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NACA M24 AIRFOIL (m24-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA M24 AIRFOIL (m24-il)
Reynolds number: 100,000
Max Cl/Cd: 25.51 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m24-il-100000.txt
Download as CSV file: xf-m24-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M24 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2670   0.11225   0.10788  -0.0247   0.8005   0.0690
  -8.500  -0.2745   0.11171   0.10734  -0.0316   0.7932   0.0695
  -8.250  -0.2757   0.11021   0.10579  -0.0356   0.7870   0.0697
  -8.000  -0.2477   0.10112   0.09671  -0.0289   0.7814   0.0713
  -7.750  -0.2349   0.09748   0.09307  -0.0290   0.7742   0.0728
  -7.500  -0.2296   0.09470   0.09024  -0.0296   0.7687   0.0743
  -7.250  -0.2245   0.09216   0.08769  -0.0310   0.7627   0.0760
  -7.000  -0.2169   0.08954   0.08504  -0.0333   0.7563   0.0781
  -6.750  -0.2107   0.08759   0.08298  -0.0360   0.7515   0.0807
  -6.500  -0.1978   0.08970   0.08476  -0.0449   0.7450   0.0828
  -6.250  -0.1883   0.08284   0.07804  -0.0434   0.7395   0.0838
  -6.000  -0.1785   0.07872   0.07392  -0.0412   0.7350   0.0855
  -5.750  -0.1639   0.07581   0.07101  -0.0418   0.7287   0.0880
  -5.500  -0.1493   0.07331   0.06843  -0.0428   0.7228   0.0910
  -5.250  -0.1317   0.07191   0.06681  -0.0447   0.7184   0.0957
  -5.000  -0.1096   0.07076   0.06538  -0.0483   0.7123   0.0983
  -4.750  -0.0974   0.06639   0.06108  -0.0475   0.7067   0.0998
  -4.500  -0.0839   0.06355   0.05819  -0.0463   0.7024   0.1022
  -4.250  -0.0651   0.06145   0.05602  -0.0469   0.6966   0.1063
  -4.000  -0.0360   0.06176   0.05586  -0.0493   0.6904   0.1138
  -3.750  -0.0245   0.05752   0.05171  -0.0479   0.6864   0.1160
  -3.500  -0.0071   0.05533   0.04948  -0.0474   0.6814   0.1207
  -3.250   0.0209   0.05515   0.04894  -0.0488   0.6746   0.1302
  -3.000   0.0357   0.05185   0.04566  -0.0476   0.6704   0.1330
  -2.750   0.0550   0.05005   0.04373  -0.0466   0.6668   0.1393
  -2.500   0.0798   0.04907   0.04258  -0.0478   0.6591   0.1480
  -2.250   0.0992   0.04713   0.04057  -0.0469   0.6546   0.1547
  -2.000   0.1211   0.04555   0.03873  -0.0457   0.6514   0.1653
  -1.750   0.1447   0.04516   0.03823  -0.0466   0.6434   0.1793
  -1.250   0.1861   0.04187   0.03469  -0.0444   0.6356   0.2122
  -1.000   0.2054   0.04099   0.03386  -0.0446   0.6282   0.2322
  -0.750   0.2249   0.03970   0.03248  -0.0437   0.6230   0.2629
  -0.250   0.2639   0.03723   0.02989  -0.0417   0.6138   0.3315
   0.000   0.2869   0.03684   0.02935  -0.0414   0.6074   0.3545
   0.250   0.3174   0.03593   0.02816  -0.0408   0.6041   0.3537
   0.500   0.3882   0.03421   0.02485  -0.0413   0.6019   0.1098
   0.750   0.4091   0.03498   0.02562  -0.0424   0.5925   0.1095
   1.000   0.4382   0.03403   0.02448  -0.0419   0.5888   0.1079
   1.250   0.4696   0.03289   0.02310  -0.0412   0.5863   0.1076
   1.500   0.4891   0.03404   0.02430  -0.0420   0.5771   0.1089
   1.750   0.5180   0.03359   0.02370  -0.0417   0.5731   0.1123
   2.000   0.5511   0.03270   0.02284  -0.0418   0.5706   0.1233
   2.250   0.7236   0.03045   0.02252  -0.0701   0.5623   1.0000
   2.500   0.7455   0.03089   0.02278  -0.0693   0.5576   1.0000
   2.750   0.7699   0.03073   0.02242  -0.0679   0.5548   1.0000
   3.000   0.7847   0.03262   0.02432  -0.0679   0.5479   1.0000
   3.250   0.8012   0.03388   0.02555  -0.0673   0.5421   1.0000
   3.500   0.8254   0.03380   0.02535  -0.0661   0.5394   1.0000
   3.750   0.8519   0.03340   0.02480  -0.0648   0.5374   1.0000
   4.000   0.8452   0.03767   0.02927  -0.0644   0.5261   1.0000
   4.250   0.8693   0.03762   0.02914  -0.0632   0.5235   1.0000
   4.500   0.8967   0.03724   0.02866  -0.0621   0.5218   1.0000
   5.000   0.7614   0.05484   0.04661  -0.0538   0.4945   1.0000
   5.250   0.7811   0.05542   0.04715  -0.0526   0.4919   1.0000
   5.500   0.8179   0.05488   0.04655  -0.0524   0.4904   1.0000
   5.750   0.8603   0.05371   0.04533  -0.0523   0.4894   1.0000
   6.000   0.7224   0.06660   0.05830  -0.0442   0.4766   1.0000
   6.250   0.7536   0.06657   0.05821  -0.0435   0.4746   1.0000
   6.500   0.7127   0.07280   0.06448  -0.0415   0.4705   1.0000
   6.750   0.6882   0.07767   0.06938  -0.0403   0.4681   1.0000
   7.000   0.6817   0.08148   0.07321  -0.0397   0.4692   1.0000
   7.250   0.6798   0.08493   0.07667  -0.0393   0.4701   1.0000
   7.500   0.6946   0.08778   0.07953  -0.0396   0.4745   1.0000
   7.750   0.7135   0.08996   0.08171  -0.0393   0.4731   1.0000
   8.000   0.6250   0.09960   0.09151  -0.0395   0.4964   1.0000
   8.250   0.6464   0.10135   0.09323  -0.0393   0.4921   1.0000
   8.500   0.6843   0.10363   0.09551  -0.0399   0.4896   1.0000
   8.750   0.6520   0.10570   0.09760  -0.0380   0.4803   1.0000
   9.000   0.6739   0.10756   0.09946  -0.0379   0.4762   1.0000
   9.250   0.7113   0.11006   0.10197  -0.0385   0.4738   1.0000
   9.500   0.6791   0.11203   0.10397  -0.0368   0.4638   1.0000
   9.750   0.7048   0.11396   0.10591  -0.0368   0.4598   1.0000
  10.000   0.7416   0.11686   0.10885  -0.0375   0.4580   1.0000
  10.250   0.7039   0.11879   0.11081  -0.0361   0.4479   1.0000
  10.500   0.7314   0.12081   0.11286  -0.0361   0.4440   1.0000
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