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

NACA 23024 (naca23024-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 23024 (naca23024-il)
Reynolds number: 1,000,000
Max Cl/Cd: 54.4 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca23024-il-1000000-n5.txt
Download as CSV file: xf-naca23024-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 23024                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.1663   0.06917   0.06417  -0.0654   1.0000   0.0564
 -19.500  -1.1686   0.06641   0.06137  -0.0654   1.0000   0.0574
 -19.250  -1.1708   0.06370   0.05859  -0.0654   1.0000   0.0583
 -19.000  -1.1746   0.06085   0.05570  -0.0654   1.0000   0.0592
 -18.750  -1.1770   0.05822   0.05302  -0.0652   1.0000   0.0600
 -18.500  -1.1807   0.05548   0.05024  -0.0649   1.0000   0.0611
 -18.250  -1.1819   0.05307   0.04778  -0.0645   1.0000   0.0620
 -18.000  -1.1817   0.05083   0.04550  -0.0640   1.0000   0.0631
 -17.750  -1.1812   0.04865   0.04327  -0.0634   1.0000   0.0641
 -17.500  -1.1807   0.04656   0.04114  -0.0626   1.0000   0.0650
 -17.250  -1.1819   0.04436   0.03890  -0.0618   1.0000   0.0662
 -17.000  -1.1820   0.04232   0.03683  -0.0608   1.0000   0.0674
 -16.750  -1.1781   0.04056   0.03503  -0.0599   0.9999   0.0688
 -16.500  -1.1641   0.03876   0.03319  -0.0609   0.9992   0.0702
 -16.250  -1.1505   0.03683   0.03125  -0.0620   0.9982   0.0724
 -16.000  -1.1338   0.03509   0.02949  -0.0634   0.9969   0.0747
 -15.750  -1.1149   0.03359   0.02797  -0.0646   0.9954   0.0767
 -15.500  -1.0986   0.03203   0.02640  -0.0656   0.9939   0.0787
 -15.250  -1.0816   0.03058   0.02493  -0.0664   0.9926   0.0813
 -15.000  -1.0614   0.02939   0.02372  -0.0674   0.9914   0.0833
 -14.750  -1.0519   0.02787   0.02220  -0.0667   0.9894   0.0866
 -14.500  -1.0358   0.02668   0.02100  -0.0667   0.9874   0.0894
 -14.250  -1.0186   0.02551   0.01982  -0.0668   0.9852   0.0922
 -14.000  -1.0009   0.02436   0.01868  -0.0671   0.9831   0.0961
 -13.750  -0.9800   0.02335   0.01766  -0.0676   0.9811   0.0996
 -13.500  -0.9587   0.02233   0.01666  -0.0683   0.9794   0.1036
 -13.000  -0.9322   0.02050   0.01484  -0.0659   0.9698   0.1114
 -12.750  -0.9139   0.01961   0.01396  -0.0655   0.9654   0.1173
 -12.500  -0.9048   0.01884   0.01321  -0.0632   0.9562   0.1214
 -12.000  -0.8652   0.01731   0.01171  -0.0624   0.9408   0.1323
 -11.750  -0.8344   0.01657   0.01098  -0.0641   0.9345   0.1390
 -11.500  -0.7954   0.01584   0.01027  -0.0673   0.9286   0.1470
 -11.250  -0.7530   0.01508   0.00954  -0.0712   0.9182   0.1567
 -11.000  -0.7130   0.01453   0.00897  -0.0745   0.9057   0.1639
 -10.750  -0.6776   0.01408   0.00848  -0.0767   0.8877   0.1725
 -10.500  -0.6525   0.01365   0.00803  -0.0770   0.8700   0.1813
 -10.250  -0.6302   0.01330   0.00764  -0.0765   0.8534   0.1878
 -10.000  -0.6075   0.01299   0.00729  -0.0760   0.8353   0.1948
  -9.750  -0.5858   0.01270   0.00696  -0.0753   0.8176   0.2023
  -9.500  -0.5649   0.01243   0.00665  -0.0743   0.7976   0.2103
  -9.250  -0.5439   0.01218   0.00635  -0.0734   0.7775   0.2172
  -9.000  -0.5215   0.01197   0.00609  -0.0727   0.7597   0.2244
  -8.750  -0.4981   0.01178   0.00585  -0.0721   0.7427   0.2310
  -8.500  -0.4750   0.01157   0.00561  -0.0714   0.7275   0.2381
  -8.000  -0.4317   0.01123   0.00519  -0.0694   0.6971   0.2515
  -7.750  -0.4112   0.01109   0.00502  -0.0681   0.6814   0.2581
  -7.500  -0.3912   0.01097   0.00485  -0.0666   0.6672   0.2627
