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NACA M19 AIRFOIL (m19-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M19 AIRFOIL (m19-il)
Reynolds number: 500,000
Max Cl/Cd: 102.54 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m19-il-500000.txt
Download as CSV file: xf-m19-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2806   0.08601   0.08336  -0.0003   0.7173   0.0144
  -7.250  -0.2767   0.08312   0.08046  -0.0025   0.7111   0.0146
  -7.000  -0.2740   0.08014   0.07748  -0.0051   0.7045   0.0147
  -6.750  -0.2672   0.07675   0.07404  -0.0088   0.6988   0.0148
  -6.500  -0.2560   0.07293   0.07019  -0.0131   0.6925   0.0149
  -6.250  -0.2426   0.06890   0.06610  -0.0167   0.6869   0.0149
  -6.000  -0.2352   0.06320   0.06039  -0.0175   0.6815   0.0151
  -5.750  -0.2279   0.05912   0.05629  -0.0164   0.6753   0.0155
  -5.500  -0.2145   0.05577   0.05288  -0.0179   0.6697   0.0161
  -5.250  -0.1979   0.05213   0.04921  -0.0204   0.6636   0.0168
  -5.000  -0.1795   0.04844   0.04542  -0.0231   0.6583   0.0174
  -4.750  -0.1584   0.04474   0.04166  -0.0260   0.6526   0.0186
  -4.500  -0.1234   0.04185   0.03862  -0.0312   0.6470   0.0199
  -4.250  -0.0956   0.03835   0.03497  -0.0343   0.6423   0.0200
  -4.000  -0.0702   0.03472   0.03124  -0.0364   0.6365   0.0201
  -3.750  -0.0617   0.04925   0.04538  -0.0383   0.6433   0.0202
  -3.500  -0.0426   0.04377   0.03982  -0.0400   0.6378   0.0209
  -3.250  -0.0211   0.04137   0.03734  -0.0407   0.6319   0.0215
  -3.000   0.0045   0.03921   0.03506  -0.0417   0.6263   0.0227
  -2.750   0.0337   0.03702   0.03275  -0.0428   0.6202   0.0251
  -2.500   0.0733   0.03600   0.03145  -0.0438   0.6148   0.0275
  -2.250   0.1038   0.03376   0.02905  -0.0444   0.6090   0.0277
  -2.000   0.1331   0.03128   0.02636  -0.0449   0.6036   0.0278
  -1.750   0.1558   0.02685   0.02173  -0.0457   0.5989   0.0294
  -1.500   0.1820   0.02544   0.02023  -0.0461   0.5928   0.0305
  -1.250   0.2094   0.02417   0.01881  -0.0464   0.5873   0.0327
  -1.000   0.2400   0.02283   0.01728  -0.0464   0.5816   0.0364
  -0.750   0.2723   0.02241   0.01661  -0.0460   0.5760   0.0382
  -0.500   0.2978   0.01916   0.01311  -0.0465   0.5712   0.0408
  -0.250   0.3252   0.01831   0.01220  -0.0467   0.5650   0.0430
   0.000   0.3536   0.01748   0.01119  -0.0467   0.5593   0.0469
   1.000   0.4664   0.01440   0.00760  -0.0470   0.5365   0.0686
   1.500   0.5225   0.01345   0.00649  -0.0471   0.5248   0.0854
   1.750   0.5531   0.01132   0.00392  -0.0460   0.5197   0.0456
   2.000   0.5807   0.01095   0.00347  -0.0459   0.5145   0.0449
   2.250   0.6084   0.01069   0.00323  -0.0459   0.5084   0.0460
   2.500   0.6358   0.01044   0.00292  -0.0458   0.5029   0.0446
   2.750   0.6634   0.01025   0.00273  -0.0458   0.4968   0.0436
   3.000   0.6910   0.01014   0.00260  -0.0458   0.4903   0.0432
   3.250   0.7187   0.01009   0.00255  -0.0459   0.4839   0.0434
