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N-24 (n24-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: N-24 (n24-il)
Reynolds number: 50,000
Max Cl/Cd: 24.47 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n24-il-50000-n5.txt
Download as CSV file: xf-n24-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.2096   0.11113   0.10409  -0.0603   0.9723   0.0846
 -12.000  -0.1954   0.10684   0.09978  -0.0643   0.9661   0.0839
 -11.750  -0.1848   0.10244   0.09537  -0.0683   0.9589   0.0834
 -11.500  -0.1783   0.09806   0.09098  -0.0721   0.9505   0.0830
 -11.250  -0.1742   0.09331   0.08622  -0.0765   0.9426   0.0832
 -11.000  -0.1771   0.08868   0.08161  -0.0802   0.9320   0.0835
 -10.750  -0.1864   0.08392   0.07686  -0.0836   0.9198   0.0838
 -10.500  -0.2028   0.07876   0.07170  -0.0871   0.9068   0.0838
 -10.250  -0.2213   0.07189   0.06472  -0.0923   0.8954   0.0838
 -10.000  -0.2424   0.06510   0.05769  -0.0958   0.8839   0.0839
  -9.750  -0.2616   0.05926   0.05147  -0.0971   0.8718   0.0843
  -9.500  -0.2646   0.05353   0.04517  -0.0986   0.8640   0.0853
  -9.250  -0.2543   0.05197   0.04353  -0.0973   0.8535   0.0864
  -9.000  -0.2365   0.04970   0.04105  -0.0974   0.8465   0.0882
  -8.750  -0.2244   0.04734   0.03837  -0.0967   0.8377   0.0907
  -8.500  -0.2113   0.04419   0.03459  -0.0964   0.8295   0.0946
  -8.250  -0.1832   0.04325   0.03366  -0.0965   0.8245   0.0983
  -8.000  -0.1702   0.04179   0.03189  -0.0950   0.8138   0.1027
  -7.750  -0.1448   0.04045   0.03038  -0.0948   0.8079   0.1075
  -7.500  -0.1234   0.03924   0.02887  -0.0941   0.8004   0.1140
  -7.250  -0.1015   0.03869   0.02830  -0.0933   0.7921   0.1203
  -7.000  -0.0729   0.03765   0.02698  -0.0933   0.7871   0.1295
  -6.750  -0.0546   0.03752   0.02680  -0.0921   0.7777   0.1377
  -6.500  -0.0292   0.03730   0.02654  -0.0917   0.7712   0.1495
  -6.250   0.0006   0.03683   0.02598  -0.0917   0.7670   0.1630
  -6.000   0.0169   0.03676   0.02569  -0.0904   0.7563   0.1721
  -5.750   0.0458   0.03599   0.02487  -0.0902   0.7511   0.1785
  -5.500   0.0714   0.03556   0.02431  -0.0898   0.7447   0.1859
  -5.250   0.0939   0.03528   0.02385  -0.0891   0.7363   0.1926
  -5.000   0.1247   0.03464   0.02320  -0.0891   0.7316   0.1999
  -4.750   0.1478   0.03454   0.02294  -0.0885   0.7237   0.2093
  -4.500   0.1730   0.03432   0.02276  -0.0880   0.7165   0.2190
  -4.250   0.2060   0.03373   0.02207  -0.0883   0.7121   0.2327
  -4.000   0.2257   0.03392   0.02224  -0.0874   0.7028   0.2458
  -3.750   0.2542   0.03357   0.02190  -0.0872   0.6963   0.2647
  -3.500   0.2886   0.03284   0.02118  -0.0874   0.6921   0.2909
  -3.250   0.3045   0.03319   0.02163  -0.0861   0.6805   0.3133
  -3.000   0.3369   0.03248   0.02100  -0.0860   0.6751   0.3522
  -2.750   0.3556   0.03256   0.02133  -0.0849   0.6652   0.3991
  -2.500   0.3817   0.03191   0.02109  -0.0840   0.6586   0.4840
  -2.250   0.4104   0.03058   0.02051  -0.0824   0.6545   0.6604
  -2.000   0.4663   0.03065   0.02101  -0.0878   0.6432   1.0002
  -1.750   0.4974   0.03045   0.02048  -0.0878   0.6378   1.0002
  -1.500   0.5136   0.03116   0.02101  -0.0864   0.6281   1.0002
  -1.250   0.5405   0.03120   0.02082  -0.0860   0.6213   1.0002
  -1.000   0.5711   0.03105   0.02042  -0.0858   0.6158   1.0002
  -0.750   0.5841   0.03196   0.02124  -0.0842   0.6050   1.0002
  -0.500   0.6170   0.03166   0.02072  -0.0843   0.6000   1.0002
  -0.250   0.6290   0.03265   0.02163  -0.0826   0.5891   1.0002
   0.000   0.6591   0.03252   0.02133  -0.0825   0.5830   1.0002
   0.250   0.6772   0.03317   0.02188  -0.0813   0.5740   1.0002
   0.500   0.7007   0.03345   0.02204  -0.0806   0.5660   1.0002
   0.750   0.7373   0.03297   0.02138  -0.0811   0.5615   1.0002
   1.000   0.7420   0.03441   0.02282  -0.0788   0.5492   1.0002
   1.250   0.7766   0.03406   0.02231  -0.0791   0.5440   1.0002
   1.500   0.7830   0.03544   0.02369  -0.0770   0.5327   1.0002
   1.750   0.8137   0.03531   0.02344  -0.0770   0.5266   1.0002
   2.000   0.8255   0.03638   0.02447  -0.0754   0.5170   1.0002
   2.250   0.8481   0.03676   0.02479  -0.0747   0.5094   1.0002
   2.500   0.8867   0.03624   0.02412  -0.0756   0.5051   1.0002
   2.750   0.8781   0.03856   0.02651  -0.0722   0.4927   1.0002
   3.000   0.9134   0.03822   0.02606  -0.0727   0.4879   1.0002
   3.250   0.9025   0.04066   0.02857  -0.0692   0.4766   1.0002
   3.500   0.9316   0.04068   0.02851  -0.0692   0.4711   1.0002
   3.750   0.9308   0.04262   0.03046  -0.0667   0.4625   1.0002
   4.000   0.9390   0.04407   0.03192  -0.0651   0.4548   1.0002
   4.250   0.9763   0.04353   0.03130  -0.0657   0.4513   1.0002
   4.500   0.9427   0.04831   0.03620  -0.0618   0.4389   1.0002
   4.750   0.9729   0.04811   0.03594  -0.0617   0.4349   1.0002
   5.000   1.0088   0.04754   0.03530  -0.0621   0.4318   1.0002
   5.250   0.9628   0.05416   0.04208  -0.0587   0.4186   1.0002
   5.500   0.9973   0.05346   0.04134  -0.0586   0.4161   1.0002
   6.000   0.9779   0.06112   0.04911  -0.0563   0.3996   1.0002
   6.250   1.0105   0.06044   0.04840  -0.0561   0.3974   1.0002
   6.750   0.9712   0.07144   0.05956  -0.0547   0.3792   1.0002
   7.250   0.9593   0.07983   0.06806  -0.0544   0.3645   1.0002
   8.250   0.9179   0.09980   0.08826  -0.0553   0.3330   1.0002
   8.500   0.9438   0.09953   0.08802  -0.0547   0.3302   1.0002
  10.000   0.9558   0.11847   0.10723  -0.0559   0.2915   1.0002
  10.250   0.9366   0.12496   0.11380  -0.0573   0.2811   1.0002
  10.500   0.9586   0.12504   0.11392  -0.0569   0.2779   1.0002
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