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NACA 2415 (n2415-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 2415 (n2415-il)
Reynolds number: 100,000
Max Cl/Cd: 46.59 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n2415-il-100000.txt
Download as CSV file: xf-n2415-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2415                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6507   0.07798   0.07213  -0.0617   1.0000   0.1023
 -11.500  -0.6802   0.07054   0.06463  -0.0652   1.0000   0.1016
 -11.250  -0.7174   0.06446   0.05847  -0.0663   1.0000   0.1008
 -11.000  -0.7559   0.06033   0.05425  -0.0633   1.0000   0.1002
 -10.750  -0.7902   0.05646   0.05019  -0.0593   1.0000   0.0999
 -10.500  -0.8179   0.05276   0.04623  -0.0550   1.0000   0.1001
 -10.250  -0.8397   0.04933   0.04246  -0.0505   1.0000   0.1007
 -10.000  -0.8564   0.04619   0.03887  -0.0461   1.0000   0.1017
  -9.750  -0.8595   0.04342   0.03584  -0.0428   1.0000   0.1032
  -9.500  -0.8450   0.04206   0.03458  -0.0411   1.0000   0.1055
  -9.250  -0.8361   0.04057   0.03300  -0.0388   1.0000   0.1081
  -9.000  -0.8320   0.03863   0.03076  -0.0359   1.0000   0.1109
  -8.750  -0.8294   0.03657   0.02818  -0.0327   1.0000   0.1137
  -8.500  -0.8155   0.03484   0.02646  -0.0310   1.0000   0.1166
  -8.250  -0.8003   0.03383   0.02543  -0.0293   1.0000   0.1204
  -8.000  -0.7879   0.03250   0.02382  -0.0272   1.0000   0.1247
  -7.750  -0.7732   0.03099   0.02214  -0.0255   1.0000   0.1289
  -7.500  -0.7559   0.03015   0.02134  -0.0241   1.0000   0.1336
  -7.250  -0.7399   0.02918   0.02007  -0.0224   1.0000   0.1395
  -7.000  -0.7213   0.02811   0.01909  -0.0212   1.0000   0.1449
  -6.750  -0.7031   0.02742   0.01828  -0.0199   1.0000   0.1518
  -6.500  -0.6838   0.02653   0.01737  -0.0189   1.0000   0.1588
  -6.250  -0.6645   0.02597   0.01675  -0.0178   1.0000   0.1672
  -6.000  -0.6448   0.02527   0.01609  -0.0168   1.0000   0.1757
  -5.750  -0.6254   0.02483   0.01547  -0.0158   1.0000   0.1862
  -5.500  -0.6056   0.02427   0.01511  -0.0150   1.0000   0.1963
  -5.250  -0.5858   0.02379   0.01464  -0.0141   1.0000   0.2081
  -5.000  -0.5661   0.02343   0.01425  -0.0133   1.0000   0.2216
  -4.750  -0.5279   0.02309   0.01401  -0.0159   0.9951   0.2406
  -4.500  -0.4845   0.02281   0.01385  -0.0195   0.9876   0.2635
  -4.250  -0.4395   0.02261   0.01366  -0.0233   0.9805   0.2910
  -4.000  -0.3989   0.02228   0.01354  -0.0262   0.9718   0.3178
  -3.750  -0.3591   0.02201   0.01337  -0.0290   0.9630   0.3485
  -3.500  -0.3148   0.02174   0.01324  -0.0324   0.9555   0.3840
  -3.250  -0.2801   0.02141   0.01313  -0.0340   0.9449   0.4178
  -3.000  -0.2369   0.02111   0.01304  -0.0370   0.9374   0.4597
  -2.750  -0.2030   0.02081   0.01298  -0.0382   0.9265   0.5007
  -2.500  -0.1674   0.02054   0.01294  -0.0394   0.9168   0.5474
  -2.250  -0.1284   0.02023   0.01289  -0.0411   0.9081   0.5999
  -2.000  -0.0976   0.02003   0.01291  -0.0411   0.8971   0.6521
  -1.750  -0.0560   0.01974   0.01284  -0.0426   0.8900   0.7094
  -1.500  -0.0280   0.01967   0.01296  -0.0415   0.8786   0.7578
  -1.250   0.0136   0.01948   0.01286  -0.0424   0.8721   0.8078
  -1.000   0.0433   0.01955   0.01300  -0.0412   0.8608   0.8485
  -0.750   0.0916   0.01945   0.01288  -0.0432   0.8544   0.8852
  -0.500   0.1401   0.01954   0.01293  -0.0458   0.8447   0.9145
  -0.250   0.2043   0.01938   0.01269  -0.0513   0.8376   0.9370
   0.000   0.2751   0.01918   0.01241  -0.0586   0.8291   0.9537
   0.250   0.3450   0.01880   0.01195  -0.0660   0.8189   0.9691
   0.500   0.4104   0.01843   0.01151  -0.0730   0.8060   0.9846
   0.750   0.4757   0.01790   0.01090  -0.0800   0.7934   0.9992
   1.000   0.4986   0.01760   0.01050  -0.0793   0.7794   1.0000
   1.250   0.5163   0.01750   0.01034  -0.0778   0.7635   1.0000
   1.500   0.5349   0.01745   0.01022  -0.0763   0.7482   1.0000
