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NACA M8 AIRFOIL (m8-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA M8 AIRFOIL (m8-il)
Reynolds number: 200,000
Max Cl/Cd: 60.24 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m8-il-200000.txt
Download as CSV file: xf-m8-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1762   0.10383   0.09982  -0.0105   0.7229   0.0491
  -8.500  -0.1699   0.10147   0.09748  -0.0121   0.7142   0.0512
  -8.250  -0.1828   0.10144   0.09745  -0.0163   0.7076   0.0522
  -8.000  -0.1722   0.09731   0.09332  -0.0168   0.7005   0.0527
  -7.750  -0.1529   0.09350   0.08946  -0.0159   0.6926   0.0534
  -7.500  -0.1413   0.09103   0.08693  -0.0158   0.6861   0.0546
  -7.250  -0.1325   0.08872   0.08465  -0.0165   0.6783   0.0559
  -7.000  -0.1271   0.08655   0.08246  -0.0172   0.6721   0.0576
  -6.750  -0.1321   0.08630   0.08219  -0.0260   0.6673   0.0602
  -6.500  -0.1194   0.08188   0.07780  -0.0250   0.6603   0.0610
  -6.250  -0.1039   0.07896   0.07484  -0.0232   0.6543   0.0620
  -6.000  -0.0895   0.07661   0.07245  -0.0237   0.6487   0.0635
  -5.750  -0.0746   0.07419   0.07004  -0.0255   0.6421   0.0656
  -5.500  -0.0488   0.07167   0.06737  -0.0394   0.6372   0.0699
  -5.250  -0.0386   0.06812   0.06379  -0.0362   0.6324   0.0707
  -5.000  -0.0230   0.06576   0.06148  -0.0344   0.6254   0.0721
  -4.750  -0.0041   0.06360   0.05927  -0.0351   0.6194   0.0745
  -4.500   0.0352   0.06027   0.05567  -0.0472   0.6151   0.0809
  -4.250   0.0488   0.05739   0.05285  -0.0454   0.6084   0.0818
  -4.000   0.0668   0.05527   0.05071  -0.0445   0.6023   0.0832
  -3.750   0.0884   0.05341   0.04874  -0.0449   0.5972   0.0864
  -3.500   0.1261   0.05005   0.04523  -0.0522   0.5906   0.0938
  -3.250   0.1450   0.04812   0.04327  -0.0511   0.5842   0.0954
  -3.000   0.1682   0.04641   0.04144  -0.0513   0.5787   0.0984
  -2.750   0.2047   0.04360   0.03847  -0.0562   0.5713   0.1069
  -2.500   0.2458   0.03251   0.02673  -0.0639   0.5672   0.0815
  -2.250   0.2751   0.02101   0.01381  -0.0679   0.5638   0.0749
  -2.000   0.3027   0.01977   0.01220  -0.0676   0.5569   0.0774
  -1.750   0.3307   0.01885   0.01093  -0.0673   0.5495   0.0793
  -1.500   0.3582   0.01801   0.00980  -0.0668   0.5435   0.0817
  -1.250   0.3856   0.01744   0.00931  -0.0664   0.5351   0.0857
  -1.000   0.4134   0.01705   0.00875  -0.0659   0.5278   0.0909
  -0.750   0.4409   0.01666   0.00835  -0.0654   0.5197   0.0965
  -0.500   0.4687   0.01638   0.00799  -0.0649   0.5116   0.1044
  -0.250   0.4963   0.01636   0.00798  -0.0644   0.5044   0.1169
   0.000   0.5238   0.01715   0.00905  -0.0637   0.4958   0.1300
   0.250   0.5511   0.01822   0.01017  -0.0629   0.4892   0.1412
   0.500   0.5797   0.01883   0.01080  -0.0624   0.4810   0.1631
   0.750   0.6078   0.01956   0.01139  -0.0618   0.4742   0.1837
   1.000   0.6344   0.01996   0.01182  -0.0613   0.4676   0.1966
   1.250   0.6611   0.02020   0.01202  -0.0609   0.4605   0.2180
   1.500   0.6864   0.02010   0.01194  -0.0604   0.4551   0.2350
   1.750   0.7115   0.02006   0.01195  -0.0600   0.4491   0.2623
   2.000   0.7357   0.01996   0.01193  -0.0594   0.4429   0.2999
   2.250   0.7581   0.01990   0.01186  -0.0585   0.4378   0.3706
   2.500   0.7808   0.01880   0.01083  -0.0579   0.4323   0.4128
   2.750   0.8119   0.01918   0.01104  -0.0581   0.4263   0.3873
   3.000   0.8386   0.01877   0.01056  -0.0578   0.4213   0.3926
   3.250   0.8672   0.01897   0.01066  -0.0577   0.4163   0.3836
   3.500   0.8947   0.01897   0.01064  -0.0575   0.4104   0.3845
   3.750   0.9220   0.01885   0.01045  -0.0573   0.4052   0.3816
