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=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 23024 (naca23024-il)
Reynolds number: 200,000
Max Cl/Cd: 33.18 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca23024-il-200000-n5.txt
Download as CSV file: xf-naca23024-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.9467   0.09303   0.08617  -0.0654   1.0000   0.0895
 -19.500  -0.9480   0.09008   0.08316  -0.0660   1.0000   0.0914
 -19.250  -0.9490   0.08727   0.08035  -0.0664   1.0000   0.0930
 -19.000  -0.9509   0.08433   0.07739  -0.0668   1.0000   0.0949
 -18.750  -0.9526   0.08142   0.07442  -0.0672   1.0000   0.0970
 -18.500  -0.9534   0.07867   0.07161  -0.0675   1.0000   0.0992
 -18.250  -0.9563   0.07578   0.06872  -0.0677   1.0000   0.1011
 -18.000  -0.9589   0.07292   0.06584  -0.0679   1.0000   0.1034
 -17.750  -0.9600   0.07025   0.06311  -0.0679   1.0000   0.1060
 -17.500  -0.9616   0.06762   0.06043  -0.0679   1.0000   0.1083
 -17.250  -0.9654   0.06482   0.05763  -0.0678   1.0000   0.1109
 -17.000  -0.9676   0.06221   0.05498  -0.0675   1.0000   0.1138
 -16.750  -0.9673   0.05993   0.05264  -0.0671   1.0000   0.1166
 -16.500  -0.9715   0.05728   0.05000  -0.0667   1.0000   0.1193
 -16.250  -0.9742   0.05485   0.04753  -0.0661   1.0000   0.1227
 -15.750  -0.9782   0.05037   0.04301  -0.0644   1.0000   0.1293
 -15.500  -0.9804   0.04822   0.04084  -0.0634   1.0000   0.1329
 -15.250  -0.9800   0.04639   0.03896  -0.0621   1.0000   0.1369
 -15.000  -0.9843   0.04428   0.03686  -0.0607   1.0000   0.1407
 -14.750  -0.9857   0.04249   0.03505  -0.0591   1.0000   0.1451
 -14.500  -0.9869   0.04083   0.03337  -0.0574   1.0000   0.1492
 -14.250  -0.9902   0.03913   0.03167  -0.0553   1.0000   0.1535
 -14.000  -0.9907   0.03774   0.03025  -0.0532   1.0000   0.1584
 -13.750  -0.9948   0.03625   0.02878  -0.0506   1.0000   0.1628
 -13.500  -0.9978   0.03497   0.02749  -0.0479   1.0000   0.1677
 -13.250  -1.0000   0.03386   0.02636  -0.0450   1.0000   0.1724
 -13.000  -0.9911   0.03247   0.02498  -0.0444   0.9983   0.1786
 -12.750  -0.9687   0.03125   0.02374  -0.0458   0.9946   0.1862
 -12.500  -0.9487   0.02999   0.02249  -0.0468   0.9904   0.1939
 -12.250  -0.9287   0.02887   0.02136  -0.0474   0.9857   0.2011
 -12.000  -0.9071   0.02784   0.02033  -0.0482   0.9811   0.2092
 -11.750  -0.8852   0.02687   0.01937  -0.0489   0.9768   0.2169
 -11.500  -0.8672   0.02598   0.01846  -0.0486   0.9697   0.2243
 -11.000  -0.8274   0.02436   0.01684  -0.0483   0.9567   0.2393
 -10.750  -0.8037   0.02365   0.01612  -0.0486   0.9509   0.2467
 -10.500  -0.7856   0.02294   0.01543  -0.0478   0.9432   0.2540
 -10.250  -0.7625   0.02235   0.01479  -0.0476   0.9362   0.2614
 -10.000  -0.7371   0.02164   0.01412  -0.0480   0.9317   0.2690
  -9.750  -0.7197   0.02114   0.01358  -0.0466   0.9217   0.2761
  -9.500  -0.6935   0.02052   0.01298  -0.0469   0.9159   0.2835
  -9.250  -0.6644   0.01996   0.01241  -0.0476   0.9101   0.2918
  -9.000  -0.6418   0.01950   0.01194  -0.0470   0.9004   0.2991
  -8.750  -0.6086   0.01896   0.01141  -0.0485   0.8945   0.3073
  -8.500  -0.5763   0.01853   0.01094  -0.0497   0.8866   0.3155
  -8.250  -0.5480   0.01809   0.01053  -0.0502   0.8764   0.3233
  -8.000  -0.5031   0.01765   0.01003  -0.0538   0.8694   0.3327
  -7.750  -0.4745   0.01730   0.00971  -0.0542   0.8578   0.3400
