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NACA M24 AIRFOIL (m24-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA M24 AIRFOIL (m24-il)
Reynolds number: 200,000
Max Cl/Cd: 67.91 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m24-il-200000.txt
Download as CSV file: xf-m24-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2225   0.10379   0.10003  -0.0161   0.7056   0.0409
  -8.750  -0.2297   0.10117   0.09739  -0.0196   0.7025   0.0410
  -8.500  -0.3016   0.10524   0.10134  -0.0049   0.7116   0.0402
  -8.250  -0.3059   0.10292   0.09903  -0.0119   0.7069   0.0408
  -8.000  -0.3110   0.10078   0.09682  -0.0172   0.7029   0.0410
  -7.750  -0.3044   0.09649   0.09250  -0.0187   0.6986   0.0413
  -7.500  -0.2912   0.09202   0.08805  -0.0162   0.6927   0.0417
  -7.250  -0.2811   0.08873   0.08472  -0.0157   0.6879   0.0424
  -7.000  -0.2721   0.08584   0.08176  -0.0164   0.6840   0.0432
  -6.750  -0.2614   0.08287   0.07879  -0.0182   0.6787   0.0444
  -6.500  -0.2502   0.07988   0.07575  -0.0203   0.6739   0.0458
  -6.250  -0.2366   0.07700   0.07275  -0.0232   0.6699   0.0476
  -6.000  -0.2113   0.07572   0.07110  -0.0308   0.6663   0.0490
  -5.750  -0.2032   0.07046   0.06594  -0.0299   0.6611   0.0496
  -5.500  -0.1906   0.06719   0.06266  -0.0293   0.6564   0.0502
  -5.250  -0.1759   0.06446   0.05985  -0.0291   0.6526   0.0511
  -5.000  -0.1584   0.06192   0.05723  -0.0297   0.6481   0.0525
  -4.750  -0.1382   0.05944   0.05467  -0.0308   0.6430   0.0549
  -4.500  -0.1045   0.05771   0.05247  -0.0338   0.6389   0.0588
  -4.250  -0.0915   0.05406   0.04880  -0.0332   0.6354   0.0595
  -4.000  -0.0741   0.05152   0.04626  -0.0331   0.6307   0.0606
  -3.750  -0.0540   0.04935   0.04404  -0.0331   0.6257   0.0622
  -3.500  -0.0317   0.04734   0.04188  -0.0331   0.6215   0.0649
  -3.250   0.0022   0.04626   0.04021  -0.0334   0.6183   0.0702
  -3.000   0.0196   0.04302   0.03707  -0.0335   0.6134   0.0713
  -2.750   0.0401   0.04098   0.03502  -0.0332   0.6086   0.0729
  -2.500   0.0628   0.03938   0.03329  -0.0329   0.6046   0.0763
  -2.250   0.0936   0.03839   0.03176  -0.0323   0.6014   0.0838
  -2.000   0.1148   0.03597   0.02944  -0.0325   0.5961   0.0854
  -1.750   0.1380   0.03439   0.02781  -0.0322   0.5915   0.0880
  -1.500   0.1642   0.03323   0.02644  -0.0318   0.5878   0.0937
  -1.250   0.1910   0.03174   0.02460  -0.0312   0.5843   0.0999
  -1.000   0.2155   0.03028   0.02318  -0.0313   0.5790   0.1030
  -0.750   0.2449   0.02987   0.02240  -0.0307   0.5746   0.1144
  -0.500   0.2687   0.02795   0.02045  -0.0305   0.5711   0.1173
  -0.250   0.2963   0.02746   0.01970  -0.0301   0.5673   0.1309
   0.000   0.3216   0.02605   0.01839  -0.0303   0.5620   0.1364
   0.250   0.3487   0.02517   0.01734  -0.0300   0.5578   0.1497
   0.500   0.3909   0.02081   0.01186  -0.0283   0.5550   0.0669
   0.750   0.4205   0.01996   0.01082  -0.0283   0.5515   0.0659
   1.000   0.4499   0.01933   0.01014  -0.0285   0.5462   0.0661
   1.250   0.4786   0.01890   0.00962  -0.0285   0.5419   0.0682
   1.500   0.5067   0.01840   0.00901  -0.0284   0.5384   0.0706
   1.750   0.5335   0.01801   0.00867  -0.0282   0.5344   0.0731
   2.000   0.5599   0.01781   0.00856  -0.0280   0.5295   0.0770
   2.250   0.5863   0.01761   0.00832  -0.0277   0.5255   0.0828
   2.500   0.6118   0.01732   0.00803  -0.0271   0.5223   0.0982
