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NACA M19 AIRFOIL (m19-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M19 AIRFOIL (m19-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117.89 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m19-il-1000000.txt
Download as CSV file: xf-m19-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M19 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4163   0.11120   0.10895   0.0179   0.7178   0.0076
  -8.250  -0.4133   0.10678   0.10452   0.0166   0.7105   0.0077
  -8.000  -0.4070   0.10360   0.10131   0.0155   0.7024   0.0078
  -7.750  -0.4002   0.10063   0.09833   0.0140   0.6947   0.0079
  -7.500  -0.3931   0.09772   0.09539   0.0121   0.6871   0.0081
  -7.250  -0.3852   0.09477   0.09242   0.0098   0.6801   0.0082
  -7.000  -0.3732   0.09155   0.08916   0.0067   0.6731   0.0084
  -6.750  -0.3596   0.08824   0.08582   0.0035   0.6667   0.0088
  -6.500  -0.3444   0.08484   0.08238   0.0000   0.6601   0.0092
  -6.250  -0.3272   0.08125   0.07875  -0.0036   0.6543   0.0100
  -6.000  -0.3018   0.07729   0.07474  -0.0094   0.6484   0.0107
  -5.500  -0.2547   0.06925   0.06658  -0.0184   0.6373   0.0108
  -5.250  -0.2394   0.06443   0.06171  -0.0208   0.6320   0.0112
  -5.000  -0.2185   0.06181   0.05903  -0.0228   0.6264   0.0115
  -4.750  -0.1949   0.05918   0.05633  -0.0253   0.6205   0.0122
  -4.500  -0.1679   0.05632   0.05338  -0.0280   0.6151   0.0140
  -4.250  -0.1300   0.05294   0.04988  -0.0325   0.6100   0.0147
  -4.000  -0.0996   0.04921   0.04603  -0.0353   0.6048   0.0148
  -3.750  -0.0700   0.04556   0.04224  -0.0375   0.5999   0.0149
  -3.500  -0.0481   0.04105   0.03764  -0.0392   0.5951   0.0155
  -3.250  -0.0241   0.03942   0.03594  -0.0400   0.5894   0.0161
  -3.000   0.0029   0.03776   0.03418  -0.0410   0.5843   0.0179
  -2.750   0.0414   0.03573   0.03198  -0.0423   0.5791   0.0199
  -2.000   0.1266   0.02582   0.02152  -0.0445   0.5645   0.0213
  -1.750   0.1525   0.02480   0.02041  -0.0449   0.5591   0.0221
  -1.500   0.1801   0.02359   0.01909  -0.0452   0.5539   0.0235
  -1.250   0.2107   0.02254   0.01791  -0.0452   0.5482   0.0267
  -1.000   0.2408   0.02151   0.01672  -0.0450   0.5429   0.0275
  -0.750   0.2700   0.01975   0.01478  -0.0449   0.5379   0.0276
  -0.500   0.2988   0.01796   0.01276  -0.0448   0.5328   0.0277
  -0.250   0.3268   0.01435   0.00870  -0.0447   0.5283   0.0288
   0.000   0.3545   0.01333   0.00756  -0.0448   0.5227   0.0298
   0.250   0.3823   0.01281   0.00696  -0.0450   0.5168   0.0307
   0.500   0.4104   0.01229   0.00636  -0.0451   0.5112   0.0319
   0.750   0.4386   0.01170   0.00565  -0.0451   0.5056   0.0333
   1.000   0.4669   0.01121   0.00505  -0.0452   0.5002   0.0351
   1.250   0.4955   0.01178   0.00561  -0.0453   0.4944   0.0381
   1.500   0.5235   0.00993   0.00354  -0.0451   0.4889   0.0356
   1.750   0.5516   0.00952   0.00307  -0.0451   0.4829   0.0361
   2.000   0.5794   0.00918   0.00268  -0.0451   0.4759   0.0358
   2.250   0.6071   0.00891   0.00239  -0.0451   0.4699   0.0353
