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NACA 2424 (naca2424-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 2424 (naca2424-il)
Reynolds number: 100,000
Max Cl/Cd: 36.82 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2424-il-100000.txt
Download as CSV file: xf-naca2424-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2424                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.7964   0.07244   0.06551  -0.0680   1.0000   0.1908
 -13.500  -0.8535   0.06598   0.05894  -0.0663   1.0000   0.1923
 -13.250  -0.8988   0.06163   0.05450  -0.0632   1.0000   0.1937
 -13.000  -0.9552   0.05746   0.05017  -0.0584   1.0000   0.1948
 -12.750  -0.9889   0.05514   0.04775  -0.0535   1.0000   0.1965
 -12.500  -1.0261   0.05302   0.04551  -0.0477   1.0000   0.1980
 -12.250  -1.0666   0.05114   0.04348  -0.0407   1.0000   0.1995
 -12.000  -1.1075   0.04959   0.04177  -0.0327   1.0000   0.2007
 -11.750  -1.1488   0.04839   0.04039  -0.0238   1.0000   0.2018
 -11.500  -1.1879   0.04725   0.03904  -0.0148   1.0000   0.2033
 -11.250  -1.2216   0.04595   0.03746  -0.0065   1.0000   0.2048
 -11.000  -1.1894   0.04561   0.03742  -0.0075   1.0000   0.2087
 -10.750  -1.1895   0.04512   0.03695  -0.0038   1.0000   0.2118
 -10.500  -1.1694   0.04436   0.03597  -0.0044   0.9920   0.2172
 -10.250  -1.1485   0.04332   0.03478  -0.0047   0.9830   0.2224
 -10.000  -1.1049   0.04327   0.03489  -0.0081   0.9761   0.2282
  -9.750  -1.0916   0.04244   0.03384  -0.0069   0.9666   0.2337
  -9.500  -1.0710   0.04157   0.03290  -0.0066   0.9577   0.2390
  -9.250  -1.0316   0.04145   0.03291  -0.0092   0.9508   0.2454
  -9.000  -1.0243   0.04068   0.03194  -0.0065   0.9404   0.2509
  -8.750  -0.9870   0.04008   0.03137  -0.0088   0.9339   0.2576
  -8.500  -0.9682   0.03976   0.03110  -0.0076   0.9239   0.2631
  -8.250  -0.9494   0.03910   0.03016  -0.0067   0.9161   0.2706
  -8.000  -0.9253   0.03863   0.02984  -0.0065   0.9067   0.2762
  -7.750  -0.8946   0.03832   0.02955  -0.0072   0.8987   0.2836
  -7.500  -0.8846   0.03774   0.02867  -0.0045   0.8898   0.2905
  -7.250  -0.8534   0.03740   0.02859  -0.0053   0.8808   0.2971
  -7.000  -0.8190   0.03693   0.02803  -0.0066   0.8747   0.3063
  -6.750  -0.8152   0.03652   0.02752  -0.0027   0.8632   0.3120
  -6.500  -0.7790   0.03624   0.02741  -0.0042   0.8560   0.3203
  -6.250  -0.7486   0.03564   0.02654  -0.0045   0.8510   0.3305
  -6.000  -0.7406   0.03551   0.02661  -0.0014   0.8382   0.3360
  -5.750  -0.7069   0.03511   0.02622  -0.0022   0.8318   0.3460
  -5.500  -0.6630   0.03442   0.02552  -0.0048   0.8281   0.3568
  -5.250  -0.6680   0.03458   0.02573   0.0006   0.8138   0.3623
  -4.750  -0.5840   0.03332   0.02451  -0.0035   0.8055   0.3856
  -4.500  -0.6017   0.03370   0.02482   0.0040   0.7899   0.3914
  -4.250  -0.5589   0.03302   0.02421   0.0019   0.7857   0.4031
  -4.000  -0.5548   0.03320   0.02439   0.0058   0.7745   0.4118
  -3.750  -0.5314   0.03282   0.02400   0.0068   0.7669   0.4226
  -3.500  -0.4884   0.03217   0.02340   0.0049   0.7633   0.4365
  -3.250  -0.4941   0.03257   0.02377   0.0103   0.7505   0.4442
  -3.000  -0.4616   0.03220   0.02351   0.0100   0.7443   0.4568
  -2.750  -0.4175   0.03138   0.02274   0.0081   0.7412   0.4717
  -2.500  -0.3937   0.03113   0.02247   0.0092   0.7350   0.4854
  -1.750  -0.3535   0.03146   0.02300   0.0169   0.7079   0.5210
  -1.500  -0.3407   0.03144   0.02293   0.0198   0.6995   0.5358
  -1.250  -0.2908   0.03051   0.02216   0.0173   0.6969   0.5539
  -1.000  -0.2377   0.02945   0.02119   0.0143   0.6948   0.5736
  -0.750  -0.2794   0.03132   0.02305   0.0246   0.6776   0.5817
  -0.500  -0.2310   0.03035   0.02220   0.0225   0.6749   0.6024
