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NACA M24 AIRFOIL (m24-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M24 AIRFOIL (m24-il)
Reynolds number: 200,000
Max Cl/Cd: 71.21 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m24-il-200000-n5.txt
Download as CSV file: xf-m24-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3027   0.09994   0.09557  -0.0060   0.6410   0.0336
  -8.000  -0.3058   0.09671   0.09231  -0.0119   0.6377   0.0340
  -7.750  -0.3066   0.09369   0.08924  -0.0167   0.6344   0.0342
  -7.500  -0.2988   0.08964   0.08519  -0.0179   0.6302   0.0344
  -7.250  -0.2878   0.08615   0.08168  -0.0167   0.6257   0.0348
  -7.000  -0.2775   0.08308   0.07857  -0.0171   0.6218   0.0352
  -6.750  -0.2667   0.08013   0.07556  -0.0182   0.6180   0.0357
  -6.500  -0.2546   0.07717   0.07257  -0.0197   0.6136   0.0363
  -6.250  -0.2415   0.07419   0.06953  -0.0214   0.6096   0.0372
  -6.000  -0.2271   0.07119   0.06643  -0.0232   0.6060   0.0383
  -5.500  -0.1838   0.06445   0.05926  -0.0305   0.5990   0.0414
  -5.250  -0.1712   0.06115   0.05595  -0.0301   0.5947   0.0418
  -5.000  -0.1553   0.05852   0.05327  -0.0300   0.5908   0.0423
  -4.750  -0.1374   0.05611   0.05075  -0.0302   0.5874   0.0431
  -4.500  -0.1175   0.05372   0.04828  -0.0307   0.5833   0.0440
  -4.250  -0.0960   0.05133   0.04578  -0.0312   0.5790   0.0454
  -4.000  -0.0616   0.04906   0.04305  -0.0328   0.5753   0.0492
  -3.750  -0.0441   0.04576   0.03962  -0.0326   0.5721   0.0498
  -3.500  -0.0257   0.04369   0.03753  -0.0323   0.5683   0.0506
  -3.250  -0.0041   0.04186   0.03564  -0.0323   0.5639   0.0517
  -3.000   0.0251   0.03647   0.02964  -0.0313   0.5608   0.0415
  -2.750   0.0461   0.03521   0.02835  -0.0311   0.5569   0.0401
  -2.500   0.0697   0.03320   0.02614  -0.0307   0.5536   0.0389
  -2.250   0.0949   0.03088   0.02359  -0.0302   0.5495   0.0378
  -2.000   0.1208   0.02870   0.02115  -0.0296   0.5455   0.0377
  -1.750   0.1471   0.02669   0.01884  -0.0290   0.5418   0.0383
  -1.500   0.1736   0.02440   0.01616  -0.0283   0.5387   0.0375
  -1.250   0.2013   0.02225   0.01363  -0.0278   0.5348   0.0369
  -1.000   0.2298   0.02069   0.01175  -0.0275   0.5306   0.0368
  -0.750   0.2585   0.01959   0.01039  -0.0275   0.5266   0.0370
  -0.500   0.2872   0.01876   0.00931  -0.0275   0.5231   0.0373
  -0.250   0.3162   0.01810   0.00851  -0.0276   0.5191   0.0378
   0.000   0.3450   0.01761   0.00793  -0.0278   0.5148   0.0389
   0.250   0.3735   0.01720   0.00741  -0.0279   0.5108   0.0402
   0.500   0.4016   0.01682   0.00691  -0.0279   0.5072   0.0409
   0.750   0.4296   0.01648   0.00653  -0.0279   0.5032   0.0412
   1.000   0.4568   0.01608   0.00617  -0.0279   0.4989   0.0421
   1.250   0.4836   0.01583   0.00593  -0.0277   0.4951   0.0431
   1.500   0.5102   0.01566   0.00572  -0.0276   0.4917   0.0444
   1.750   0.5369   0.01553   0.00559  -0.0274   0.4878   0.0460
   2.000   0.5637   0.01544   0.00551  -0.0273   0.4834   0.0484
   2.250   0.5903   0.01535   0.00545  -0.0272   0.4793   0.0531
   2.500   0.6167   0.01529   0.00538  -0.0270   0.4760   0.0600
   2.750   0.6427   0.01523   0.00538  -0.0267   0.4725   0.0823
   3.000   0.6685   0.01518   0.00548  -0.0265   0.4683   0.1274
