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NACA 2415 (naca2415-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 2415 (naca2415-il)
Reynolds number: 100,000
Max Cl/Cd: 46.68 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2415-il-100000.txt
Download as CSV file: xf-naca2415-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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6054   0.08336   0.07758  -0.0565   1.0000   0.1095
 -11.250  -0.6180   0.07674   0.07095  -0.0592   1.0000   0.1082
 -11.000  -0.6583   0.06811   0.06226  -0.0634   1.0000   0.1064
 -10.750  -0.7137   0.06170   0.05575  -0.0628   1.0000   0.1047
 -10.500  -0.7608   0.05720   0.05108  -0.0583   1.0000   0.1036
 -10.250  -0.7944   0.05295   0.04657  -0.0539   1.0000   0.1030
 -10.000  -0.8149   0.04936   0.04269  -0.0498   1.0000   0.1030
  -9.750  -0.8258   0.04633   0.03937  -0.0460   1.0000   0.1035
  -9.500  -0.8307   0.04371   0.03645  -0.0425   1.0000   0.1048
  -9.250  -0.8326   0.04124   0.03362  -0.0392   1.0000   0.1064
  -9.000  -0.8321   0.03894   0.03087  -0.0359   1.0000   0.1082
  -8.750  -0.8259   0.03670   0.02832  -0.0333   1.0000   0.1100
  -8.500  -0.8113   0.03517   0.02682  -0.0316   1.0000   0.1123
  -8.250  -0.7973   0.03387   0.02543  -0.0298   1.0000   0.1151
  -8.000  -0.7840   0.03255   0.02390  -0.0278   1.0000   0.1187
  -7.750  -0.7713   0.03114   0.02209  -0.0257   1.0000   0.1226
  -7.500  -0.7532   0.03000   0.02111  -0.0245   1.0000   0.1269
  -7.250  -0.7364   0.02903   0.02001  -0.0230   1.0000   0.1321
  -7.000  -0.7190   0.02786   0.01865  -0.0216   1.0000   0.1380
  -6.750  -0.7002   0.02716   0.01804  -0.0204   1.0000   0.1448
  -6.500  -0.6814   0.02626   0.01700  -0.0192   1.0000   0.1529
  -6.250  -0.6622   0.02569   0.01649  -0.0182   1.0000   0.1619
  -6.000  -0.6428   0.02500   0.01582  -0.0172   1.0000   0.1716
  -5.750  -0.6236   0.02449   0.01521  -0.0161   1.0000   0.1834
  -5.500  -0.6043   0.02410   0.01490  -0.0152   1.0000   0.1954
  -5.250  -0.5849   0.02369   0.01459  -0.0143   1.0000   0.2080
  -5.000  -0.5654   0.02336   0.01429  -0.0135   1.0000   0.2218
  -4.750  -0.5289   0.02312   0.01411  -0.0159   0.9954   0.2413
  -4.500  -0.4853   0.02291   0.01389  -0.0194   0.9880   0.2654
  -4.250  -0.4400   0.02266   0.01381  -0.0233   0.9814   0.2909
  -4.000  -0.4003   0.02238   0.01360  -0.0261   0.9723   0.3189
  -3.750  -0.3602   0.02207   0.01347  -0.0289   0.9638   0.3483
  -3.250  -0.2814   0.02146   0.01318  -0.0339   0.9457   0.4170
  -3.000  -0.2362   0.02115   0.01311  -0.0373   0.9388   0.4579
  -2.750  -0.2040   0.02086   0.01303  -0.0381   0.9273   0.4970
  -2.500  -0.1676   0.02061   0.01298  -0.0396   0.9177   0.5441
  -2.250  -0.1286   0.02029   0.01292  -0.0413   0.9088   0.5958
  -2.000  -0.0978   0.02007   0.01294  -0.0413   0.8978   0.6470
  -1.750  -0.0556   0.01975   0.01285  -0.0428   0.8908   0.7051
  -1.500  -0.0277   0.01966   0.01293  -0.0418   0.8792   0.7555
  -1.250   0.0147   0.01945   0.01284  -0.0427   0.8731   0.8058
  -1.000   0.0426   0.01951   0.01296  -0.0412   0.8612   0.8479
  -0.750   0.0909   0.01938   0.01281  -0.0431   0.8554   0.8852
  -0.500   0.1387   0.01949   0.01289  -0.0455   0.8449   0.9135
  -0.250   0.2036   0.01928   0.01260  -0.0512   0.8386   0.9358
   0.000   0.2682   0.01916   0.01240  -0.0575   0.8286   0.9533
   0.250   0.3396   0.01873   0.01188  -0.0650   0.8200   0.9672
   0.500   0.4024   0.01844   0.01153  -0.0716   0.8068   0.9824
   0.750   0.4668   0.01797   0.01099  -0.0785   0.7940   0.9966
   1.000   0.4986   0.01762   0.01054  -0.0794   0.7810   1.0000
   1.250   0.5165   0.01751   0.01036  -0.0780   0.7653   1.0000
   1.500   0.5347   0.01747   0.01027  -0.0765   0.7499   1.0000
