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NACA M8 AIRFOIL (m8-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M8 AIRFOIL (m8-il)
Reynolds number: 1,000,000
Max Cl/Cd: 99.15 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m8-il-1000000-n5.txt
Download as CSV file: xf-m8-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M8 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3068   0.13114   0.12815   0.0031   0.6104   0.0083
  -9.250  -0.4582   0.03866   0.03501  -0.0618   0.5620   0.0201
  -9.000  -0.4386   0.03365   0.02975  -0.0661   0.5546   0.0207
  -8.750  -0.4156   0.03044   0.02633  -0.0685   0.5479   0.0211
  -8.500  -0.3912   0.02803   0.02373  -0.0700   0.5406   0.0216
  -8.250  -0.3663   0.02600   0.02149  -0.0711   0.5329   0.0220
  -8.000  -0.3408   0.02422   0.01956  -0.0719   0.5272   0.0224
  -7.750  -0.3147   0.02281   0.01804  -0.0724   0.5219   0.0229
  -7.500  -0.2884   0.02152   0.01663  -0.0727   0.5170   0.0233
  -7.000  -0.2348   0.01944   0.01432  -0.0730   0.5090   0.0242
  -6.750  -0.2077   0.01852   0.01329  -0.0730   0.5051   0.0248
  -6.500  -0.1806   0.01763   0.01228  -0.0730   0.5010   0.0252
  -6.250  -0.1533   0.01688   0.01140  -0.0729   0.4967   0.0256
  -6.000  -0.1258   0.01620   0.01061  -0.0728   0.4927   0.0260
  -5.750  -0.0982   0.01556   0.00987  -0.0725   0.4895   0.0263
  -5.500  -0.0705   0.01498   0.00921  -0.0723   0.4856   0.0269
  -5.250  -0.0427   0.01445   0.00861  -0.0721   0.4812   0.0275
  -5.000  -0.0149   0.01398   0.00806  -0.0718   0.4767   0.0280
  -4.750   0.0132   0.01356   0.00757  -0.0716   0.4729   0.0284
  -4.500   0.0413   0.01317   0.00712  -0.0713   0.4688   0.0289
  -4.250   0.0695   0.01284   0.00672  -0.0710   0.4639   0.0294
  -4.000   0.0977   0.01255   0.00635  -0.0707   0.4585   0.0298
  -3.750   0.1260   0.01228   0.00602  -0.0704   0.4538   0.0303
  -3.500   0.1544   0.01204   0.00571  -0.0701   0.4464   0.0307
  -3.250   0.1826   0.01184   0.00542  -0.0698   0.4371   0.0313
  -3.000   0.2109   0.01163   0.00514  -0.0695   0.4253   0.0320
  -2.750   0.2391   0.01145   0.00489  -0.0692   0.4132   0.0327
  -2.500   0.2673   0.01132   0.00467  -0.0689   0.3995   0.0335
  -2.250   0.2955   0.01122   0.00448  -0.0687   0.3863   0.0342
  -2.000   0.3238   0.01112   0.00431  -0.0684   0.3761   0.0350
  -1.750   0.3521   0.01104   0.00415  -0.0681   0.3680   0.0358
  -1.500   0.3804   0.01091   0.00398  -0.0678   0.3610   0.0372
  -1.000   0.4370   0.01073   0.00372  -0.0673   0.3479   0.0410
  -0.750   0.4653   0.01064   0.00360  -0.0671   0.3428   0.0433
  -0.500   0.4935   0.01055   0.00349  -0.0669   0.3386   0.0469
   0.000   0.5501   0.01039   0.00330  -0.0664   0.3309   0.0559
   0.250   0.5783   0.01029   0.00320  -0.0662   0.3278   0.0614
   0.500   0.6065   0.01024   0.00315  -0.0660   0.3247   0.0668
   0.750   0.6346   0.01016   0.00307  -0.0657   0.3210   0.0735
   1.000   0.6625   0.01016   0.00304  -0.0655   0.3170   0.0783
   1.250   0.6904   0.01008   0.00297  -0.0653   0.3139   0.0852
   1.500   0.7185   0.01003   0.00293  -0.0650   0.3120   0.0919
   1.750   0.7460   0.00989   0.00282  -0.0648   0.3093   0.1064
   2.000   0.7754   0.01046   0.00354  -0.0646   0.3054   0.1600
   2.250   0.8035   0.01064   0.00369  -0.0644   0.3019   0.1645
   2.500   0.8314   0.01078   0.00381  -0.0642   0.2981   0.1670
   2.750   0.8589   0.01068   0.00364  -0.0640   0.2954   0.1698
   3.000   0.8872   0.01087   0.00387  -0.0638   0.2926   0.1705
   3.250   0.9151   0.01109   0.00409  -0.0636   0.2877   0.1712
