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NACA M26 AIRFOIL (m26-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M26 AIRFOIL (m26-il)
Reynolds number: 1,000,000
Max Cl/Cd: 141.1 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m26-il-1000000.txt
Download as CSV file: xf-m26-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3003   0.10594   0.10290   0.0128   0.5196   0.0099
  -7.750  -0.2935   0.10293   0.09990   0.0104   0.5184   0.0099
  -7.500  -0.2882   0.10003   0.09701   0.0080   0.5172   0.0099
  -7.250  -0.2772   0.09673   0.09370   0.0050   0.5161   0.0099
  -7.000  -0.2680   0.09260   0.08956   0.0028   0.5149   0.0100
  -6.750  -0.2563   0.08949   0.08644   0.0010   0.5137   0.0102
  -6.500  -0.2420   0.08665   0.08357  -0.0014   0.5125   0.0104
  -6.250  -0.2259   0.08383   0.08072  -0.0040   0.5111   0.0107
  -6.000  -0.2084   0.08093   0.07778  -0.0068   0.5095   0.0112
  -5.750  -0.1871   0.07760   0.07441  -0.0104   0.5084   0.0126
  -5.500  -0.1611   0.07416   0.07093  -0.0151   0.5078   0.0128
  -5.250  -0.1365   0.07073   0.06746  -0.0189   0.5070   0.0129
  -5.000  -0.1115   0.06735   0.06402  -0.0223   0.5061   0.0129
  -4.750  -0.0983   0.06355   0.06022  -0.0230   0.5051   0.0132
  -4.500  -0.0764   0.06110   0.05772  -0.0249   0.5039   0.0136
  -4.250  -0.0522   0.05863   0.05521  -0.0270   0.5027   0.0142
  -4.000  -0.0234   0.05593   0.05244  -0.0295   0.5015   0.0160
  -3.750   0.0128   0.05311   0.04949  -0.0330   0.5004   0.0163
  -3.500   0.0439   0.05018   0.04646  -0.0354   0.4994   0.0164
  -3.250   0.0724   0.02814   0.02463  -0.0363   0.4967   0.0168
  -3.000   0.0943   0.02612   0.02256  -0.0371   0.4954   0.0172
  -2.750   0.1186   0.02423   0.02059  -0.0382   0.4937   0.0179
  -2.500   0.1451   0.02221   0.01850  -0.0392   0.4931   0.0194
  -2.250   0.1816   0.02059   0.01673  -0.0408   0.4923   0.0204
  -2.000   0.2096   0.01852   0.01455  -0.0414   0.4914   0.0205
  -1.750   0.2368   0.01657   0.01249  -0.0419   0.4905   0.0205
  -1.500   0.2585   0.01372   0.00954  -0.0424   0.4896   0.0210
  -1.250   0.2826   0.01252   0.00829  -0.0427   0.4885   0.0214
  -1.000   0.3081   0.01151   0.00722  -0.0431   0.4873   0.0219
  -0.750   0.3349   0.01054   0.00616  -0.0434   0.4861   0.0229
  -0.500   0.3674   0.00994   0.00541  -0.0434   0.4848   0.0255
  -0.250   0.3967   0.00913   0.00447  -0.0435   0.4833   0.0258
   0.000   0.4246   0.00829   0.00349  -0.0435   0.4815   0.0258
   0.250   0.4525   0.00754   0.00259  -0.0435   0.4793   0.0259
   0.750   0.5205   0.01806   0.01254  -0.0446   0.4783   0.0269
   1.000   0.5483   0.01731   0.01174  -0.0449   0.4773   0.0276
   1.250   0.5766   0.01659   0.01096  -0.0451   0.4762   0.0287
   1.500   0.6060   0.01583   0.01010  -0.0451   0.4749   0.0319
   1.750   0.6357   0.01545   0.00962  -0.0450   0.4735   0.0331
   2.000   0.6637   0.01330   0.00720  -0.0448   0.4723   0.0347
   2.250   0.6919   0.01288   0.00676  -0.0451   0.4709   0.0358
   2.500   0.7202   0.01256   0.00641  -0.0454   0.4694   0.0375
   2.750   0.7487   0.01217   0.00595  -0.0456   0.4679   0.0399
   3.000   0.7775   0.01212   0.00579  -0.0457   0.4663   0.0436
   3.250   0.8051   0.01148   0.00512  -0.0460   0.4643   0.0475
   3.500   0.8336   0.01123   0.00488  -0.0462   0.4633   0.0509
   3.750   0.8619   0.01040   0.00391  -0.0458   0.4620   0.0333
   4.000   0.8893   0.01010   0.00362  -0.0458   0.4605   0.0335
   4.250   0.9168   0.00992   0.00344  -0.0459   0.4589   0.0337
