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N-24 (n24-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: N-24 (n24-il)
Reynolds number: 100,000
Max Cl/Cd: 47.01 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n24-il-100000-n5.txt
Download as CSV file: xf-n24-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-24                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.2148   0.09902   0.09374  -0.0608   0.9031   0.0530
 -12.250  -0.2206   0.09405   0.08876  -0.0631   0.8957   0.0528
 -11.750  -0.4098   0.05050   0.04457  -0.0984   0.8732   0.0516
 -11.500  -0.4134   0.04714   0.04096  -0.0984   0.8654   0.0521
 -11.250  -0.4100   0.04427   0.03782  -0.0983   0.8575   0.0526
 -11.000  -0.4036   0.04153   0.03478  -0.0977   0.8495   0.0533
 -10.750  -0.3950   0.03892   0.03182  -0.0966   0.8439   0.0539
 -10.500  -0.3815   0.03653   0.02909  -0.0961   0.8354   0.0547
 -10.250  -0.3664   0.03434   0.02652  -0.0951   0.8288   0.0556
 -10.000  -0.3497   0.03228   0.02403  -0.0937   0.8237   0.0567
  -9.750  -0.3267   0.03148   0.02320  -0.0932   0.8150   0.0576
  -9.500  -0.3048   0.03053   0.02212  -0.0922   0.8086   0.0587
  -9.250  -0.2825   0.02947   0.02086  -0.0912   0.8028   0.0603
  -9.000  -0.2590   0.02832   0.01943  -0.0906   0.7947   0.0628
  -8.750  -0.2349   0.02772   0.01879  -0.0898   0.7889   0.0648
  -8.500  -0.2104   0.02691   0.01778  -0.0890   0.7825   0.0680
  -8.250  -0.1854   0.02617   0.01695  -0.0885   0.7746   0.0711
  -8.000  -0.1606   0.02538   0.01599  -0.0875   0.7688   0.0753
  -7.750  -0.1351   0.02472   0.01528  -0.0871   0.7613   0.0798
  -7.500  -0.1093   0.02408   0.01450  -0.0865   0.7542   0.0858
  -7.250  -0.0836   0.02355   0.01394  -0.0858   0.7490   0.0917
  -7.000  -0.0569   0.02322   0.01358  -0.0856   0.7410   0.0981
  -6.750  -0.0300   0.02286   0.01312  -0.0852   0.7341   0.1049
  -6.500  -0.0033   0.02254   0.01276  -0.0845   0.7289   0.1110
  -6.250   0.0242   0.02239   0.01257  -0.0845   0.7202   0.1179
  -6.000   0.0516   0.02218   0.01228  -0.0842   0.7142   0.1252
  -5.750   0.0791   0.02193   0.01198  -0.0838   0.7086   0.1316
  -5.500   0.1067   0.02182   0.01182  -0.0838   0.7006   0.1394
  -5.250   0.1342   0.02156   0.01154  -0.0834   0.6946   0.1469
  -5.000   0.1620   0.02136   0.01126  -0.0832   0.6884   0.1550
  -4.750   0.1893   0.02112   0.01106  -0.0831   0.6811   0.1616
  -4.500   0.2169   0.02080   0.01067  -0.0827   0.6750   0.1692
  -4.250   0.2440   0.02055   0.01043  -0.0824   0.6664   0.1779
  -4.000   0.2714   0.02027   0.01009  -0.0820   0.6579   0.1899
  -3.750   0.2985   0.02002   0.00987  -0.0817   0.6492   0.2042
  -3.500   0.3258   0.01981   0.00968  -0.0815   0.6407   0.2217
  -3.250   0.3538   0.01960   0.00945  -0.0812   0.6347   0.2424
  -3.000   0.3810   0.01954   0.00947  -0.0812   0.6265   0.2660
  -2.750   0.4089   0.01937   0.00933  -0.0811   0.6201   0.2942
  -2.500   0.4368   0.01925   0.00928  -0.0811   0.6135   0.3299
  -2.250   0.4643   0.01912   0.00933  -0.0811   0.6059   0.3808
  -2.000   0.4919   0.01883   0.00924  -0.0810   0.6000   0.4574
  -1.750   0.5168   0.01852   0.00938  -0.0804   0.5928   0.5764
  -1.500   0.5849   0.01772   0.00944  -0.0876   0.5844   0.9940
  -1.250   0.6145   0.01785   0.00937  -0.0880   0.5779   1.0002
  -1.000   0.6399   0.01807   0.00949  -0.0877   0.5698   1.0002
  -0.750   0.6664   0.01819   0.00943  -0.0874   0.5632   1.0002
  -0.500   0.6920   0.01842   0.00955  -0.0871   0.5559   1.0002
  -0.250   0.7177   0.01863   0.00965  -0.0869   0.5483   1.0002
   0.000   0.7444   0.01876   0.00961  -0.0866   0.5418   1.0002
