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

NACA 0024 (naca0024-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 0024 (naca0024-il)
Reynolds number: 500,000
Max Cl/Cd: 52.1 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca0024-il-500000.txt
Download as CSV file: xf-naca0024-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0024                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.2119   0.08663   0.08133  -0.0434   1.0000   0.0959
 -19.500  -1.2128   0.08353   0.07821  -0.0443   1.0000   0.0976
 -19.250  -1.2140   0.08032   0.07494  -0.0453   1.0000   0.0994
 -19.000  -1.2126   0.07743   0.07196  -0.0461   1.0000   0.1011
 -18.750  -1.2135   0.07441   0.06890  -0.0468   1.0000   0.1029
 -18.500  -1.2149   0.07138   0.06588  -0.0474   1.0000   0.1048
 -18.250  -1.2158   0.06837   0.06283  -0.0481   1.0000   0.1067
 -18.000  -1.2132   0.06574   0.06014  -0.0486   1.0000   0.1086
 -17.750  -1.2100   0.06318   0.05749  -0.0491   1.0000   0.1104
 -17.500  -1.2112   0.06034   0.05465  -0.0494   1.0000   0.1125
 -17.250  -1.2116   0.05753   0.05183  -0.0498   1.0000   0.1146
 -17.000  -1.2093   0.05501   0.04926  -0.0501   1.0000   0.1168
 -16.750  -1.2034   0.05287   0.04706  -0.0503   1.0000   0.1191
 -16.500  -1.2013   0.05044   0.04458  -0.0504   1.0000   0.1213
 -16.250  -1.2007   0.04792   0.04207  -0.0504   1.0000   0.1237
 -16.000  -1.1967   0.04574   0.03986  -0.0503   1.0000   0.1263
 -15.750  -1.1895   0.04387   0.03793  -0.0503   1.0000   0.1288
 -15.500  -1.1841   0.04191   0.03594  -0.0501   1.0000   0.1314
 -15.250  -1.1819   0.03973   0.03376  -0.0497   1.0000   0.1341
 -15.000  -1.1758   0.03792   0.03193  -0.0493   1.0000   0.1371
 -14.750  -1.1656   0.03651   0.03046  -0.0490   1.0000   0.1400
 -14.500  -1.1609   0.03472   0.02866  -0.0483   1.0000   0.1430
 -14.250  -1.1557   0.03303   0.02698  -0.0475   1.0000   0.1461
 -14.000  -1.1469   0.03170   0.02562  -0.0467   1.0000   0.1495
 -13.750  -1.1361   0.03057   0.02443  -0.0459   1.0000   0.1526
 -13.500  -1.1329   0.02905   0.02294  -0.0444   1.0000   0.1560
 -13.250  -1.1266   0.02786   0.02175  -0.0429   1.0000   0.1595
 -13.000  -1.1182   0.02695   0.02081  -0.0413   1.0000   0.1630
 -12.750  -1.1148   0.02595   0.01980  -0.0390   1.0000   0.1664
 -12.500  -1.1147   0.02496   0.01884  -0.0360   1.0000   0.1698
 -12.250  -1.1143   0.02421   0.01808  -0.0327   1.0000   0.1733
 -12.000  -1.1132   0.02368   0.01751  -0.0292   1.0000   0.1764
 -11.750  -1.1217   0.02300   0.01683  -0.0244   1.0000   0.1795
 -11.500  -1.1177   0.02225   0.01610  -0.0217   0.9991   0.1835
 -11.250  -1.0870   0.02154   0.01538  -0.0236   0.9965   0.1890
 -11.000  -1.0580   0.02071   0.01457  -0.0253   0.9937   0.1946
 -10.750  -1.0270   0.01999   0.01387  -0.0273   0.9915   0.2007
 -10.500  -0.9962   0.01939   0.01325  -0.0288   0.9882   0.2063
 -10.250  -0.9686   0.01862   0.01254  -0.0300   0.9838   0.2127
 -10.000  -0.9344   0.01811   0.01201  -0.0321   0.9809   0.2189
  -9.750  -0.9019   0.01740   0.01135  -0.0341   0.9784   0.2258
  -9.500  -0.8668   0.01685   0.01081  -0.0363   0.9760   0.2327
  -9.250  -0.8425   0.01634   0.01031  -0.0362   0.9680   0.2387
  -9.000  -0.8145   0.01578   0.00979  -0.0369   0.9622   0.2456
  -8.750  -0.7893   0.01542   0.00940  -0.0368   0.9540   0.2516
  -8.500  -0.7700   0.01489   0.00892  -0.0355   0.9443   0.2583
  -8.250  -0.7508   0.01453   0.00855  -0.0341   0.9335   0.2647
  -8.000  -0.7302   0.01419   0.00818  -0.0328   0.9235   0.2708
  -7.750  -0.7135   0.01382   0.00784  -0.0309   0.9111   0.2776