   4.000   0.9504   0.01920   0.01065  -0.0571   0.3998   0.3699
   4.250   0.9773   0.01902   0.01052  -0.0570   0.3934   0.3609
   4.500   1.0049   0.01913   0.01051  -0.0567   0.3874   0.3487
   4.750   1.0322   0.01939   0.01069  -0.0565   0.3811   0.3364
   5.000   1.0585   0.01932   0.01065  -0.0562   0.3743   0.3307
   5.250   1.0857   0.01969   0.01080  -0.0558   0.3683   0.3209
   5.500   1.1109   0.01966   0.01090  -0.0555   0.3608   0.3183
   5.750   1.1366   0.01974   0.01092  -0.0552   0.3538   0.3152
   6.000   1.1617   0.01995   0.01113  -0.0548   0.3461   0.3099
   6.250   1.1867   0.02029   0.01140  -0.0542   0.3380   0.3044
   6.500   1.2109   0.02049   0.01159  -0.0538   0.3300   0.3021
   6.750   1.2347   0.02067   0.01181  -0.0533   0.3215   0.2996
   7.000   1.2582   0.02100   0.01211  -0.0527   0.3137   0.2967
   7.250   1.2812   0.02127   0.01241  -0.0521   0.3056   0.2939
   7.500   1.3045   0.02171   0.01274  -0.0515   0.2990   0.2910
   7.750   1.3264   0.02209   0.01322  -0.0508   0.2919   0.2889
   8.000   1.3490   0.02245   0.01355  -0.0502   0.2863   0.2877
   8.250   1.3711   0.02287   0.01399  -0.0495   0.2813   0.2867
   8.500   1.3923   0.02324   0.01448  -0.0488   0.2760   0.2858
   8.750   1.4139   0.02362   0.01488  -0.0481   0.2717   0.2848
   9.000   1.4365   0.02410   0.01529  -0.0476   0.2681   0.2840
   9.250   1.4570   0.02463   0.01597  -0.0469   0.2643   0.2832
   9.500   1.4775   0.02514   0.01657  -0.0462   0.2607   0.2825
   9.750   1.4979   0.02564   0.01712  -0.0454   0.2576   0.2820
  10.000   1.5186   0.02615   0.01762  -0.0447   0.2548   0.2821
  10.250   1.5409   0.02679   0.01822  -0.0442   0.2520   0.2825
  10.500   1.5564   0.02747   0.01906  -0.0429   0.2494   0.2830
  10.750   1.5726   0.02816   0.01986  -0.0418   0.2468   0.2835
  11.000   1.5895   0.02885   0.02063  -0.0407   0.2445   0.2838
  11.250   1.6070   0.02954   0.02137  -0.0398   0.2424   0.2838
  11.500   1.6256   0.03023   0.02209  -0.0389   0.2405   0.2840
  11.750   1.6490   0.03098   0.02281  -0.0387   0.2384   0.2842
  12.000   1.6664   0.03193   0.02383  -0.0379   0.2363   0.2847
  12.250   1.6690   0.03296   0.02504  -0.0353   0.2344   0.2849
  12.500   1.6725   0.03408   0.02630  -0.0333   0.2321   0.2853
  12.750   1.6795   0.03516   0.02747  -0.0318   0.2296   0.2861
  13.000   1.6908   0.03606   0.02841  -0.0307   0.2270   0.2870
  13.250   1.7104   0.03672   0.02903  -0.0302   0.2241   0.2881
  13.500   1.7286   0.03780   0.03014  -0.0297   0.2212   0.2902
  13.750   1.7201   0.03973   0.03229  -0.0279   0.2193   0.2907
  14.000   1.7147   0.04178   0.03451  -0.0267   0.2171   0.2921
  14.250   1.7145   0.04369   0.03655  -0.0259   0.2147   0.2934
  14.500   1.7206   0.04519   0.03813  -0.0253   0.2122   0.2959
  14.750   1.7417   0.04561   0.03851  -0.0249   0.2089   0.3005
  15.000   1.7559   0.04692   0.03985  -0.0244   0.2058   0.3072
  15.250   1.7360   0.05041   0.04359  -0.0239   0.2040   0.3089
  15.500   1.7185   0.05412   0.04751  -0.0238   0.2019   0.3104
  15.750   1.7055   0.05762   0.05118  -0.0241   0.1992   0.3167
  16.000   1.7458   0.05750   0.05173  -0.0282   0.1937   1.0000
  16.250   1.7549   0.05898   0.05321  -0.0278   0.1903   1.0000
  16.500   1.7269   0.06438   0.05888  -0.0288   0.1887   1.0000
  16.750   1.6988   0.07034   0.06507  -0.0303   0.1870   1.0000
  17.000   1.6662   0.07743   0.07240  -0.0324   0.1853   1.0000
  17.750   1.5699   0.10101   0.09650  -0.0410   0.1790   1.0000
  18.000   1.4993   0.11634   0.11202  -0.0474   0.1766   1.0000
  18.250   1.1531   0.19447   0.18937  -0.0857   0.1494   0.2828
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