   1.750   0.5537   0.01746   0.01019  -0.0750   0.7351   1.0000
   2.000   0.5740   0.01743   0.01007  -0.0735   0.7206   1.0000
   2.250   0.5955   0.01736   0.00990  -0.0721   0.7061   1.0000
   2.500   0.6171   0.01734   0.00977  -0.0706   0.6914   1.0000
   2.750   0.6362   0.01746   0.00985  -0.0690   0.6758   1.0000
   3.000   0.6560   0.01763   0.00998  -0.0674   0.6615   1.0000
   3.250   0.6775   0.01778   0.01006  -0.0660   0.6480   1.0000
   3.500   0.7016   0.01789   0.01006  -0.0650   0.6356   1.0000
   3.750   0.7215   0.01812   0.01028  -0.0634   0.6213   1.0000
   4.000   0.7416   0.01839   0.01052  -0.0619   0.6073   1.0000
   4.250   0.7637   0.01863   0.01070  -0.0606   0.5942   1.0000
   4.500   0.7884   0.01880   0.01077  -0.0597   0.5815   1.0000
   4.750   0.8084   0.01907   0.01104  -0.0581   0.5668   1.0000
   5.000   0.8285   0.01933   0.01128  -0.0564   0.5517   1.0000
   5.250   0.8494   0.01957   0.01148  -0.0549   0.5364   1.0000
   5.500   0.8710   0.01980   0.01166  -0.0534   0.5212   1.0000
   5.750   0.8933   0.02004   0.01183  -0.0521   0.5064   1.0000
   6.000   0.9164   0.02028   0.01198  -0.0509   0.4915   1.0000
   6.250   0.9363   0.02057   0.01227  -0.0493   0.4754   1.0000
   6.500   0.9560   0.02087   0.01257  -0.0476   0.4590   1.0000
   6.750   0.9758   0.02118   0.01286  -0.0460   0.4422   1.0000
   7.000   0.9954   0.02149   0.01314  -0.0443   0.4248   1.0000
   7.250   1.0144   0.02180   0.01341  -0.0426   0.4069   1.0000
   7.500   1.0328   0.02213   0.01370  -0.0407   0.3885   1.0000
   7.750   1.0504   0.02250   0.01399  -0.0388   0.3697   1.0000
   8.000   1.0672   0.02292   0.01433  -0.0369   0.3507   1.0000
   8.250   1.0813   0.02340   0.01482  -0.0345   0.3306   1.0000
   8.500   1.0947   0.02393   0.01534  -0.0321   0.3104   1.0000
   8.750   1.1072   0.02452   0.01588  -0.0296   0.2903   1.0000
   9.000   1.1188   0.02518   0.01647  -0.0271   0.2708   1.0000
   9.250   1.1294   0.02595   0.01713  -0.0245   0.2521   1.0000
   9.500   1.1398   0.02687   0.01791  -0.0220   0.2343   1.0000
   9.750   1.1492   0.02792   0.01884  -0.0194   0.2172   1.0000
  10.000   1.1582   0.02903   0.01984  -0.0169   0.2017   1.0000
  10.250   1.1647   0.03013   0.02096  -0.0140   0.1878   1.0000
  10.500   1.1724   0.03135   0.02217  -0.0114   0.1751   1.0000
  10.750   1.1818   0.03266   0.02348  -0.0092   0.1639   1.0000
  11.000   1.1941   0.03400   0.02470  -0.0075   0.1542   1.0000
  11.250   1.2036   0.03530   0.02603  -0.0055   0.1455   1.0000
  11.500   1.2165   0.03683   0.02757  -0.0041   0.1380   1.0000
  11.750   1.2312   0.03821   0.02892  -0.0028   0.1314   1.0000
  12.000   1.2482   0.03993   0.03067  -0.0019   0.1258   1.0000
  12.250   1.2586   0.04151   0.03239  -0.0003   0.1209   1.0000
  12.500   1.2904   0.04323   0.03387  -0.0012   0.1155   1.0000
  12.750   1.2915   0.04510   0.03605   0.0013   0.1128   1.0000
  13.000   1.2975   0.04709   0.03826   0.0031   0.1099   1.0000
  13.250   1.3079   0.04895   0.04022   0.0043   0.1071   1.0000
  13.500   1.3426   0.05114   0.04221   0.0032   0.1033   1.0000
  13.750   1.3316   0.05351   0.04495   0.0061   0.1021   1.0000
  14.000   1.3212   0.05625   0.04800   0.0085   0.1008   1.0000
  14.250   1.3106   0.05930   0.05133   0.0104   0.0996   1.0000
  14.500   1.2988   0.06268   0.05497   0.0118   0.0985   1.0000
  14.750   1.2847   0.06642   0.05896   0.0128   0.0977   1.0000
  15.000   1.2674   0.07063   0.06341   0.0132   0.0969   1.0000
  15.250   1.2433   0.07571   0.06876   0.0130   0.0965   1.0000
  15.500   1.1975   0.08354   0.07694   0.0111   0.0970   1.0000
  15.750   1.1065   0.09902   0.09289   0.0036   0.0994   1.0000
  16.000   0.9747   0.12816   0.12233  -0.0133   0.1032   1.0000
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