  -7.500  -0.6924   0.01354   0.00751  -0.0296   0.9007   0.2843
  -7.250  -0.6737   0.01324   0.00722  -0.0280   0.8879   0.2909
  -7.000  -0.6538   0.01295   0.00692  -0.0266   0.8766   0.2981
  -6.750  -0.6313   0.01278   0.00669  -0.0255   0.8640   0.3047
  -6.500  -0.6126   0.01248   0.00641  -0.0238   0.8519   0.3123
  -6.250  -0.5916   0.01229   0.00619  -0.0225   0.8390   0.3198
  -6.000  -0.5711   0.01212   0.00599  -0.0210   0.8266   0.3268
  -5.750  -0.5521   0.01195   0.00580  -0.0193   0.8138   0.3345
  -5.500  -0.5298   0.01185   0.00566  -0.0181   0.8009   0.3419
  -5.250  -0.5089   0.01167   0.00546  -0.0167   0.7884   0.3499
  -5.000  -0.4862   0.01154   0.00533  -0.0157   0.7753   0.3582
  -4.750  -0.4628   0.01144   0.00518  -0.0148   0.7628   0.3659
  -4.500  -0.4404   0.01129   0.00505  -0.0137   0.7497   0.3745
  -4.250  -0.4156   0.01125   0.00493  -0.0130   0.7374   0.3824
  -4.000  -0.3932   0.01110   0.00480  -0.0119   0.7244   0.3910
  -3.750  -0.3689   0.01103   0.00470  -0.0111   0.7123   0.3997
  -3.500  -0.3450   0.01095   0.00459  -0.0102   0.6994   0.4080
  -3.250  -0.3212   0.01086   0.00451  -0.0094   0.6875   0.4170
  -3.000  -0.2961   0.01084   0.00442  -0.0087   0.6750   0.4253
  -2.750  -0.2726   0.01073   0.00435  -0.0078   0.6633   0.4345
  -2.500  -0.2477   0.01072   0.00428  -0.0071   0.6510   0.4435
  -2.250  -0.2233   0.01063   0.00422  -0.0063   0.6396   0.4525
  -2.000  -0.1989   0.01061   0.00416  -0.0055   0.6276   0.4621
  -1.750  -0.1737   0.01057   0.00412  -0.0049   0.6165   0.4711
  -1.500  -0.1496   0.01054   0.00407  -0.0041   0.6048   0.4809
  -1.250  -0.1238   0.01053   0.00404  -0.0036   0.5939   0.4901
  -1.000  -0.1000   0.01048   0.00401  -0.0027   0.5826   0.5001
  -0.750  -0.0743   0.01049   0.00400  -0.0021   0.5721   0.5098
  -0.500  -0.0500   0.01045   0.00397  -0.0013   0.5609   0.5196
  -0.250  -0.0248   0.01046   0.00397  -0.0007   0.5508   0.5300
   0.000   0.0000   0.01045   0.00396   0.0000   0.5399   0.5399
   0.250   0.0248   0.01046   0.00397   0.0007   0.5300   0.5508
   0.500   0.0501   0.01045   0.00397   0.0013   0.5196   0.5609
   0.750   0.0743   0.01049   0.00400   0.0021   0.5098   0.5721
   1.000   0.1000   0.01048   0.00401   0.0027   0.5001   0.5826
   1.250   0.1239   0.01053   0.00404   0.0036   0.4900   0.5939
   1.500   0.1497   0.01054   0.00407   0.0041   0.4809   0.6048
   1.750   0.1738   0.01057   0.00412   0.0049   0.4711   0.6165
   2.000   0.1990   0.01061   0.00416   0.0055   0.4621   0.6276
   2.250   0.2234   0.01063   0.00422   0.0063   0.4525   0.6396
   2.500   0.2477   0.01072   0.00428   0.0071   0.4435   0.6510
   2.750   0.2726   0.01073   0.00435   0.0078   0.4345   0.6633
   3.000   0.2962   0.01084   0.00442   0.0087   0.4252   0.6750
   3.250   0.3213   0.01086   0.00451   0.0093   0.4170   0.6875
   3.500   0.3451   0.01095   0.00459   0.0102   0.4079   0.6994
   3.750   0.3691   0.01103   0.00470   0.0110   0.3997   0.7123
   4.000   0.3934   0.01110   0.00480   0.0118   0.3910   0.7244
   4.250   0.4157   0.01125   0.00493   0.0129   0.3824   0.7374
   4.500   0.4406   0.01129   0.00505   0.0136   0.3745   0.7498
   4.750   0.4630   0.01144   0.00518   0.0147   0.3659   0.7628
   5.000   0.4864   0.01154   0.00533   0.0157   0.3582   0.7753
   5.250   0.5092   0.01167   0.00546   0.0167   0.3499   0.7884
   5.500   0.5302   0.01185   0.00566   0.0181   0.3419   0.8009
   5.750   0.5525   0.01195   0.00580   0.0192   0.3345   0.8138
   6.000   0.5716   0.01213   0.00599   0.0209   0.3267   0.8265
