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NACA M26 AIRFOIL (m26-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M26 AIRFOIL (m26-il)
Reynolds number: 200,000
Max Cl/Cd: 78.26 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m26-il-200000-n5.txt
Download as CSV file: xf-m26-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M26 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3404   0.13996   0.13547   0.0200   0.5806   0.0147
 -10.250  -0.3336   0.13729   0.13277   0.0181   0.5784   0.0148
 -10.000  -0.3267   0.13443   0.12989   0.0163   0.5764   0.0148
  -9.750  -0.3184   0.12965   0.12511   0.0161   0.5740   0.0150
  -9.500  -0.3109   0.12616   0.12162   0.0152   0.5716   0.0152
  -9.250  -0.3034   0.12305   0.11849   0.0140   0.5695   0.0154
  -9.000  -0.2957   0.12003   0.11546   0.0126   0.5675   0.0156
  -8.750  -0.2880   0.11706   0.11245   0.0112   0.5656   0.0159
  -8.500  -0.2801   0.11410   0.10947   0.0097   0.5639   0.0163
  -8.250  -0.2722   0.11116   0.10650   0.0081   0.5624   0.0166
  -8.000  -0.2640   0.10821   0.10354   0.0064   0.5607   0.0171
  -7.750  -0.2557   0.10526   0.10061   0.0045   0.5590   0.0176
  -7.500  -0.2471   0.10237   0.09772   0.0023   0.5572   0.0182
  -7.250  -0.2398   0.09980   0.09516  -0.0001   0.5555   0.0185
  -7.000  -0.2265   0.09746   0.09280  -0.0044   0.5538   0.0188
  -6.750  -0.2105   0.09509   0.09039  -0.0092   0.5521   0.0190
  -6.500  -0.1939   0.09216   0.08740  -0.0130   0.5504   0.0190
  -6.250  -0.1763   0.08900   0.08418  -0.0165   0.5488   0.0190
  -6.000  -0.1572   0.08579   0.08089  -0.0199   0.5474   0.0191
  -5.750  -0.1457   0.08117   0.07627  -0.0203   0.5460   0.0192
  -5.500  -0.1342   0.07733   0.07242  -0.0205   0.5444   0.0196
  -5.250  -0.1168   0.07429   0.06935  -0.0223   0.5428   0.0202
  -5.000  -0.0963   0.07155   0.06656  -0.0247   0.5412   0.0217
  -4.750  -0.0610   0.06981   0.06468  -0.0299   0.5396   0.0243
  -4.500  -0.0300   0.06740   0.06214  -0.0340   0.5381   0.0246
  -4.250  -0.0005   0.06472   0.05932  -0.0373   0.5367   0.0247
  -4.000   0.0296   0.06210   0.05654  -0.0401   0.5353   0.0248
  -3.750   0.0419   0.05710   0.05152  -0.0403   0.5340   0.0254
  -3.500   0.0595   0.05402   0.04837  -0.0407   0.5327   0.0261
  -3.250   0.0830   0.05159   0.04584  -0.0420   0.5313   0.0272
  -3.000   0.1099   0.04935   0.04352  -0.0436   0.5296   0.0290
  -2.750   0.1565   0.04939   0.04329  -0.0468   0.5280   0.0333
  -2.500   0.1872   0.04744   0.04116  -0.0481   0.5265   0.0335
  -2.250   0.2159   0.04531   0.03889  -0.0491   0.5251   0.0336
  -2.000   0.2372   0.04123   0.03471  -0.0499   0.5238   0.0344
  -1.750   0.2564   0.03884   0.03231  -0.0502   0.5224   0.0360
  -1.500   0.2822   0.03721   0.03057  -0.0508   0.5209   0.0381
  -1.250   0.3105   0.03568   0.02887  -0.0514   0.5194   0.0402
  -1.000   0.3489   0.03546   0.02833  -0.0521   0.5180   0.0452
  -0.750   0.3804   0.03446   0.02708  -0.0524   0.5168   0.0456
  -0.250   0.4273   0.03017   0.02273  -0.0534   0.5142   0.0492
   0.000   0.4555   0.02909   0.02155  -0.0538   0.5125   0.0516
   0.500   0.5195   0.02763   0.01962  -0.0541   0.5089   0.0584
   0.750   0.5451   0.02607   0.01801  -0.0544   0.5074   0.0596