   3.500   0.7466   0.01006   0.00253  -0.0459   0.4777   0.0446
   3.750   0.7743   0.01009   0.00254  -0.0460   0.4716   0.0477
   4.000   0.8019   0.01004   0.00256  -0.0461   0.4606   0.0871
   4.250   0.8443   0.00851   0.00277  -0.0499   0.4456   1.0000
   4.500   0.8708   0.00861   0.00284  -0.0497   0.4332   1.0000
   4.750   0.8970   0.00876   0.00291  -0.0496   0.4137   1.0000
   5.000   0.9229   0.00900   0.00303  -0.0495   0.3848   1.0000
   5.250   0.9477   0.00954   0.00330  -0.0494   0.3294   1.0000
   5.500   0.9610   0.01281   0.00514  -0.0492   0.0545   1.0000
   5.750   0.9848   0.01350   0.00574  -0.0489   0.0221   1.0000
   6.000   1.0095   0.01395   0.00628  -0.0486   0.0200   1.0000
   6.250   1.0336   0.01453   0.00695  -0.0482   0.0183   1.0000
   6.500   1.0565   0.01529   0.00784  -0.0477   0.0171   1.0000
   6.750   1.0765   0.01646   0.00917  -0.0470   0.0157   1.0000
   7.000   1.0952   0.01766   0.01048  -0.0462   0.0149   1.0000
   7.250   1.1146   0.01865   0.01156  -0.0454   0.0145   1.0000
   7.500   1.1316   0.01983   0.01283  -0.0443   0.0141   1.0000
   7.750   1.1459   0.02122   0.01431  -0.0429   0.0138   1.0000
   8.000   1.1573   0.02281   0.01600  -0.0412   0.0139   1.0000
   8.250   1.1665   0.02465   0.01789  -0.0391   0.0142   1.0000
   8.500   1.1836   0.02576   0.01902  -0.0376   0.0165   1.0000
   9.250   1.1801   0.01911   0.01297  -0.0262   0.0213   1.0000
   9.500   1.1968   0.02084   0.01480  -0.0249   0.0196   1.0000
   9.750   1.2172   0.02320   0.01720  -0.0243   0.0180   1.0000
  10.000   1.2471   0.02721   0.02119  -0.0250   0.0163   1.0000
  10.250   1.3248   0.04547   0.03956  -0.0306   0.0149   1.0000
  10.500   1.2650   0.03816   0.03272  -0.0221   0.0149   1.0000
  10.750   1.2623   0.03782   0.03256  -0.0190   0.0142   1.0000
  11.000   1.2559   0.03893   0.03382  -0.0157   0.0136   1.0000
  11.250   1.2487   0.04097   0.03604  -0.0132   0.0131   1.0000
  11.500   1.2404   0.04367   0.03891  -0.0111   0.0128   1.0000
  11.750   1.2300   0.04675   0.04217  -0.0094   0.0125   1.0000
  12.000   1.2176   0.05022   0.04581  -0.0080   0.0123   1.0000
  12.250   1.2035   0.05405   0.04980  -0.0068   0.0122   1.0000
  12.500   1.1878   0.05822   0.05414  -0.0060   0.0120   1.0000
  12.750   1.1708   0.06269   0.05877  -0.0054   0.0119   1.0000
  13.000   1.1523   0.06744   0.06367  -0.0051   0.0119   1.0000
  13.250   1.1327   0.07241   0.06879  -0.0052   0.0118   1.0000
  13.500   1.1123   0.07752   0.07405  -0.0056   0.0118   1.0000
  13.750   1.0904   0.08274   0.07942  -0.0063   0.0119   1.0000
  14.000   1.0675   0.08812   0.08494  -0.0074   0.0119   1.0000
  14.250   1.0437   0.09362   0.09058  -0.0089   0.0119   1.0000
  14.500   1.0181   0.09908   0.09618  -0.0106   0.0121   1.0000
  14.750   0.9869   0.10395   0.10119  -0.0123   0.0123   1.0000
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