   1.750   0.5544   0.01742   0.01012  -0.0749   0.7339   1.0000
   2.000   0.5761   0.01736   0.00997  -0.0736   0.7208   1.0000
   2.250   0.5971   0.01737   0.00990  -0.0723   0.7070   1.0000
   2.500   0.6159   0.01750   0.00999  -0.0706   0.6922   1.0000
   2.750   0.6362   0.01763   0.01005  -0.0691   0.6783   1.0000
   3.000   0.6588   0.01771   0.01005  -0.0679   0.6654   1.0000
   3.250   0.6808   0.01782   0.01008  -0.0666   0.6519   1.0000
   3.500   0.7000   0.01804   0.01028  -0.0649   0.6373   1.0000
   3.750   0.7210   0.01824   0.01044  -0.0634   0.6234   1.0000
   4.000   0.7441   0.01840   0.01051  -0.0622   0.6102   1.0000
   4.250   0.7669   0.01857   0.01060  -0.0610   0.5965   1.0000
   4.500   0.7864   0.01883   0.01088  -0.0593   0.5816   1.0000
   4.750   0.8072   0.01909   0.01110  -0.0578   0.5671   1.0000
   5.000   0.8292   0.01932   0.01127  -0.0564   0.5527   1.0000
   5.250   0.8524   0.01952   0.01139  -0.0552   0.5384   1.0000
   5.500   0.8741   0.01975   0.01156  -0.0538   0.5232   1.0000
   5.750   0.8937   0.02003   0.01183  -0.0520   0.5071   1.0000
   6.000   0.9138   0.02031   0.01211  -0.0504   0.4911   1.0000
   6.250   0.9341   0.02059   0.01237  -0.0488   0.4748   1.0000
   6.500   0.9545   0.02088   0.01262  -0.0472   0.4583   1.0000
   6.750   0.9745   0.02117   0.01289  -0.0456   0.4414   1.0000
   7.000   0.9941   0.02148   0.01316  -0.0439   0.4240   1.0000
   7.250   1.0130   0.02179   0.01344  -0.0421   0.4061   1.0000
   7.500   1.0311   0.02213   0.01375  -0.0403   0.3877   1.0000
   7.750   1.0484   0.02251   0.01408  -0.0383   0.3688   1.0000
   8.000   1.0649   0.02292   0.01444  -0.0363   0.3496   1.0000
   8.250   1.0807   0.02341   0.01485  -0.0342   0.3303   1.0000
   8.500   1.0960   0.02398   0.01531  -0.0321   0.3110   1.0000
   8.750   1.1093   0.02465   0.01592  -0.0297   0.2914   1.0000
   9.000   1.1215   0.02539   0.01663  -0.0273   0.2721   1.0000
   9.250   1.1333   0.02621   0.01739  -0.0249   0.2538   1.0000
   9.500   1.1446   0.02711   0.01822  -0.0224   0.2367   1.0000
   9.750   1.1555   0.02808   0.01912  -0.0201   0.2209   1.0000
  10.000   1.1664   0.02912   0.02009  -0.0177   0.2066   1.0000
  10.250   1.1771   0.03020   0.02106  -0.0155   0.1938   1.0000
  10.500   1.1872   0.03129   0.02209  -0.0131   0.1821   1.0000
  10.750   1.1956   0.03250   0.02336  -0.0107   0.1713   1.0000
  11.000   1.2077   0.03382   0.02464  -0.0089   0.1618   1.0000
  11.250   1.2215   0.03505   0.02577  -0.0074   0.1529   1.0000
  11.500   1.2295   0.03652   0.02738  -0.0052   0.1452   1.0000
  11.750   1.2507   0.03795   0.02861  -0.0048   0.1374   1.0000
  12.000   1.2531   0.03948   0.03041  -0.0021   0.1317   1.0000
  12.250   1.2799   0.04099   0.03164  -0.0024   0.1247   1.0000
  12.500   1.2781   0.04273   0.03374   0.0005   0.1207   1.0000
  12.750   1.2876   0.04430   0.03536   0.0021   0.1159   1.0000
  13.000   1.3072   0.04615   0.03716   0.0025   0.1112   1.0000
  13.250   1.3049   0.04826   0.03956   0.0049   0.1080   1.0000
  13.500   1.3095   0.05017   0.04158   0.0065   0.1046   1.0000
  13.750   1.3345   0.05206   0.04333   0.0063   0.1005   1.0000
  14.000   1.3214   0.05477   0.04640   0.0089   0.0988   1.0000
  14.250   1.3119   0.05767   0.04959   0.0108   0.0969   1.0000
  14.500   1.3078   0.06041   0.05251   0.0120   0.0947   1.0000
  14.750   1.3125   0.06267   0.05481   0.0128   0.0924   1.0000
  15.000   1.3232   0.06537   0.05750   0.0133   0.0900   1.0000
  15.250   1.2974   0.06974   0.06222   0.0142   0.0894   1.0000
  15.500   1.2692   0.07486   0.06766   0.0142   0.0890   1.0000
  15.750   1.2373   0.08091   0.07402   0.0132   0.0887   1.0000
  16.000   1.2005   0.08819   0.08160   0.0110   0.0888   1.0000
  16.250   1.1568   0.09720   0.09090   0.0071   0.0892   1.0000
  16.500   1.1059   0.10868   0.10263   0.0011   0.0899   1.0000
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