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NACA M8 AIRFOIL (m8-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M8 AIRFOIL (m8-il)
Reynolds number: 1,000,000
Max Cl/Cd: 96.61 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m8-il-1000000.txt
Download as CSV file: xf-m8-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1914   0.08913   0.08617  -0.0137   0.5765   0.0220
  -8.000  -0.1796   0.08759   0.08462  -0.0140   0.5690   0.0224
  -7.750  -0.3372   0.02845   0.02461  -0.0642   0.5917   0.0258
  -7.500  -0.3110   0.02716   0.02323  -0.0648   0.5826   0.0262
  -7.250  -0.2846   0.02578   0.02175  -0.0655   0.5747   0.0267
  -7.000  -0.2589   0.02351   0.01926  -0.0667   0.5673   0.0273
  -6.750  -0.2332   0.02147   0.01700  -0.0675   0.5604   0.0279
  -6.500  -0.2073   0.01954   0.01484  -0.0680   0.5546   0.0285
  -6.250  -0.1808   0.01802   0.01311  -0.0683   0.5485   0.0290
  -6.000  -0.1534   0.01692   0.01183  -0.0684   0.5426   0.0293
  -5.750  -0.1284   0.01548   0.01022  -0.0681   0.5382   0.0303
  -5.500  -0.1010   0.01492   0.00958  -0.0678   0.5328   0.0308
  -5.250  -0.0735   0.01439   0.00896  -0.0675   0.5272   0.0314
  -5.000  -0.0458   0.01388   0.00836  -0.0671   0.5226   0.0320
  -4.750  -0.0180   0.01340   0.00780  -0.0668   0.5180   0.0326
  -4.500   0.0099   0.01302   0.00732  -0.0664   0.5133   0.0332
  -4.250   0.0380   0.01271   0.00691  -0.0661   0.5082   0.0338
  -4.000   0.0659   0.01229   0.00641  -0.0657   0.5043   0.0343
  -3.750   0.0935   0.01185   0.00590  -0.0652   0.5001   0.0352
  -3.500   0.1216   0.01161   0.00561  -0.0649   0.4949   0.0360
  -3.250   0.1498   0.01141   0.00534  -0.0645   0.4886   0.0368
  -3.000   0.1783   0.01117   0.00507  -0.0642   0.4833   0.0376
  -2.750   0.2067   0.01098   0.00481  -0.0639   0.4770   0.0386
  -2.500   0.2351   0.01084   0.00459  -0.0635   0.4708   0.0393
  -2.250   0.2637   0.01066   0.00437  -0.0632   0.4658   0.0406
  -2.000   0.2922   0.01050   0.00418  -0.0629   0.4585   0.0419
  -1.750   0.3207   0.01038   0.00400  -0.0626   0.4507   0.0434
  -1.500   0.3492   0.01026   0.00383  -0.0623   0.4420   0.0449
  -1.250   0.3777   0.01016   0.00368  -0.0620   0.4336   0.0472
  -1.000   0.4062   0.01003   0.00353  -0.0617   0.4242   0.0501
  -0.750   0.4346   0.00996   0.00339  -0.0614   0.4140   0.0532
  -0.250   0.4910   0.00972   0.00309  -0.0610   0.3921   0.0647
   0.000   0.5191   0.00967   0.00298  -0.0607   0.3826   0.0704
   0.250   0.5472   0.00955   0.00285  -0.0605   0.3748   0.0784
   0.500   0.5751   0.00949   0.00275  -0.0602   0.3675   0.0861
   0.750   0.6032   0.00941   0.00266  -0.0599   0.3621   0.0936
   1.000   0.6304   0.00920   0.00250  -0.0596   0.3570   0.1177
   1.250   0.6603   0.01001   0.00339  -0.0595   0.3512   0.1629
   1.500   0.6892   0.01056   0.00397  -0.0592   0.3478   0.1683
   1.750   0.7176   0.01076   0.00413  -0.0589   0.3435   0.1726
   2.000   0.7459   0.01138   0.00482  -0.0587   0.3392   0.1750
   2.250   0.7739   0.01179   0.00526  -0.0584   0.3348   0.1782
   2.500   0.8023   0.01198   0.00543  -0.0582   0.3323   0.1818
   2.750   0.8301   0.01207   0.00557  -0.0580   0.3295   0.1857
   3.000   0.8579   0.01238   0.00593  -0.0578   0.3261   0.1915
   3.250   0.8850   0.01260   0.00619  -0.0577   0.3223   0.2015
   3.500   0.9139   0.01346   0.00693  -0.0574   0.3178   0.2054
   3.750   0.9419   0.01348   0.00695  -0.0572   0.3152   0.2055
   4.000   0.9681   0.01257   0.00607  -0.0571   0.3120   0.2073