   6.250   0.5920   0.01229   0.00619   0.0224   0.3197   0.8390
   6.500   0.6131   0.01247   0.00641   0.0237   0.3122   0.8519
   6.750   0.6318   0.01278   0.00669   0.0254   0.3047   0.8639
   7.000   0.6543   0.01295   0.00692   0.0264   0.2981   0.8765
   7.250   0.6742   0.01324   0.00722   0.0279   0.2909   0.8879
   7.500   0.6930   0.01354   0.00751   0.0295   0.2843   0.9007
   7.750   0.7142   0.01382   0.00784   0.0308   0.2775   0.9110
   8.000   0.7308   0.01419   0.00817   0.0327   0.2708   0.9234
   8.250   0.7515   0.01453   0.00855   0.0340   0.2647   0.9335
   8.500   0.7707   0.01489   0.00891   0.0354   0.2582   0.9443
   8.750   0.7901   0.01541   0.00939   0.0366   0.2516   0.9539
   9.000   0.8153   0.01577   0.00978   0.0368   0.2456   0.9622
   9.250   0.8432   0.01633   0.01030   0.0361   0.2386   0.9681
   9.500   0.8677   0.01684   0.01080   0.0362   0.2327   0.9760
   9.750   0.9028   0.01739   0.01134   0.0339   0.2257   0.9784
  10.000   0.9353   0.01809   0.01199   0.0319   0.2189   0.9809
  10.250   0.9695   0.01861   0.01252   0.0299   0.2126   0.9839
  10.500   0.9971   0.01937   0.01324   0.0287   0.2063   0.9883
  10.750   1.0281   0.01997   0.01385   0.0271   0.2006   0.9916
  11.000   1.0592   0.02069   0.01455   0.0251   0.1945   0.9938
  11.250   1.0883   0.02151   0.01535   0.0234   0.1889   0.9966
  11.500   1.1191   0.02222   0.01608   0.0215   0.1834   0.9992
  11.750   1.1217   0.02296   0.01679   0.0244   0.1795   1.0000
  12.000   1.1132   0.02364   0.01746   0.0293   0.1765   1.0000
  12.250   1.1146   0.02416   0.01803   0.0327   0.1733   1.0000
  12.500   1.1152   0.02492   0.01879   0.0360   0.1698   1.0000
  12.750   1.1154   0.02590   0.01975   0.0389   0.1663   1.0000
  13.000   1.1192   0.02690   0.02075   0.0412   0.1630   1.0000
  13.250   1.1278   0.02781   0.02170   0.0428   0.1594   1.0000
  13.500   1.1344   0.02900   0.02289   0.0442   0.1559   1.0000
  13.750   1.1376   0.03053   0.02439   0.0457   0.1525   1.0000
  14.000   1.1489   0.03164   0.02555   0.0464   0.1494   1.0000
  14.250   1.1578   0.03297   0.02691   0.0472   0.1460   1.0000
  14.500   1.1629   0.03467   0.02860   0.0480   0.1429   1.0000
  14.750   1.1681   0.03643   0.03038   0.0486   0.1399   1.0000
  15.000   1.1784   0.03785   0.03185   0.0490   0.1370   1.0000
  15.250   1.1844   0.03967   0.03369   0.0493   0.1340   1.0000
  15.500   1.1866   0.04186   0.03587   0.0497   0.1313   1.0000
  15.750   1.1925   0.04377   0.03783   0.0499   0.1288   1.0000
  16.000   1.1997   0.04566   0.03977   0.0499   0.1262   1.0000
  16.250   1.2037   0.04784   0.04198   0.0500   0.1236   1.0000
  16.500   1.2043   0.05037   0.04451   0.0500   0.1212   1.0000
  16.750   1.2069   0.05277   0.04695   0.0499   0.1190   1.0000
  17.000   1.2128   0.05490   0.04915   0.0496   0.1167   1.0000
  17.250   1.2151   0.05745   0.05174   0.0493   0.1145   1.0000
  17.500   1.2146   0.06026   0.05456   0.0490   0.1124   1.0000
  17.750   1.2138   0.06307   0.05738   0.0486   0.1103   1.0000
  18.000   1.2171   0.06564   0.06003   0.0481   0.1085   1.0000
  18.250   1.2196   0.06828   0.06273   0.0476   0.1065   1.0000
  18.500   1.2187   0.07130   0.06579   0.0469   0.1047   1.0000
  18.750   1.2173   0.07433   0.06881   0.0463   0.1028   1.0000
  19.000   1.2166   0.07734   0.07187   0.0456   0.1010   1.0000
  19.250   1.2181   0.08023   0.07484   0.0447   0.0993   1.0000
<< Back to NACA 0024 (naca0024-il)

Polar data table (+)

Polar graphs


<< Back to NACA 0024 (naca0024-il)