   3.250   0.6942   0.01511   0.00557  -0.0263   0.4642   0.1955
   3.750   0.8743   0.01463   0.00663  -0.0527   0.4533   0.9968
   4.000   0.9134   0.01474   0.00672  -0.0554   0.4491   1.0000
   4.250   0.9388   0.01488   0.00679  -0.0552   0.4456   1.0000
   4.500   0.9640   0.01503   0.00688  -0.0550   0.4422   1.0000
   4.750   0.9892   0.01520   0.00709  -0.0548   0.4378   1.0000
   5.000   1.0142   0.01536   0.00726  -0.0546   0.4338   1.0000
   5.250   1.0389   0.01554   0.00741  -0.0543   0.4305   1.0000
   5.500   1.0635   0.01573   0.00755  -0.0539   0.4276   1.0000
   5.750   1.0879   0.01595   0.00784  -0.0537   0.4238   1.0000
   6.000   1.1121   0.01616   0.00810  -0.0534   0.4199   1.0000
   6.250   1.1360   0.01637   0.00833  -0.0530   0.4162   1.0000
   6.500   1.1598   0.01659   0.00852  -0.0526   0.4130   1.0000
   6.750   1.1833   0.01684   0.00883  -0.0522   0.4095   1.0000
   7.000   1.2064   0.01712   0.00919  -0.0518   0.4059   1.0000
   7.250   1.2293   0.01738   0.00951  -0.0513   0.4025   1.0000
   7.500   1.2521   0.01765   0.00980  -0.0507   0.3995   1.0000
   7.750   1.2748   0.01792   0.01006  -0.0501   0.3967   1.0000
   8.000   1.2962   0.01825   0.01053  -0.0495   0.3922   1.0000
   8.250   1.3171   0.01854   0.01089  -0.0488   0.3869   1.0000
   8.500   1.3380   0.01879   0.01111  -0.0479   0.3816   1.0000
   8.750   1.3568   0.01913   0.01160  -0.0469   0.3744   1.0000
   9.000   1.3754   0.01943   0.01190  -0.0458   0.3673   1.0000
   9.250   1.3927   0.01982   0.01238  -0.0445   0.3602   1.0000
   9.500   1.4086   0.02021   0.01280  -0.0431   0.3524   1.0000
   9.750   1.4223   0.02068   0.01336  -0.0413   0.3433   1.0000
  10.000   1.4339   0.02119   0.01388  -0.0393   0.3352   1.0000
  10.250   1.4438   0.02178   0.01457  -0.0371   0.3267   1.0000
  10.500   1.4477   0.02252   0.01534  -0.0341   0.3167   1.0000
  10.750   1.4400   0.02352   0.01634  -0.0295   0.3062   1.0000
  11.000   1.4332   0.02477   0.01763  -0.0257   0.2946   1.0000
  11.250   1.4280   0.02633   0.01920  -0.0229   0.2816   1.0000
  11.500   1.4221   0.02828   0.02116  -0.0205   0.2660   1.0000
  11.750   1.4119   0.03085   0.02367  -0.0185   0.2468   1.0000
  12.000   1.3967   0.03412   0.02684  -0.0168   0.2213   1.0000
  12.250   1.3769   0.03805   0.03067  -0.0153   0.1959   1.0000
  12.500   1.3551   0.04240   0.03492  -0.0140   0.1738   1.0000
  12.750   1.3327   0.04700   0.03943  -0.0130   0.1525   1.0000
  13.000   1.3070   0.05226   0.04458  -0.0124   0.1253   1.0000
  13.250   1.2810   0.05788   0.05007  -0.0121   0.0980   1.0000
  13.500   1.2592   0.06322   0.05533  -0.0120   0.0807   1.0000
  14.000   1.2222   0.07366   0.06562  -0.0124   0.0403   1.0000
  14.250   1.2091   0.07840   0.07033  -0.0128   0.0318   1.0000
  14.500   1.2022   0.08244   0.07442  -0.0132   0.0283   1.0000
  14.750   1.1960   0.08644   0.07848  -0.0136   0.0260   1.0000
  15.000   1.1922   0.09016   0.08228  -0.0141   0.0245   1.0000
  15.250   1.1894   0.09381   0.08602  -0.0146   0.0233   1.0000
  15.500   1.1861   0.09755   0.08986  -0.0151   0.0223   1.0000
  15.750   1.1822   0.10139   0.09379  -0.0158   0.0215   1.0000
  16.000   1.1776   0.10540   0.09789  -0.0165   0.0208   1.0000
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