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NACA 2414 (n2414-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 2414 (n2414-il)
Reynolds number: 100,000
Max Cl/Cd: 47.77 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n2414-il-100000.txt
Download as CSV file: xf-n2414-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2414                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4901   0.12030   0.11467  -0.0300   1.0000   0.1630
 -11.000  -0.6812   0.07017   0.06439  -0.0629   1.0000   0.0947
 -10.750  -0.7034   0.06566   0.05983  -0.0620   1.0000   0.0942
 -10.500  -0.7291   0.06152   0.05560  -0.0597   1.0000   0.0937
 -10.250  -0.7536   0.05737   0.05128  -0.0569   1.0000   0.0933
 -10.000  -0.7749   0.05335   0.04700  -0.0536   1.0000   0.0932
  -9.750  -0.7925   0.04955   0.04286  -0.0499   1.0000   0.0935
  -9.500  -0.8061   0.04613   0.03898  -0.0460   1.0000   0.0943
  -9.250  -0.8067   0.04314   0.03575  -0.0432   1.0000   0.0959
  -9.000  -0.7905   0.04194   0.03469  -0.0417   1.0000   0.0984
  -8.750  -0.7832   0.04001   0.03258  -0.0393   1.0000   0.1006
  -8.500  -0.7777   0.03778   0.03001  -0.0366   1.0000   0.1031
  -8.250  -0.7722   0.03563   0.02733  -0.0338   1.0000   0.1060
  -8.000  -0.7587   0.03373   0.02537  -0.0321   1.0000   0.1092
  -7.750  -0.7426   0.03259   0.02420  -0.0305   1.0000   0.1128
  -7.500  -0.7282   0.03122   0.02253  -0.0286   1.0000   0.1173
  -7.250  -0.7122   0.02969   0.02081  -0.0271   1.0000   0.1218
  -7.000  -0.6940   0.02877   0.01990  -0.0257   1.0000   0.1268
  -6.750  -0.6766   0.02780   0.01859  -0.0242   1.0000   0.1330
  -6.500  -0.6569   0.02672   0.01766  -0.0232   1.0000   0.1390
  -6.250  -0.6377   0.02597   0.01669  -0.0220   1.0000   0.1467
  -6.000  -0.6172   0.02510   0.01594  -0.0211   1.0000   0.1544
  -5.750  -0.5967   0.02444   0.01508  -0.0201   1.0000   0.1641
  -5.500  -0.5761   0.02384   0.01462  -0.0193   1.0000   0.1740
  -5.250  -0.5555   0.02324   0.01404  -0.0185   1.0000   0.1853
  -5.000  -0.5348   0.02274   0.01352  -0.0177   1.0000   0.1984
  -4.750  -0.5143   0.02234   0.01313  -0.0169   1.0000   0.2132
  -4.500  -0.4938   0.02199   0.01282  -0.0162   1.0000   0.2294
  -4.250  -0.4732   0.02165   0.01259  -0.0155   1.0000   0.2473
  -4.000  -0.4270   0.02139   0.01249  -0.0197   0.9933   0.2767
  -3.750  -0.3839   0.02109   0.01236  -0.0232   0.9853   0.3091
  -3.500  -0.3413   0.02081   0.01225  -0.0265   0.9771   0.3459
  -3.250  -0.2957   0.02055   0.01218  -0.0304   0.9699   0.3893
  -3.000  -0.2584   0.02020   0.01210  -0.0325   0.9598   0.4321
  -2.750  -0.2188   0.01992   0.01209  -0.0350   0.9507   0.4836
  -2.500  -0.1778   0.01962   0.01210  -0.0374   0.9420   0.5430
  -2.250  -0.1446   0.01937   0.01213  -0.0382   0.9309   0.6051
  -2.000  -0.1015   0.01910   0.01218  -0.0403   0.9241   0.6767
  -1.750  -0.0741   0.01897   0.01228  -0.0393   0.9116   0.7389
  -1.500  -0.0405   0.01892   0.01241  -0.0390   0.9021   0.7998
  -1.250  -0.0007   0.01893   0.01250  -0.0396   0.8936   0.8553
  -1.000   0.0465   0.01902   0.01258  -0.0417   0.8858   0.9023
  -0.750   0.1088   0.01909   0.01258  -0.0470   0.8785   0.9357
  -0.500   0.1914   0.01891   0.01229  -0.0564   0.8748   0.9566
  -0.250   0.2703   0.01864   0.01193  -0.0658   0.8670   0.9741
   0.000   0.3473   0.01809   0.01131  -0.0748   0.8588   0.9906
   0.250   0.3990   0.01762   0.01078  -0.0796   0.8453   1.0000
   0.500   0.4204   0.01731   0.01040  -0.0786   0.8297   1.0000
   0.750   0.4425   0.01705   0.01007  -0.0774   0.8147   1.0000
   1.000   0.4656   0.01681   0.00974  -0.0763   0.8006   1.0000
   1.250   0.4873   0.01666   0.00950  -0.0750   0.7856   1.0000
   1.500   0.5073   0.01663   0.00941  -0.0734   0.7697   1.0000