  -7.250  -0.3739   0.01080   0.00467  -0.0646   0.6544   0.2710
  -7.000  -0.3541   0.01069   0.00453  -0.0630   0.6422   0.2770
  -6.750  -0.3364   0.01056   0.00438  -0.0611   0.6298   0.2834
  -6.500  -0.3186   0.01045   0.00425  -0.0591   0.6176   0.2902
  -6.250  -0.3002   0.01038   0.00413  -0.0571   0.6052   0.2957
  -6.000  -0.2832   0.01026   0.00401  -0.0549   0.5954   0.3024
  -5.750  -0.2659   0.01017   0.00390  -0.0528   0.5834   0.3096
  -5.500  -0.2472   0.01013   0.00382  -0.0508   0.5727   0.3138
  -5.250  -0.2313   0.01002   0.00371  -0.0483   0.5624   0.3214
  -5.000  -0.2152   0.00996   0.00363  -0.0458   0.5519   0.3275
  -4.750  -0.1967   0.00992   0.00356  -0.0438   0.5409   0.3328
  -4.500  -0.1813   0.00988   0.00349  -0.0412   0.5299   0.3391
  -4.250  -0.1646   0.00981   0.00342  -0.0388   0.5203   0.3458
  -4.000  -0.1488   0.00980   0.00337  -0.0362   0.5096   0.3521
  -3.750  -0.1337   0.00974   0.00332  -0.0334   0.4993   0.3587
  -3.500  -0.1197   0.00973   0.00327  -0.0304   0.4867   0.3655
  -3.250  -0.1031   0.00971   0.00323  -0.0280   0.4775   0.3719
  -3.000  -0.0886   0.00970   0.00320  -0.0251   0.4664   0.3777
  -2.750  -0.0758   0.00967   0.00317  -0.0218   0.4585   0.3849
  -2.500  -0.0635   0.00964   0.00314  -0.0184   0.4516   0.3923
  -2.250  -0.0541   0.00965   0.00312  -0.0144   0.4421   0.3975
  -2.000  -0.0434   0.00961   0.00309  -0.0106   0.4358   0.4049
  -1.750  -0.0309   0.00959   0.00308  -0.0073   0.4285   0.4125
  -1.500  -0.0198   0.00962   0.00308  -0.0036   0.4190   0.4188
  -1.250  -0.0074   0.00959   0.00307  -0.0002   0.4142   0.4266
  -1.000   0.0051   0.00960   0.00307   0.0031   0.4054   0.4341
  -0.750   0.0164   0.00966   0.00309   0.0068   0.3966   0.4395
  -0.500   0.0278   0.00963   0.00309   0.0104   0.3905   0.4481
  -0.250   0.0384   0.00966   0.00312   0.0141   0.3830   0.4560
   0.000   0.0483   0.00971   0.00315   0.0180   0.3760   0.4621
   0.250   0.0609   0.00970   0.00317   0.0213   0.3702   0.4713
   0.500   0.0765   0.00974   0.00320   0.0240   0.3632   0.4790
   0.750   0.0902   0.00979   0.00325   0.0270   0.3548   0.4877
   1.000   0.1068   0.00980   0.00328   0.0294   0.3491   0.4965
   1.250   0.1228   0.00986   0.00333   0.0320   0.3418   0.5051
   1.500   0.1368   0.00992   0.00339   0.0349   0.3342   0.5136
   1.750   0.1537   0.00996   0.00345   0.0372   0.3273   0.5230
   2.000   0.1701   0.01003   0.00351   0.0396   0.3204   0.5321
   2.250   0.1862   0.01008   0.00358   0.0420   0.3144   0.5434
   2.500   0.2044   0.01015   0.00366   0.0440   0.3079   0.5522
   2.750   0.2197   0.01022   0.00375   0.0466   0.3011   0.5627
   3.000   0.2369   0.01031   0.00385   0.0487   0.2948   0.5747
   3.250   0.2544   0.01038   0.00394   0.0508   0.2883   0.5851
   3.500   0.2713   0.01050   0.00406   0.0529   0.2812   0.5976
   3.750   0.2887   0.01058   0.00418   0.0549   0.2753   0.6087
   4.000   0.3074   0.01068   0.00430   0.0567   0.2699   0.6205
   4.250   0.3242   0.01081   0.00445   0.0588   0.2630   0.6336
   4.500   0.3439   0.01092   0.00458   0.0603   0.2574   0.6461
   4.750   0.3616   0.01106   0.00475   0.0621   0.2504   0.6596
   5.000   0.3807   0.01123   0.00493   0.0636   0.2452   0.6731
   5.250   0.4013   0.01133   0.00509   0.0648   0.2405   0.6876
   5.500   0.4222   0.01149   0.00527   0.0659   0.2354   0.7015
   5.750   0.4437   0.01167   0.00549   0.0667   0.2302   0.7171
   6.000   0.4685   0.01181   0.00569   0.0670   0.2264   0.7322