   4.250   0.9954   0.01250   0.00599  -0.0570   0.3077   0.2078
   4.500   1.0223   0.01251   0.00597  -0.0568   0.3023   0.2087
   4.750   1.0496   0.01248   0.00596  -0.0566   0.2980   0.2097
   5.000   1.0770   0.01247   0.00596  -0.0564   0.2927   0.2113
   5.250   1.1038   0.01254   0.00598  -0.0562   0.2854   0.2123
   5.500   1.1309   0.01257   0.00600  -0.0561   0.2778   0.2130
   5.750   1.1573   0.01270   0.00606  -0.0558   0.2652   0.2137
   6.000   1.1830   0.01297   0.00622  -0.0555   0.2468   0.2149
   6.250   1.2084   0.01358   0.00670  -0.0551   0.2324   0.2167
   6.500   1.2333   0.01393   0.00698  -0.0548   0.2228   0.2170
   6.750   1.2589   0.01412   0.00716  -0.0545   0.2180   0.2171
   7.000   1.2833   0.01377   0.00681  -0.0542   0.2137   0.2194
   7.250   1.3077   0.01398   0.00701  -0.0538   0.2090   0.2201
   7.500   1.3326   0.01415   0.00720  -0.0534   0.2059   0.2208
   7.750   1.3580   0.01425   0.00735  -0.0531   0.2041   0.2217
   8.000   1.3828   0.01441   0.00754  -0.0527   0.2020   0.2228
   8.250   1.4071   0.01462   0.00776  -0.0523   0.1998   0.2242
   8.500   1.4308   0.01490   0.00805  -0.0518   0.1973   0.2263
   9.250   1.4994   0.01573   0.00886  -0.0499   0.1904   0.2065
   9.500   1.5233   0.01597   0.00914  -0.0494   0.1890   0.2059
   9.750   1.5465   0.01622   0.00944  -0.0489   0.1873   0.2055
  10.000   1.5679   0.01623   0.00952  -0.0481   0.1852   0.2028
  10.250   1.5886   0.01651   0.00983  -0.0473   0.1835   0.2023
  10.500   1.6078   0.01686   0.01021  -0.0462   0.1812   0.2018
  10.750   1.6247   0.01731   0.01067  -0.0449   0.1790   0.2016
  11.000   1.6373   0.01791   0.01130  -0.0431   0.1761   0.2013
  11.250   1.6563   0.01807   0.01153  -0.0420   0.1750   0.2012
  11.500   1.6705   0.01834   0.01186  -0.0401   0.1735   0.2010
  11.750   1.6822   0.01878   0.01236  -0.0381   0.1719   0.2008
  12.000   1.6924   0.01940   0.01302  -0.0363   0.1702   0.2007
  12.250   1.7020   0.02015   0.01382  -0.0346   0.1686   0.2006
  12.500   1.7106   0.02107   0.01477  -0.0331   0.1667   0.2006
  12.750   1.7158   0.02231   0.01604  -0.0316   0.1637   0.2009
  13.000   1.7209   0.02370   0.01747  -0.0303   0.1616   0.2015
  13.250   1.7358   0.02443   0.01829  -0.0296   0.1605   0.2018
  13.500   1.7487   0.02533   0.01926  -0.0290   0.1587   0.2027
  13.750   1.7589   0.02645   0.02042  -0.0282   0.1562   0.2027
  14.000   1.7652   0.02792   0.02191  -0.0274   0.1527   0.2031
  14.250   1.7663   0.02984   0.02385  -0.0264   0.1489   0.2030
  14.500   1.7742   0.03123   0.02532  -0.0258   0.1469   0.2036
  14.750   1.7816   0.03270   0.02683  -0.0252   0.1427   0.2039
  15.000   1.7796   0.03506   0.02919  -0.0246   0.1373   0.2044
  15.250   1.7789   0.03737   0.03153  -0.0240   0.1313   0.2048
  15.500   1.7715   0.04039   0.03455  -0.0236   0.1243   0.2044
  15.750   1.7566   0.04430   0.03843  -0.0235   0.1129   0.2047
  16.000   1.7388   0.04879   0.04291  -0.0236   0.1022   0.2049
  16.250   1.7107   0.05470   0.04878  -0.0243   0.0896   0.2049
  16.500   1.6769   0.06161   0.05566  -0.0255   0.0767   0.2048
  16.750   1.6571   0.06710   0.06118  -0.0268   0.0703   0.2050
  17.000   1.6324   0.07346   0.06757  -0.0284   0.0623   0.2050
  17.250   1.6138   0.07925   0.07340  -0.0301   0.0566   0.2046
  17.500   1.5918   0.08576   0.07996  -0.0323   0.0505   0.2052
  17.750   1.5668   0.09295   0.08720  -0.0349   0.0440   0.2050
  18.000   1.5441   0.10002   0.09432  -0.0376   0.0381   0.2051
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