   0.250   0.7688   0.01906   0.00988  -0.0863   0.5329   1.0002
   0.500   0.7949   0.01923   0.00991  -0.0860   0.5256   1.0002
   0.750   0.8196   0.01951   0.01013  -0.0857   0.5174   1.0002
   1.000   0.8446   0.01975   0.01029  -0.0854   0.5095   1.0002
   1.250   0.8701   0.01999   0.01042  -0.0852   0.5022   1.0002
   1.500   0.8937   0.02030   0.01071  -0.0847   0.4931   1.0002
   1.750   0.9193   0.02051   0.01078  -0.0845   0.4858   1.0002
   2.000   0.9415   0.02089   0.01118  -0.0839   0.4760   1.0002
   2.250   0.9663   0.02112   0.01129  -0.0836   0.4685   1.0002
   2.500   0.9881   0.02153   0.01172  -0.0830   0.4593   1.0002
   2.750   1.0118   0.02183   0.01193  -0.0826   0.4517   1.0002
   3.000   1.0334   0.02224   0.01234  -0.0820   0.4431   1.0002
   3.250   1.0557   0.02259   0.01262  -0.0814   0.4351   1.0002
   3.500   1.0769   0.02300   0.01301  -0.0807   0.4272   1.0002
   3.750   1.0978   0.02342   0.01340  -0.0800   0.4194   1.0002
   4.000   1.1197   0.02382   0.01372  -0.0794   0.4130   1.0002
   4.250   1.1389   0.02434   0.01427  -0.0786   0.4057   1.0002
   4.500   1.1599   0.02476   0.01462  -0.0779   0.3997   1.0002
   4.750   1.1791   0.02529   0.01515  -0.0771   0.3933   1.0002
   5.000   1.1971   0.02585   0.01571  -0.0761   0.3870   1.0002
   5.250   1.2179   0.02630   0.01608  -0.0755   0.3819   1.0002
   5.500   1.2356   0.02692   0.01672  -0.0745   0.3766   1.0002
   5.750   1.2512   0.02757   0.01740  -0.0733   0.3711   1.0002
   6.000   1.2691   0.02811   0.01791  -0.0723   0.3663   1.0002
   6.250   1.2883   0.02868   0.01843  -0.0716   0.3619   1.0002
   6.500   1.2999   0.02951   0.01935  -0.0699   0.3568   1.0002
   6.750   1.3144   0.03025   0.02011  -0.0687   0.3519   1.0002
   7.000   1.3343   0.03078   0.02056  -0.0681   0.3471   1.0002
   7.250   1.3435   0.03175   0.02161  -0.0664   0.3414   1.0002
   7.500   1.3525   0.03272   0.02263  -0.0648   0.3352   1.0002
   7.750   1.3700   0.03333   0.02316  -0.0641   0.3297   1.0002
   8.000   1.3775   0.03450   0.02440  -0.0625   0.3242   1.0002
   8.250   1.3855   0.03568   0.02568  -0.0611   0.3189   1.0002
   8.500   1.3998   0.03657   0.02658  -0.0603   0.3145   1.0002
   8.750   1.4224   0.03706   0.02699  -0.0602   0.3108   1.0002
   9.000   1.4240   0.03875   0.02887  -0.0585   0.3065   1.0002
   9.250   1.4303   0.04022   0.03046  -0.0573   0.3021   1.0002
   9.500   1.4413   0.04138   0.03167  -0.0565   0.2979   1.0002
   9.750   1.4604   0.04202   0.03227  -0.0562   0.2941   1.0002
  10.000   1.4602   0.04403   0.03444  -0.0548   0.2897   1.0002
  10.250   1.4592   0.04616   0.03674  -0.0535   0.2849   1.0002
  10.500   1.4658   0.04771   0.03835  -0.0527   0.2805   1.0002
  10.750   1.4832   0.04842   0.03902  -0.0524   0.2766   1.0002
  11.000   1.4743   0.05141   0.04221  -0.0512   0.2720   1.0002
  11.250   1.4675   0.05433   0.04530  -0.0502   0.2672   1.0002
  11.500   1.4718   0.05623   0.04728  -0.0496   0.2629   1.0002
  11.750   1.4904   0.05677   0.04777  -0.0495   0.2593   1.0002
  12.000   1.4640   0.06202   0.05332  -0.0486   0.2539   1.0002
  12.250   1.4536   0.06581   0.05725  -0.0482   0.2488   1.0002
  12.500   1.4628   0.06735   0.05881  -0.0481   0.2447   1.0002
  12.750   1.4510   0.07153   0.06313  -0.0480   0.2398   1.0002
  13.000   1.4194   0.07846   0.07029  -0.0484   0.2334   1.0002
  13.250   1.4288   0.08008   0.07192  -0.0485   0.2291   1.0002
  13.500   1.3992   0.08719   0.07921  -0.0493   0.2231   1.0002
  13.750   1.3673   0.09493   0.08711  -0.0506   0.2162   1.0002
  14.000   1.3909   0.09450   0.08665  -0.0505   0.2131   1.0002
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