   3.500   0.9426   0.01134   0.00432  -0.0634   0.2808   0.1722
   3.750   0.9701   0.01145   0.00442  -0.0632   0.2746   0.1728
   4.000   0.9970   0.01162   0.00453  -0.0630   0.2629   0.1735
   4.250   1.0233   0.01187   0.00468  -0.0627   0.2447   0.1744
   4.500   1.0490   0.01212   0.00484  -0.0624   0.2293   0.1749
   4.750   1.0750   0.01236   0.00500  -0.0621   0.2200   0.1764
   5.000   1.1014   0.01254   0.00514  -0.0618   0.2142   0.1775
   5.250   1.1277   0.01265   0.00524  -0.0615   0.2102   0.1775
   5.500   1.1537   0.01280   0.00537  -0.0613   0.2062   0.1776
   5.750   1.1795   0.01296   0.00552  -0.0610   0.2021   0.1777
   6.000   1.2056   0.01306   0.00563  -0.0607   0.1997   0.1778
   6.250   1.2317   0.01316   0.00574  -0.0604   0.1979   0.1779
   6.500   1.2575   0.01328   0.00588  -0.0601   0.1958   0.1781
   6.750   1.2830   0.01342   0.00604  -0.0598   0.1936   0.1782
   7.000   1.3082   0.01359   0.00622  -0.0594   0.1913   0.1783
   7.250   1.3330   0.01379   0.00643  -0.0590   0.1889   0.1784
   7.500   1.3574   0.01401   0.00667  -0.0586   0.1859   0.1785
   7.750   1.3819   0.01421   0.00689  -0.0581   0.1839   0.1786
   8.000   1.4067   0.01436   0.00708  -0.0577   0.1829   0.1788
   8.250   1.4312   0.01453   0.00729  -0.0573   0.1818   0.1789
   8.500   1.4552   0.01472   0.00752  -0.0569   0.1806   0.1790
   8.750   1.4789   0.01492   0.00776  -0.0564   0.1792   0.1792
   9.000   1.5021   0.01515   0.00803  -0.0558   0.1778   0.1794
   9.250   1.5248   0.01540   0.00832  -0.0552   0.1764   0.1796
   9.500   1.5468   0.01568   0.00862  -0.0545   0.1750   0.1798
   9.750   1.5680   0.01598   0.00895  -0.0537   0.1735   0.1799
  10.000   1.5878   0.01634   0.00934  -0.0528   0.1708   0.1802
  10.250   1.6069   0.01671   0.00974  -0.0518   0.1680   0.1804
  10.500   1.6272   0.01697   0.01006  -0.0509   0.1668   0.1807
  10.750   1.6460   0.01729   0.01042  -0.0498   0.1650   0.1809
  11.000   1.6617   0.01765   0.01083  -0.0483   0.1631   0.1812
  11.250   1.6711   0.01812   0.01132  -0.0458   0.1606   0.1814
  11.500   1.6773   0.01885   0.01207  -0.0433   0.1574   0.1817
  11.750   1.6837   0.01973   0.01298  -0.0412   0.1542   0.1819
  12.000   1.6949   0.02048   0.01378  -0.0397   0.1528   0.1822
  12.250   1.7062   0.02129   0.01465  -0.0385   0.1511   0.1827
  12.500   1.7158   0.02230   0.01570  -0.0373   0.1481   0.1833
  12.750   1.7245   0.02345   0.01689  -0.0363   0.1458   0.1835
  13.000   1.7308   0.02484   0.01831  -0.0352   0.1431   0.1839
  13.250   1.7359   0.02637   0.01988  -0.0342   0.1396   0.1841
  13.500   1.7430   0.02779   0.02134  -0.0334   0.1361   0.1846
  13.750   1.7480   0.02940   0.02300  -0.0326   0.1329   0.1848
  14.000   1.7442   0.03180   0.02539  -0.0316   0.1257   0.1849
  14.250   1.7386   0.03446   0.02803  -0.0307   0.1173   0.1852
  14.500   1.7176   0.03868   0.03218  -0.0299   0.1027   0.1851
  14.750   1.6809   0.04476   0.03819  -0.0295   0.0840   0.1851
  15.000   1.6633   0.04930   0.04274  -0.0296   0.0755   0.1853
  15.250   1.6441   0.05426   0.04771  -0.0301   0.0669   0.1854
  15.500   1.6197   0.06005   0.05351  -0.0309   0.0572   0.1854
  15.750   1.6051   0.06489   0.05839  -0.0319   0.0519   0.1855
  16.000   1.5958   0.06919   0.06276  -0.0328   0.0484   0.1855
  16.250   1.5736   0.07541   0.06900  -0.0344   0.0407   0.1855
  16.500   1.5580   0.08093   0.07457  -0.0360   0.0355   0.1855
  16.750   1.5245   0.08940   0.08307  -0.0389   0.0236   0.1854
  17.000   1.5056   0.09587   0.08961  -0.0412   0.0193   0.1857
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