   4.500   0.9444   0.00975   0.00328  -0.0461   0.4572   0.0347
   4.750   0.9725   0.00962   0.00316  -0.0463   0.4541   0.0352
   5.000   1.0004   0.00960   0.00310  -0.0466   0.4494   0.0358
   5.250   1.0290   0.00946   0.00303  -0.0469   0.4451   0.0375
   5.500   1.0574   0.00938   0.00294  -0.0473   0.4382   0.0416
   5.750   1.0855   0.00936   0.00301  -0.0476   0.4333   0.0911
   6.000   1.1074   0.00839   0.00316  -0.0471   0.4267   0.7911
   6.250   1.1500   0.00815   0.00339  -0.0504   0.4077   0.9915
   6.500   1.2112   0.01015   0.00463  -0.0602   0.2804   0.9980
   6.750   1.2340   0.01523   0.00835  -0.0652   0.0203   1.0000
   7.000   1.2551   0.01573   0.00887  -0.0646   0.0172   1.0000
   7.250   1.2749   0.01632   0.00952  -0.0639   0.0149   1.0000
   7.500   1.2941   0.01685   0.01009  -0.0632   0.0143   1.0000
   7.750   1.3117   0.01747   0.01075  -0.0622   0.0136   1.0000
   8.000   1.3268   0.01821   0.01154  -0.0610   0.0129   1.0000
   8.250   1.3388   0.01908   0.01247  -0.0594   0.0123   1.0000
   8.500   1.3454   0.02028   0.01374  -0.0577   0.0116   1.0000
   8.750   1.3359   0.02220   0.01574  -0.0544   0.0112   1.0000
   9.000   1.3268   0.02464   0.01827  -0.0519   0.0108   1.0000
   9.250   1.3155   0.02817   0.02195  -0.0506   0.0104   1.0000
   9.500   1.3180   0.03050   0.02435  -0.0501   0.0103   1.0000
   9.750   1.3220   0.03273   0.02663  -0.0496   0.0101   1.0000
  10.000   1.3235   0.03522   0.02919  -0.0491   0.0099   1.0000
  10.250   1.3230   0.03793   0.03197  -0.0486   0.0097   1.0000
  10.500   1.3218   0.04073   0.03483  -0.0480   0.0095   1.0000
  10.750   1.3192   0.04364   0.03783  -0.0475   0.0093   1.0000
  11.000   1.3160   0.04665   0.04091  -0.0469   0.0091   1.0000
  11.250   1.3131   0.04966   0.04398  -0.0464   0.0089   1.0000
  11.500   1.3106   0.05274   0.04713  -0.0461   0.0087   1.0000
  11.750   1.3090   0.05574   0.05019  -0.0457   0.0085   1.0000
  12.000   1.3077   0.05877   0.05327  -0.0455   0.0083   1.0000
  12.250   1.3081   0.06161   0.05615  -0.0452   0.0080   1.0000
  12.500   1.3071   0.06464   0.05923  -0.0451   0.0078   1.0000
  12.750   1.3047   0.06780   0.06242  -0.0448   0.0075   1.0000
  13.000   1.2958   0.07158   0.06624  -0.0442   0.0073   1.0000
  13.250   1.2935   0.07398   0.06867  -0.0428   0.0071   1.0000
  13.500   1.2996   0.07628   0.07102  -0.0428   0.0070   1.0000
  13.750   1.3062   0.07838   0.07317  -0.0425   0.0069   1.0000
  14.000   1.3134   0.08024   0.07508  -0.0420   0.0067   1.0000
  14.250   1.3213   0.08188   0.07676  -0.0414   0.0066   1.0000
  14.500   1.3304   0.08328   0.07820  -0.0405   0.0065   1.0000
  14.750   1.3409   0.08443   0.07938  -0.0395   0.0063   1.0000
  15.000   1.3532   0.08522   0.08023  -0.0383   0.0061   1.0000
  15.250   1.3661   0.08590   0.08096  -0.0368   0.0059   1.0000
  15.500   1.3807   0.08622   0.08134  -0.0349   0.0057   1.0000
  15.750   1.3954   0.08654   0.08174  -0.0328   0.0057   1.0000
  16.000   1.4030   0.08834   0.08360  -0.0321   0.0055   1.0000
  16.250   1.4065   0.09091   0.08623  -0.0325   0.0053   1.0000
  16.500   1.4086   0.09379   0.08914  -0.0334   0.0052   1.0000
  16.750   1.4105   0.09662   0.09202  -0.0339   0.0050   1.0000
  17.000   1.4174   0.09824   0.09369  -0.0329   0.0049   1.0000
  17.250   1.4236   0.10021   0.09580  -0.0317   0.0049   1.0000
  19.000   1.3368   0.13995   0.13713  -0.0389   0.0063   1.0000
  19.250   1.3240   0.14633   0.14366  -0.0422   0.0062   1.0000
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