  -0.250  -0.1782   0.02934   0.02129   0.0197   0.6727   0.6242
   0.000  -0.1672   0.02961   0.02161   0.0227   0.6646   0.6414
   0.250  -0.0350   0.02704   0.01914   0.0073   0.6693   0.6740
   0.500  -0.1205   0.02944   0.02161   0.0254   0.6506   0.6820
   0.750  -0.0502   0.02822   0.02046   0.0198   0.6488   0.7080
   1.000   0.0412   0.02701   0.01929   0.0102   0.6470   0.7351
   1.500   0.0521   0.02830   0.02080   0.0180   0.6276   0.7722
   1.750   0.1897   0.02719   0.01964   0.0003   0.6252   0.7947
   2.000   0.0951   0.02937   0.02201   0.0202   0.6105   0.8149
   2.250   0.2582   0.02835   0.02091  -0.0016   0.6071   0.8287
   2.500   0.4055   0.02784   0.02016  -0.0218   0.6016   0.8390
   2.750   0.4419   0.02911   0.02156  -0.0235   0.5901   0.8472
   3.000   0.5513   0.02916   0.02143  -0.0373   0.5813   0.8521
   3.250   0.5801   0.02967   0.02193  -0.0372   0.5730   0.8655
   3.500   0.6374   0.03030   0.02256  -0.0422   0.5625   0.8719
   3.750   0.7218   0.03029   0.02233  -0.0518   0.5543   0.8789
   4.000   0.7228   0.03112   0.02332  -0.0472   0.5445   0.8930
   4.250   0.7989   0.03099   0.02300  -0.0555   0.5355   0.9006
   4.750   0.8436   0.03188   0.02396  -0.0541   0.5179   0.9278
   5.000   0.9185   0.03183   0.02375  -0.0626   0.5085   0.9330
   5.250   0.9311   0.03239   0.02443  -0.0605   0.4990   0.9475
   5.500   1.0118   0.03196   0.02374  -0.0700   0.4899   0.9530
   5.750   1.0217   0.03260   0.02457  -0.0678   0.4802   0.9672
   6.000   1.0730   0.03242   0.02427  -0.0723   0.4712   0.9773
   6.250   1.1134   0.03258   0.02448  -0.0756   0.4616   0.9876
   6.500   1.1616   0.03232   0.02417  -0.0800   0.4516   0.9972
   6.750   1.1907   0.03234   0.02408  -0.0810   0.4442   1.0000
   7.000   1.1622   0.03296   0.02485  -0.0722   0.4381   1.0000
   7.250   1.1630   0.03307   0.02492  -0.0681   0.4317   1.0000
   7.500   1.1952   0.03299   0.02464  -0.0691   0.4249   1.0000
   7.750   1.1505   0.03378   0.02561  -0.0576   0.4199   1.0000
   8.000   1.1216   0.03418   0.02606  -0.0484   0.4147   1.0000
   8.250   1.1827   0.03383   0.02545  -0.0540   0.4067   1.0000
   8.500   1.1392   0.03449   0.02621  -0.0425   0.4026   1.0000
   8.750   1.0895   0.03534   0.02719  -0.0303   0.3980   1.0000
   9.000   1.0832   0.03571   0.02753  -0.0250   0.3921   1.0000
   9.250   1.1395   0.03534   0.02694  -0.0292   0.3846   1.0000
   9.500   1.0800   0.03679   0.02857  -0.0162   0.3804   1.0000
   9.750   1.0573   0.03784   0.02967  -0.0092   0.3745   1.0000
  10.000   1.1464   0.03652   0.02800  -0.0174   0.3663   1.0000
  10.250   1.0795   0.03865   0.03037  -0.0044   0.3621   1.0000
  10.500   1.0449   0.04053   0.03236   0.0033   0.3562   1.0000
  10.750   1.1247   0.03876   0.03028  -0.0025   0.3488   1.0000
  11.000   1.0817   0.04105   0.03274   0.0060   0.3438   1.0000
  11.250   1.0293   0.04427   0.03614   0.0142   0.3381   1.0000
  11.500   1.0988   0.04220   0.03383   0.0107   0.3314   1.0000
  11.750   1.0843   0.04404   0.03573   0.0150   0.3260   1.0000
  12.000   0.8048   0.06653   0.05887   0.0300   0.3139   1.0000
  12.250   1.0608   0.04753   0.03932   0.0222   0.3142   1.0000
  12.500   1.0832   0.04783   0.03955   0.0229   0.3085   1.0000
  12.750   0.7801   0.07637   0.06874   0.0328   0.2938   1.0000
  13.000   0.9409   0.06119   0.05333   0.0332   0.2960   1.0000
  13.250   1.0766   0.05265   0.04443   0.0297   0.2918   1.0000
  14.000   1.0707   0.05818   0.05002   0.0350   0.2757   1.0000
  14.250   0.4799   0.14015   0.13285   0.0200   0.2400   1.0000
  14.500   0.4638   0.14613   0.13887   0.0183   0.2387   1.0000
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