  -7.500  -0.4347   0.01692   0.00930  -0.0569   0.8471   0.3488
  -7.250  -0.4055   0.01665   0.00898  -0.0573   0.8342   0.3561
  -7.000  -0.3716   0.01633   0.00865  -0.0586   0.8213   0.3641
  -6.750  -0.3489   0.01613   0.00839  -0.0577   0.8063   0.3716
  -6.500  -0.3209   0.01589   0.00812  -0.0578   0.7926   0.3788
  -6.250  -0.3004   0.01571   0.00791  -0.0563   0.7774   0.3860
  -6.000  -0.2797   0.01557   0.00769  -0.0549   0.7632   0.3937
  -5.750  -0.2574   0.01540   0.00748  -0.0537   0.7489   0.4006
  -5.500  -0.2425   0.01527   0.00734  -0.0511   0.7341   0.4079
  -5.250  -0.2233   0.01518   0.00714  -0.0492   0.7210   0.4155
  -5.000  -0.2081   0.01506   0.00702  -0.0466   0.7071   0.4223
  -4.750  -0.1919   0.01497   0.00689  -0.0441   0.6945   0.4300
  -4.500  -0.1774   0.01491   0.00676  -0.0413   0.6817   0.4378
  -4.250  -0.1622   0.01482   0.00667  -0.0387   0.6696   0.4451
  -4.000  -0.1488   0.01476   0.00659  -0.0356   0.6573   0.4528
  -3.500  -0.1211   0.01467   0.00644  -0.0296   0.6341   0.4684
  -3.250  -0.1072   0.01464   0.00637  -0.0266   0.6234   0.4765
  -3.000  -0.0956   0.01463   0.00633  -0.0231   0.6120   0.4845
  -2.500  -0.0716   0.01460   0.00629  -0.0163   0.5910   0.5012
  -2.250  -0.0582   0.01460   0.00624  -0.0132   0.5802   0.5093
  -2.000  -0.0450   0.01458   0.00624  -0.0100   0.5701   0.5182
  -1.750  -0.0326   0.01459   0.00621  -0.0067   0.5593   0.5276
  -1.500  -0.0183   0.01458   0.00620  -0.0038   0.5495   0.5360
  -1.250  -0.0058   0.01457   0.00620  -0.0005   0.5389   0.5454
  -1.000   0.0077   0.01460   0.00617   0.0026   0.5293   0.5546
  -0.750   0.0206   0.01458   0.00620   0.0058   0.5192   0.5642
  -0.500   0.0328   0.01461   0.00618   0.0092   0.5098   0.5743
  -0.250   0.0464   0.01460   0.00621   0.0122   0.5010   0.5841
   0.000   0.0569   0.01460   0.00622   0.0159   0.4915   0.5944
   0.250   0.0687   0.01463   0.00622   0.0193   0.4832   0.6045
   0.500   0.0807   0.01462   0.00627   0.0227   0.4743   0.6155
   0.750   0.0923   0.01466   0.00629   0.0262   0.4660   0.6265
   1.000   0.1064   0.01470   0.00636   0.0291   0.4582   0.6380
   1.500   0.1329   0.01481   0.00650   0.0352   0.4415   0.6610
   1.750   0.1456   0.01487   0.00657   0.0383   0.4336   0.6735
   2.000   0.1614   0.01494   0.00670   0.0408   0.4250   0.6857
   2.500   0.1920   0.01512   0.00694   0.0460   0.4092   0.7122
   2.750   0.2058   0.01523   0.00706   0.0488   0.4011   0.7255
   3.000   0.2241   0.01536   0.00723   0.0507   0.3938   0.7399
   3.250   0.2429   0.01549   0.00741   0.0524   0.3855   0.7537
   3.500   0.2591   0.01565   0.00758   0.0547   0.3778   0.7688
   3.750   0.2835   0.01583   0.00783   0.0552   0.3696   0.7830
   4.000   0.3038   0.01603   0.00805   0.0566   0.3615   0.7981
   4.250   0.3293   0.01628   0.00831   0.0568   0.3539   0.8126
   4.500   0.3590   0.01653   0.00861   0.0561   0.3451   0.8261
   4.750   0.3830   0.01683   0.00889   0.0565   0.3372   0.8406
   5.000   0.4234   0.01719   0.00929   0.0536   0.3284   0.8514
   5.250   0.4543   0.01756   0.00965   0.0525   0.3201   0.8639
   5.500   0.4949   0.01799   0.01008   0.0495   0.3119   0.8722
   5.750   0.5338   0.01845   0.01055   0.0467   0.3034   0.8804
   6.000   0.5572   0.01890   0.01095   0.0470   0.2970   0.8916
   6.250   0.5969   0.01941   0.01150   0.0441   0.2890   0.8968
