Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 2412 (naca2412-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 2412 (naca2412-il)
Reynolds number: 50,000
Max Cl/Cd: 34.64 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2412-il-50000-n5.txt
Download as CSV file: xf-naca2412-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2412                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5477   0.09827   0.09043  -0.0346   1.0000   0.0782
 -10.500  -0.5580   0.09162   0.08383  -0.0383   1.0000   0.0780
 -10.250  -0.5767   0.08302   0.07526  -0.0440   1.0000   0.0778
 -10.000  -0.6041   0.07479   0.06704  -0.0499   1.0000   0.0775
  -9.750  -0.6334   0.06891   0.06111  -0.0518   1.0000   0.0773
  -9.500  -0.6585   0.06345   0.05549  -0.0524   1.0000   0.0774
  -9.250  -0.6787   0.05847   0.05023  -0.0517   1.0000   0.0779
  -9.000  -0.6907   0.05416   0.04558  -0.0503   1.0000   0.0788
  -8.750  -0.6811   0.05224   0.04364  -0.0490   1.0000   0.0806
  -8.500  -0.6748   0.04986   0.04112  -0.0474   1.0000   0.0823
  -8.250  -0.6699   0.04702   0.03802  -0.0458   1.0000   0.0838
  -8.000  -0.6633   0.04417   0.03483  -0.0442   1.0000   0.0854
  -7.750  -0.6545   0.04150   0.03178  -0.0425   1.0000   0.0876
  -7.500  -0.6442   0.03894   0.02866  -0.0408   1.0000   0.0908
  -7.250  -0.6286   0.03734   0.02702  -0.0395   1.0000   0.0936
  -7.000  -0.6122   0.03582   0.02538  -0.0381   1.0000   0.0968
  -6.750  -0.5952   0.03412   0.02341  -0.0367   1.0000   0.1002
  -6.500  -0.5772   0.03246   0.02133  -0.0353   1.0000   0.1047
  -6.250  -0.5590   0.03135   0.02033  -0.0341   1.0000   0.1095
  -6.000  -0.5399   0.03021   0.01901  -0.0329   1.0000   0.1160
  -5.750  -0.5202   0.02904   0.01774  -0.0317   1.0000   0.1222
  -5.500  -0.5006   0.02814   0.01678  -0.0305   1.0000   0.1308
  -5.250  -0.4808   0.02726   0.01591  -0.0294   1.0000   0.1404
  -5.000  -0.4605   0.02648   0.01506  -0.0284   1.0000   0.1526
  -4.750  -0.4401   0.02578   0.01435  -0.0274   1.0000   0.1669
  -4.500  -0.4197   0.02517   0.01378  -0.0264   1.0000   0.1837
  -4.250  -0.3989   0.02461   0.01327  -0.0256   1.0000   0.2032
  -4.000  -0.3774   0.02410   0.01278  -0.0249   1.0000   0.2269
  -3.750  -0.3560   0.02364   0.01243  -0.0242   1.0000   0.2532
  -3.500  -0.3346   0.02321   0.01211  -0.0236   1.0000   0.2838
  -3.250  -0.3132   0.02282   0.01182  -0.0230   1.0000   0.3187
  -3.000  -0.2815   0.02242   0.01161  -0.0243   0.9954   0.3657
  -2.750  -0.2435   0.02203   0.01145  -0.0268   0.9869   0.4255
  -2.500  -0.2072   0.02166   0.01141  -0.0287   0.9780   0.4958
  -2.250  -0.1724   0.02136   0.01146  -0.0299   0.9689   0.5795
  -2.000  -0.1388   0.02111   0.01156  -0.0303   0.9597   0.6724
  -1.750  -0.1084   0.02097   0.01172  -0.0296   0.9492   0.7671
  -1.500  -0.0638   0.02102   0.01188  -0.0315   0.9411   0.8665
  -1.250  -0.0006   0.02114   0.01188  -0.0379   0.9339   0.9476
  -1.000   0.0749   0.02117   0.01169  -0.0476   0.9291   1.0000
  -0.750   0.1092   0.02114   0.01148  -0.0495   0.9152   1.0000
  -0.500   0.1437   0.02113   0.01132  -0.0513   0.9017   1.0000
  -0.250   0.1775   0.02111   0.01117  -0.0527   0.8883   1.0000
   0.000   0.2112   0.02110   0.01104  -0.0540   0.8752   1.0000
   0.250   0.2457   0.02106   0.01091  -0.0553   0.8626   1.0000
   0.500   0.2790   0.02102   0.01079  -0.0562   0.8497   1.0000
   0.750   0.3077   0.02104   0.01074  -0.0563   0.8350   1.0000
   1.000   0.3361   0.02107   0.01071  -0.0562   0.8203   1.0000