   6.250   0.4925   0.01199   0.00591   0.0673   0.2212   0.7490
   6.500   0.5154   0.01219   0.00616   0.0679   0.2167   0.7675
   6.750   0.5381   0.01238   0.00641   0.0684   0.2124   0.7839
   7.000   0.5612   0.01257   0.00667   0.0689   0.2089   0.8012
   7.250   0.5832   0.01280   0.00695   0.0695   0.2044   0.8201
   7.500   0.6058   0.01306   0.00726   0.0699   0.2008   0.8391
   7.750   0.6312   0.01328   0.00755   0.0698   0.1976   0.8568
   8.000   0.6573   0.01353   0.00787   0.0695   0.1946   0.8732
   8.250   0.6848   0.01384   0.00823   0.0688   0.1908   0.8906
   8.500   0.7219   0.01424   0.00868   0.0661   0.1866   0.9069
   8.750   0.7655   0.01463   0.00910   0.0621   0.1829   0.9185
   9.000   0.8107   0.01514   0.00962   0.0577   0.1783   0.9280
   9.250   0.8511   0.01576   0.01023   0.0541   0.1739   0.9339
   9.500   0.8861   0.01629   0.01078   0.0518   0.1710   0.9396
   9.750   0.9104   0.01682   0.01132   0.0515   0.1684   0.9478
  10.000   0.9343   0.01742   0.01191   0.0512   0.1649   0.9534
  10.500   0.9674   0.01866   0.01316   0.0532   0.1598   0.9681
  10.750   0.9879   0.01925   0.01376   0.0535   0.1573   0.9728
  11.000   0.9986   0.01999   0.01451   0.0554   0.1548   0.9786
  11.250   1.0231   0.02077   0.01527   0.0544   0.1513   0.9801
  11.500   1.0474   0.02150   0.01601   0.0535   0.1485   0.9818
  11.750   1.0712   0.02225   0.01677   0.0526   0.1465   0.9838
  12.000   1.0926   0.02308   0.01761   0.0521   0.1432   0.9859
  12.250   1.1101   0.02412   0.01864   0.0519   0.1401   0.9881
  12.500   1.1288   0.02503   0.01958   0.0517   0.1384   0.9900
  12.750   1.1465   0.02601   0.02057   0.0517   0.1361   0.9917
  13.000   1.1676   0.02704   0.02161   0.0506   0.1333   0.9930
  13.250   1.1878   0.02818   0.02275   0.0495   0.1304   0.9945
  13.500   1.2088   0.02935   0.02394   0.0482   0.1280   0.9960
  13.750   1.2304   0.03046   0.02508   0.0469   0.1253   0.9974
  14.000   1.2481   0.03186   0.02649   0.0457   0.1227   0.9986
  14.250   1.2627   0.03339   0.02803   0.0449   0.1198   0.9995
  14.500   1.2780   0.03475   0.02942   0.0443   0.1179   1.0000
  14.750   1.2832   0.03612   0.03082   0.0455   0.1160   1.0000
  15.000   1.2850   0.03781   0.03253   0.0466   0.1137   1.0000
  15.250   1.2858   0.03964   0.03439   0.0477   0.1117   1.0000
  15.500   1.2894   0.04130   0.03608   0.0486   0.1101   1.0000
  15.750   1.2923   0.04307   0.03789   0.0494   0.1082   1.0000
  16.000   1.2942   0.04495   0.03980   0.0501   0.1062   1.0000
  16.250   1.2931   0.04718   0.04206   0.0508   0.1044   1.0000
  16.500   1.2919   0.04944   0.04435   0.0513   0.1026   1.0000
  16.750   1.2941   0.05145   0.04642   0.0517   0.1015   1.0000
  17.000   1.2940   0.05371   0.04873   0.0521   0.0997   1.0000
  17.250   1.2923   0.05615   0.05120   0.0523   0.0976   1.0000
  17.500   1.2890   0.05885   0.05394   0.0525   0.0963   1.0000
  17.750   1.2844   0.06170   0.05683   0.0525   0.0939   1.0000
  18.000   1.2835   0.06422   0.05940   0.0525   0.0931   1.0000
  18.250   1.2799   0.06707   0.06231   0.0523   0.0915   1.0000
  18.500   1.2734   0.07025   0.06552   0.0521   0.0893   1.0000
  18.750   1.2640   0.07386   0.06917   0.0516   0.0875   1.0000
  19.000   1.2627   0.07658   0.07195   0.0513   0.0865   1.0000
  19.250   1.2567   0.07986   0.07529   0.0507   0.0847   1.0000
<< Back to NACA 23024 (naca23024-il)

Polar data table (+)

Polar graphs


<< Back to NACA 23024 (naca23024-il)