   1.000   0.5727   0.02504   0.01689  -0.0546   0.5059   0.0605
   1.500   0.6325   0.02242   0.01374  -0.0542   0.5029   0.0436
   1.750   0.6609   0.02158   0.01270  -0.0542   0.5015   0.0430
   2.000   0.6898   0.02077   0.01181  -0.0544   0.4992   0.0415
   2.250   0.7187   0.02000   0.01093  -0.0545   0.4966   0.0403
   2.500   0.7475   0.01930   0.01010  -0.0546   0.4943   0.0394
   2.750   0.7758   0.01874   0.00942  -0.0547   0.4921   0.0389
   3.000   0.8035   0.01832   0.00891  -0.0547   0.4902   0.0390
   3.250   0.8307   0.01800   0.00853  -0.0547   0.4885   0.0394
   3.500   0.8575   0.01777   0.00824  -0.0546   0.4870   0.0403
   3.750   0.8841   0.01766   0.00816  -0.0546   0.4850   0.0415
   4.000   0.9108   0.01767   0.00825  -0.0548   0.4824   0.0442
   4.250   0.9369   0.01763   0.00829  -0.0548   0.4799   0.0469
   4.500   0.9632   0.01762   0.00829  -0.0548   0.4777   0.0482
   4.750   0.9901   0.01764   0.00830  -0.0548   0.4755   0.0502
   5.000   1.0173   0.01768   0.00833  -0.0549   0.4735   0.0538
   5.250   1.0446   0.01774   0.00839  -0.0550   0.4718   0.0680
   5.500   1.0713   0.01791   0.00877  -0.0554   0.4692   0.1380
   6.000   1.1781   0.01685   0.00913  -0.0673   0.4585   1.0000
   6.250   1.2028   0.01675   0.00910  -0.0671   0.4493   1.0000
   6.500   1.2280   0.01655   0.00886  -0.0667   0.4420   1.0000
   6.750   1.2524   0.01658   0.00900  -0.0665   0.4306   1.0000
   7.000   1.2767   0.01660   0.00909  -0.0663   0.4172   1.0000
   7.250   1.2991   0.01660   0.00889  -0.0658   0.3740   1.0000
   7.500   1.3121   0.01784   0.00967  -0.0649   0.3106   1.0000
   7.750   1.3089   0.02061   0.01191  -0.0629   0.2293   1.0000
   8.000   1.2836   0.02458   0.01540  -0.0595   0.1478   1.0000
   8.250   1.2589   0.02810   0.01880  -0.0561   0.1094   1.0000
   8.500   1.2355   0.03242   0.02296  -0.0541   0.0725   1.0000
   8.750   1.2188   0.03648   0.02690  -0.0529   0.0290   1.0000
   9.000   1.2169   0.03919   0.02965  -0.0520   0.0235   1.0000
   9.250   1.2194   0.04149   0.03204  -0.0513   0.0212   1.0000
   9.500   1.2222   0.04377   0.03445  -0.0507   0.0202   1.0000
   9.750   1.2241   0.04618   0.03698  -0.0501   0.0193   1.0000
  10.000   1.2249   0.04871   0.03963  -0.0494   0.0183   1.0000
  10.250   1.2245   0.05140   0.04244  -0.0488   0.0172   1.0000
  10.500   1.2227   0.05427   0.04545  -0.0483   0.0161   1.0000
  10.750   1.2199   0.05740   0.04871  -0.0479   0.0153   1.0000
  11.000   1.2166   0.06069   0.05213  -0.0475   0.0148   1.0000
  11.250   1.2116   0.06424   0.05583  -0.0473   0.0143   1.0000
  11.500   1.2049   0.06811   0.05984  -0.0471   0.0140   1.0000
  11.750   1.1965   0.07226   0.06412  -0.0470   0.0137   1.0000
  12.000   1.1925   0.07589   0.06785  -0.0470   0.0135   1.0000
  12.250   1.1903   0.07934   0.07139  -0.0469   0.0133   1.0000
  12.500   1.1898   0.08256   0.07469  -0.0469   0.0130   1.0000
  12.750   1.1898   0.08572   0.07792  -0.0469   0.0125   1.0000
  13.000   1.1908   0.08874   0.08100  -0.0468   0.0119   1.0000
  13.250   1.1920   0.09170   0.08405  -0.0467   0.0113   1.0000
  13.500   1.1939   0.09447   0.08687  -0.0465   0.0110   1.0000
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