203   0.01161  -0.0112   0.0826   1.0000
   6.000   0.7053   0.02271   0.01228  -0.0091   0.0781   1.0000
   6.250   0.7211   0.02336   0.01299  -0.0070   0.0745   1.0000
   6.500   0.7367   0.02405   0.01370  -0.0049   0.0715   1.0000
   6.750   0.7521   0.02483   0.01446  -0.0029   0.0691   1.0000
   7.000   0.7684   0.02574   0.01539  -0.0010   0.0670   1.0000
   7.250   0.7858   0.02652   0.01631   0.0009   0.0646   1.0000
   7.500   0.8029   0.02733   0.01721   0.0027   0.0621   1.0000
   7.750   0.8197   0.02820   0.01814   0.0044   0.0601   1.0000
   8.000   0.8369   0.02919   0.01918   0.0061   0.0587   1.0000
   8.250   0.8545   0.03036   0.02036   0.0076   0.0574   1.0000
   8.500   0.8723   0.03173   0.02186   0.0091   0.0562   1.0000
   8.750   0.8880   0.03302   0.02342   0.0111   0.0548   1.0000
   9.000   0.9023   0.03434   0.02496   0.0132   0.0531   1.0000
   9.250   0.9156   0.03568   0.02653   0.0153   0.0515   1.0000
   9.500   0.9281   0.03719   0.02823   0.0175   0.0505   1.0000
   9.750   0.9395   0.03872   0.02993   0.0197   0.0495   1.0000
  10.000   0.9505   0.04016   0.03148   0.0218   0.0485   1.0000
  10.250   0.9619   0.04190   0.03326   0.0236   0.0475   1.0000
  10.500   0.9618   0.04409   0.03587   0.0272   0.0465   1.0000
  10.750   0.9584   0.04655   0.03874   0.0309   0.0455   1.0000
  11.000   0.9522   0.04925   0.04180   0.0345   0.0448   1.0000
  11.250   0.9412   0.05202   0.04489   0.0383   0.0443   1.0000
  11.500   0.9249   0.05483   0.04796   0.0424   0.0439   1.0000
  11.750   0.9058   0.05805   0.05143   0.0455   0.0435   1.0000
  12.000   0.8829   0.06194   0.05557   0.0474   0.0433   1.0000
  12.250   0.8543   0.06698   0.06083   0.0477   0.0433   1.0000
  12.500   0.8162   0.07428   0.06837   0.0451   0.0436   1.0000
  12.750   0.7593   0.08756   0.08187   0.0363   0.0446   1.0000
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