   1.250   0.3643   0.02111   0.01070  -0.0560   0.8056   1.0000
   1.500   0.3924   0.02116   0.01071  -0.0558   0.7908   1.0000
   1.750   0.4206   0.02122   0.01073  -0.0555   0.7761   1.0000
   2.000   0.4485   0.02128   0.01076  -0.0552   0.7613   1.0000
   2.250   0.4763   0.02135   0.01081  -0.0548   0.7464   1.0000
   2.500   0.5037   0.02144   0.01088  -0.0543   0.7313   1.0000
   2.750   0.5306   0.02155   0.01097  -0.0537   0.7159   1.0000
   3.000   0.5571   0.02167   0.01108  -0.0530   0.7002   1.0000
   3.250   0.5831   0.02182   0.01124  -0.0522   0.6841   1.0000
   3.500   0.6086   0.02200   0.01141  -0.0514   0.6677   1.0000
   3.750   0.6337   0.02220   0.01163  -0.0505   0.6509   1.0000
   4.000   0.6585   0.02242   0.01186  -0.0495   0.6338   1.0000
   4.250   0.6831   0.02266   0.01212  -0.0485   0.6163   1.0000
   4.500   0.7074   0.02291   0.01241  -0.0475   0.5985   1.0000
   4.750   0.7317   0.02318   0.01269  -0.0465   0.5805   1.0000
   5.000   0.7558   0.02346   0.01300  -0.0454   0.5622   1.0000
   5.250   0.7799   0.02375   0.01332  -0.0443   0.5435   1.0000
   5.500   0.8039   0.02404   0.01362  -0.0432   0.5245   1.0000
   5.750   0.8250   0.02445   0.01408  -0.0418   0.5030   1.0000
   6.000   0.8459   0.02479   0.01443  -0.0402   0.4793   1.0000
   6.250   0.8652   0.02516   0.01482  -0.0385   0.4534   1.0000
   6.500   0.8841   0.02552   0.01513  -0.0366   0.4268   1.0000
   6.750   0.9011   0.02602   0.01566  -0.0347   0.3983   1.0000
   7.000   0.9177   0.02657   0.01622  -0.0327   0.3695   1.0000
   7.250   0.9332   0.02719   0.01680  -0.0307   0.3394   1.0000
   7.500   0.9472   0.02794   0.01747  -0.0286   0.3077   1.0000
   7.750   0.9597   0.02884   0.01826  -0.0264   0.2758   1.0000
   8.000   0.9709   0.02991   0.01920  -0.0242   0.2453   1.0000
   8.250   0.9810   0.03115   0.02031  -0.0220   0.2177   1.0000
   8.500   0.9904   0.03251   0.02155  -0.0199   0.1945   1.0000
   8.750   0.9994   0.03396   0.02289  -0.0178   0.1752   1.0000
   9.000   1.0085   0.03543   0.02431  -0.0157   0.1597   1.0000
   9.250   1.0168   0.03694   0.02574  -0.0136   0.1475   1.0000
   9.500   1.0277   0.03846   0.02736  -0.0119   0.1363   1.0000
   9.750   1.0397   0.04004   0.02899  -0.0103   0.1276   1.0000
  10.000   1.0506   0.04161   0.03054  -0.0087   0.1203   1.0000
  10.250   1.0639   0.04329   0.03237  -0.0073   0.1133   1.0000
  10.500   1.0779   0.04493   0.03405  -0.0061   0.1080   1.0000
  10.750   1.0938   0.04673   0.03595  -0.0050   0.1033   1.0000
  11.000   1.1055   0.04869   0.03815  -0.0038   0.0986   1.0000
  11.250   1.1177   0.05050   0.04000  -0.0027   0.0946   1.0000
  11.500   1.1318   0.05263   0.04222  -0.0017   0.0913   1.0000
  11.750   1.1370   0.05529   0.04523  -0.0004   0.0886   1.0000
  12.000   1.1398   0.05797   0.04817   0.0008   0.0859   1.0000
  12.250   1.1430   0.06051   0.05089   0.0019   0.0833   1.0000
  12.500   1.1537   0.06269   0.05305   0.0026   0.0807   1.0000
  12.750   1.1467   0.06631   0.05694   0.0034   0.0793   1.0000
  13.000   1.1314   0.07072   0.06171   0.0037   0.0784   1.0000
  13.250   1.1122   0.07582   0.06713   0.0031   0.0776   1.0000
  13.500   1.0885   0.08185   0.07346   0.0014   0.0772   1.0000
  13.750   1.0588   0.08931   0.08118  -0.0017   0.0771   1.0000
  14.000   1.0209   0.09902   0.09111  -0.0070   0.0775   1.0000
  14.250   0.9730   0.11220   0.10447  -0.0150   0.0783   1.0000
<< Back to NACA 2412 (naca2412-il)

Polar data table (+)

Polar graphs


<< Back to NACA 2412 (naca2412-il)