   2.500   0.6349   0.00872   0.00218  -0.0451   0.4641   0.0351
   2.750   0.6627   0.00862   0.00204  -0.0452   0.4585   0.0354
   3.000   0.6906   0.00848   0.00190  -0.0453   0.4529   0.0345
   3.500   0.7464   0.00844   0.00178  -0.0455   0.4325   0.0337
   3.750   0.7744   0.00844   0.00176  -0.0457   0.4228   0.0340
   4.000   0.8022   0.00850   0.00177  -0.0458   0.4095   0.0354
   4.250   0.8298   0.00863   0.00183  -0.0460   0.3911   0.0382
   4.500   0.8573   0.00874   0.00196  -0.0462   0.3701   0.0860
   4.750   0.8842   0.00750   0.00233  -0.0468   0.3325   0.9933
   5.000   0.9133   0.01038   0.00386  -0.0497   0.0659   1.0000
   5.500   0.9630   0.01137   0.00475  -0.0492   0.0149   1.0000
   5.750   0.9883   0.01170   0.00512  -0.0489   0.0141   1.0000
   6.000   1.0134   0.01210   0.00556  -0.0487   0.0130   1.0000
   6.250   1.0380   0.01258   0.00609  -0.0484   0.0117   1.0000
   6.500   1.0617   0.01320   0.00678  -0.0480   0.0105   1.0000
   6.750   1.0829   0.01426   0.00796  -0.0474   0.0098   1.0000
   7.000   1.1021   0.01551   0.00933  -0.0467   0.0093   1.0000
   7.250   1.1257   0.01597   0.00983  -0.0463   0.0089   1.0000
   7.500   1.1468   0.01675   0.01067  -0.0457   0.0084   1.0000
   7.750   1.1651   0.01785   0.01184  -0.0448   0.0080   1.0000
   8.000   1.1806   0.01916   0.01324  -0.0435   0.0079   1.0000
   8.250   1.1969   0.02028   0.01442  -0.0424   0.0076   1.0000
   8.500   1.2134   0.02130   0.01547  -0.0413   0.0072   1.0000
   8.750   1.2266   0.02265   0.01687  -0.0398   0.0070   1.0000
   9.000   1.2391   0.02413   0.01841  -0.0381   0.0070   1.0000
   9.250   1.2527   0.02552   0.01985  -0.0366   0.0069   1.0000
   9.500   1.2670   0.02695   0.02134  -0.0350   0.0068   1.0000
   9.750   1.2797   0.02812   0.02252  -0.0336   0.0064   1.0000
  10.000   1.2978   0.02989   0.02429  -0.0326   0.0061   1.0000
  10.250   1.3267   0.03297   0.02745  -0.0325   0.0060   1.0000
  10.500   1.3461   0.03647   0.03137  -0.0304   0.0068   1.0000
  10.750   1.3590   0.03860   0.03362  -0.0293   0.0066   1.0000
  11.000   1.3703   0.04086   0.03599  -0.0281   0.0064   1.0000
  11.250   1.3804   0.04331   0.03854  -0.0269   0.0063   1.0000
  11.500   1.3851   0.04604   0.04142  -0.0252   0.0062   1.0000
  11.750   1.3854   0.04947   0.04501  -0.0233   0.0060   1.0000
  12.000   1.3602   0.05933   0.05528  -0.0205   0.0057   1.0000
  12.250   1.3464   0.06214   0.05825  -0.0184   0.0057   1.0000
  12.500   1.3319   0.06532   0.06159  -0.0171   0.0057   1.0000
  12.750   1.3167   0.06883   0.06526  -0.0165   0.0057   1.0000
  13.000   1.3010   0.07267   0.06925  -0.0164   0.0057   1.0000
  13.250   1.2847   0.07684   0.07356  -0.0168   0.0057   1.0000
  13.500   1.2680   0.08134   0.07820  -0.0177   0.0057   1.0000
  13.750   1.2507   0.08613   0.08314  -0.0190   0.0057   1.0000
  14.000   1.2332   0.09123   0.08837  -0.0207   0.0057   1.0000
  14.250   1.2152   0.09666   0.09393  -0.0228   0.0057   1.0000
  14.500   1.1977   0.10235   0.09974  -0.0253   0.0057   1.0000
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