   2.750   0.6337   0.01693   0.00801  -0.0260   0.5182   0.2066
   3.000   0.8095   0.01616   0.00875  -0.0566   0.5094   1.0000
   3.250   0.8353   0.01625   0.00870  -0.0563   0.5063   1.0000
   3.500   0.8610   0.01648   0.00892  -0.0562   0.5021   1.0000
   3.750   0.8866   0.01667   0.00912  -0.0561   0.4972   1.0000
   4.000   0.9120   0.01677   0.00915  -0.0558   0.4933   1.0000
   4.250   0.9376   0.01688   0.00915  -0.0555   0.4901   1.0000
   4.500   0.9626   0.01717   0.00950  -0.0554   0.4858   1.0000
   4.750   0.9875   0.01742   0.00979  -0.0552   0.4813   1.0000
   5.000   1.0126   0.01758   0.00992  -0.0549   0.4777   1.0000
   5.250   1.0379   0.01772   0.00997  -0.0546   0.4747   1.0000
   5.500   1.0621   0.01806   0.01037  -0.0544   0.4705   1.0000
   5.750   1.0860   0.01835   0.01074  -0.0541   0.4659   1.0000
   6.000   1.1105   0.01855   0.01093  -0.0538   0.4623   1.0000
   6.250   1.1355   0.01873   0.01106  -0.0534   0.4594   1.0000
   6.500   1.1593   0.01911   0.01148  -0.0531   0.4560   1.0000
   6.750   1.1817   0.01955   0.01206  -0.0527   0.4516   1.0000
   7.000   1.2051   0.01983   0.01240  -0.0523   0.4478   1.0000
   7.250   1.2297   0.02000   0.01254  -0.0519   0.4447   1.0000
   7.500   1.2546   0.02028   0.01278  -0.0515   0.4419   1.0000
   7.750   1.2742   0.02090   0.01361  -0.0509   0.4376   1.0000
   8.000   1.2959   0.02129   0.01412  -0.0503   0.4336   1.0000
   8.250   1.3205   0.02126   0.01405  -0.0498   0.4293   1.0000
   8.500   1.3426   0.02142   0.01424  -0.0491   0.4240   1.0000
   8.750   1.3626   0.02151   0.01443  -0.0481   0.4171   1.0000
   9.000   1.3884   0.02132   0.01414  -0.0476   0.4120   1.0000
   9.250   1.4051   0.02175   0.01478  -0.0464   0.4059   1.0000
   9.500   1.4265   0.02172   0.01478  -0.0455   0.3995   1.0000
   9.750   1.4452   0.02179   0.01489  -0.0443   0.3919   1.0000
  10.000   1.4633   0.02177   0.01494  -0.0429   0.3837   1.0000
  10.250   1.4778   0.02198   0.01524  -0.0412   0.3748   1.0000
  10.500   1.4948   0.02201   0.01524  -0.0397   0.3658   1.0000
  10.750   1.5021   0.02250   0.01592  -0.0370   0.3564   1.0000
  11.000   1.5082   0.02292   0.01640  -0.0341   0.3450   1.0000
  11.250   1.5093   0.02351   0.01701  -0.0306   0.3333   1.0000
  11.500   1.4983   0.02446   0.01802  -0.0256   0.3229   1.0000
  11.750   1.4858   0.02591   0.01951  -0.0215   0.3096   1.0000
  12.000   1.4753   0.02785   0.02146  -0.0186   0.2935   1.0000
  12.250   1.4614   0.03053   0.02411  -0.0163   0.2716   1.0000
  12.500   1.4429   0.03400   0.02748  -0.0145   0.2450   1.0000
  12.750   1.4200   0.03818   0.03153  -0.0129   0.2153   1.0000
  13.000   1.3940   0.04293   0.03614  -0.0117   0.1884   1.0000
  13.250   1.3676   0.04795   0.04105  -0.0108   0.1656   1.0000
  13.500   1.3412   0.05336   0.04635  -0.0103   0.1411   1.0000
  13.750   1.3130   0.05927   0.05214  -0.0101   0.1119   1.0000
  14.000   1.2860   0.06531   0.05805  -0.0102   0.0895   1.0000
  14.250   1.2632   0.07103   0.06369  -0.0105   0.0724   1.0000
  14.500   1.2442   0.07646   0.06906  -0.0108   0.0565   1.0000
  14.750   1.2299   0.08144   0.07402  -0.0113   0.0483   1.0000
  15.000   1.2196   0.08597   0.07859  -0.0118   0.0440   1.0000
  15.250   1.2107   0.09041   0.08307  -0.0123   0.0412   1.0000
  15.500   1.2009   0.09505   0.08777  -0.0130   0.0392   1.0000
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