   1.750   0.5279   0.01664   0.00936  -0.0719   0.7541   1.0000
   2.000   0.5492   0.01667   0.00932  -0.0705   0.7389   1.0000
   2.250   0.5712   0.01672   0.00930  -0.0691   0.7243   1.0000
   2.500   0.5944   0.01676   0.00927  -0.0679   0.7102   1.0000
   2.750   0.6189   0.01679   0.00920  -0.0668   0.6965   1.0000
   3.000   0.6397   0.01697   0.00933  -0.0653   0.6810   1.0000
   3.250   0.6611   0.01715   0.00948  -0.0639   0.6658   1.0000
   3.500   0.6833   0.01734   0.00963  -0.0625   0.6509   1.0000
   3.750   0.7061   0.01752   0.00975  -0.0613   0.6363   1.0000
   4.000   0.7295   0.01770   0.00987  -0.0601   0.6217   1.0000
   4.250   0.7536   0.01787   0.00995  -0.0590   0.6071   1.0000
   4.500   0.7758   0.01808   0.01012  -0.0576   0.5913   1.0000
   4.750   0.7973   0.01832   0.01034  -0.0561   0.5751   1.0000
   5.000   0.8191   0.01856   0.01056  -0.0547   0.5587   1.0000
   5.250   0.8411   0.01881   0.01077  -0.0533   0.5421   1.0000
   5.500   0.8631   0.01906   0.01099  -0.0519   0.5251   1.0000
   5.750   0.8849   0.01931   0.01121  -0.0505   0.5076   1.0000
   6.000   0.9066   0.01957   0.01142  -0.0491   0.4897   1.0000
   6.250   0.9279   0.01983   0.01164  -0.0476   0.4712   1.0000
   6.500   0.9490   0.02010   0.01186  -0.0461   0.4523   1.0000
   6.750   0.9697   0.02039   0.01208  -0.0446   0.4329   1.0000
   7.000   0.9881   0.02072   0.01243  -0.0428   0.4120   1.0000
   7.250   1.0060   0.02106   0.01277  -0.0408   0.3901   1.0000
   7.500   1.0237   0.02143   0.01307  -0.0389   0.3681   1.0000
   7.750   1.0405   0.02189   0.01343  -0.0369   0.3455   1.0000
   8.000   1.0554   0.02242   0.01395  -0.0347   0.3211   1.0000
   8.250   1.0702   0.02307   0.01443  -0.0325   0.2981   1.0000
   8.500   1.0830   0.02382   0.01515  -0.0301   0.2736   1.0000
   8.750   1.0955   0.02468   0.01586  -0.0278   0.2513   1.0000
   9.000   1.1077   0.02567   0.01673  -0.0255   0.2303   1.0000
   9.250   1.1191   0.02670   0.01770  -0.0231   0.2109   1.0000
   9.500   1.1307   0.02781   0.01873  -0.0209   0.1939   1.0000
   9.750   1.1427   0.02898   0.01982  -0.0187   0.1791   1.0000
  10.000   1.1552   0.03021   0.02099  -0.0168   0.1664   1.0000
  10.250   1.1695   0.03151   0.02214  -0.0151   0.1552   1.0000
  10.500   1.1802   0.03269   0.02338  -0.0129   0.1455   1.0000
  10.750   1.1939   0.03413   0.02486  -0.0112   0.1367   1.0000
  11.000   1.2165   0.03570   0.02620  -0.0110   0.1283   1.0000
  11.250   1.2223   0.03705   0.02784  -0.0082   0.1222   1.0000
  11.500   1.2487   0.03878   0.02933  -0.0086   0.1152   1.0000
  11.750   1.2519   0.04031   0.03119  -0.0057   0.1108   1.0000
  12.000   1.2658   0.04180   0.03270  -0.0044   0.1058   1.0000
  12.250   1.2838   0.04390   0.03483  -0.0037   0.1014   1.0000
  12.500   1.2864   0.04577   0.03698  -0.0012   0.0980   1.0000
  12.750   1.2956   0.04750   0.03878   0.0003   0.0946   1.0000
  13.000   1.3158   0.04989   0.04113   0.0005   0.0910   1.0000
  13.250   1.3064   0.05229   0.04390   0.0036   0.0893   1.0000
  13.500   1.2995   0.05490   0.04680   0.0060   0.0875   1.0000
  13.750   1.2977   0.05739   0.04946   0.0076   0.0854   1.0000
  14.000   1.3022   0.05963   0.05177   0.0087   0.0832   1.0000
  14.250   1.3153   0.06265   0.05477   0.0091   0.0810   1.0000
  14.500   1.2925   0.06640   0.05887   0.0109   0.0806   1.0000
  14.750   1.2677   0.07080   0.06359   0.0119   0.0802   1.0000
  15.000   1.2403   0.07593   0.06902   0.0118   0.0801   1.0000
  15.250   1.2099   0.08192   0.07529   0.0107   0.0800   1.0000
  15.500   1.1761   0.08894   0.08259   0.0084   0.0802   1.0000
  15.750   1.1390   0.09719   0.09108   0.0049   0.0806   1.0000
  16.000   1.0996   0.10683   0.10091   0.0000   0.0810   1.0000
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