   6.500   0.6270   0.01996   0.01202   0.0430   0.2820   0.9039
   6.750   0.6493   0.02044   0.01251   0.0434   0.2761   0.9133
   7.000   0.6818   0.02103   0.01310   0.0418   0.2693   0.9178
   7.250   0.7059   0.02164   0.01368   0.0417   0.2639   0.9247
   7.500   0.7266   0.02219   0.01424   0.0423   0.2589   0.9330
   7.750   0.7540   0.02281   0.01487   0.0414   0.2531   0.9379
   8.000   0.7710   0.02344   0.01548   0.0425   0.2486   0.9474
   8.250   0.7969   0.02413   0.01615   0.0417   0.2439   0.9521
   8.500   0.8216   0.02476   0.01682   0.0412   0.2390   0.9585
   8.750   0.8415   0.02547   0.01752   0.0414   0.2344   0.9656
   9.000   0.8650   0.02628   0.01829   0.0406   0.2300   0.9706
   9.250   0.8857   0.02701   0.01907   0.0407   0.2261   0.9777
   9.500   0.9133   0.02773   0.01982   0.0392   0.2217   0.9811
   9.750   0.9380   0.02856   0.02065   0.0380   0.2177   0.9855
  10.000   0.9601   0.02951   0.02155   0.0372   0.2141   0.9900
  10.250   0.9860   0.03033   0.02245   0.0358   0.2100   0.9938
  10.500   1.0116   0.03122   0.02338   0.0342   0.2059   0.9975
  10.750   1.0340   0.03222   0.02437   0.0330   0.2024   1.0000
  11.000   1.0337   0.03310   0.02520   0.0359   0.1999   1.0000
  11.250   1.0370   0.03389   0.02606   0.0384   0.1973   1.0000
  11.500   1.0398   0.03480   0.02702   0.0408   0.1944   1.0000
  11.750   1.0426   0.03579   0.02803   0.0430   0.1918   1.0000
  12.000   1.0449   0.03688   0.02911   0.0451   0.1891   1.0000
  12.250   1.0474   0.03803   0.03023   0.0470   0.1866   1.0000
  12.500   1.0522   0.03915   0.03141   0.0487   0.1842   1.0000
  12.750   1.0559   0.04040   0.03273   0.0502   0.1814   1.0000
  13.000   1.0596   0.04171   0.03408   0.0517   0.1787   1.0000
  13.250   1.0622   0.04315   0.03552   0.0531   0.1761   1.0000
  13.500   1.0664   0.04450   0.03686   0.0543   0.1740   1.0000
  13.750   1.0698   0.04603   0.03844   0.0554   0.1715   1.0000
  14.000   1.0727   0.04766   0.04015   0.0563   0.1688   1.0000
  14.250   1.0746   0.04943   0.04197   0.0572   0.1662   1.0000
  14.500   1.0771   0.05118   0.04374   0.0580   0.1638   1.0000
  14.750   1.0808   0.05284   0.04537   0.0587   0.1617   1.0000
  15.000   1.0824   0.05482   0.04743   0.0592   0.1593   1.0000
  15.250   1.0825   0.05701   0.04972   0.0596   0.1566   1.0000
  15.500   1.0833   0.05916   0.05193   0.0600   0.1543   1.0000
  15.750   1.0845   0.06130   0.05408   0.0602   0.1521   1.0000
  16.000   1.0880   0.06316   0.05591   0.0605   0.1500   1.0000
  16.250   1.0855   0.06587   0.05875   0.0605   0.1477   1.0000
  16.500   1.0829   0.06863   0.06160   0.0604   0.1452   1.0000
  16.750   1.0810   0.07132   0.06435   0.0602   0.1428   1.0000
  17.000   1.0808   0.07383   0.06687   0.0600   0.1407   1.0000
  17.250   1.0808   0.07634   0.06940   0.0597   0.1385   1.0000
  17.500   1.0728   0.07999   0.07318   0.0590   0.1360   1.0000
  17.750   1.0668   0.08341   0.07669   0.0583   0.1336   1.0000
  18.000   1.0644   0.08639   0.07970   0.0577   0.1315   1.0000
  18.250   1.0681   0.08854   0.08182   0.0574   0.1296   1.0000
  18.500   1.0565   0.09285   0.08627   0.0562   0.1273   1.0000
  18.750   1.0444   0.09730   0.09084   0.0549   0.1249   1.0000
<< Back to NACA 23024 (naca23024-il)

Polar data table (+)

Polar graphs


<< Back to NACA 23024 (naca23024-il)