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NACA M19 AIRFOIL (m19-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M19 AIRFOIL (m19-il)
Reynolds number: 200,000
Max Cl/Cd: 75.45 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m19-il-200000-n5.txt
Download as CSV file: xf-m19-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2883   0.11450   0.11118  -0.0017   0.7809   0.0158
  -9.250  -0.2868   0.11209   0.10875  -0.0031   0.7727   0.0159
  -9.000  -0.2843   0.10929   0.10592  -0.0043   0.7650   0.0160
  -8.750  -0.2815   0.10634   0.10295  -0.0056   0.7573   0.0160
  -8.500  -0.2777   0.10307   0.09966  -0.0067   0.7500   0.0160
  -8.250  -0.2737   0.09967   0.09624  -0.0079   0.7427   0.0160
  -8.000  -0.2694   0.09623   0.09278  -0.0091   0.7358   0.0160
  -7.750  -0.2649   0.09276   0.08929  -0.0105   0.7286   0.0160
  -7.500  -0.2606   0.08925   0.08577  -0.0121   0.7223   0.0160
  -7.250  -0.2536   0.08229   0.07880  -0.0103   0.7161   0.0164
  -6.750  -0.2436   0.07465   0.07109  -0.0112   0.7034   0.0170
  -6.500  -0.2364   0.07105   0.06745  -0.0126   0.6975   0.0173
  -6.250  -0.2276   0.06741   0.06379  -0.0145   0.6914   0.0177
  -6.000  -0.2605   0.08074   0.07683  -0.0211   0.7046   0.0162
  -5.750  -0.2385   0.07754   0.07352  -0.0241   0.6979   0.0160
  -5.500  -0.2365   0.07228   0.06829  -0.0220   0.6918   0.0169
  -5.250  -0.2209   0.07013   0.06608  -0.0226   0.6846   0.0208
  -5.000  -0.1869   0.06763   0.06343  -0.0283   0.6784   0.0238
  -4.750  -0.1610   0.06407   0.05976  -0.0318   0.6720   0.0239
  -4.500  -0.1370   0.06032   0.05588  -0.0344   0.6665   0.0238
  -4.250  -0.1197   0.05591   0.05141  -0.0359   0.6602   0.0212
  -4.000  -0.0917   0.05234   0.04767  -0.0387   0.6546   0.0208
  -3.750  -0.0509   0.04976   0.04483  -0.0428   0.6487   0.0241
  -3.500  -0.0268   0.04606   0.04099  -0.0442   0.6427   0.0236
  -3.000   0.0375   0.04220   0.03670  -0.0478   0.6309   0.0343
  -2.750   0.0694   0.03964   0.03386  -0.0489   0.6255   0.0346
  -2.500   0.0973   0.03594   0.02991  -0.0499   0.6201   0.0351
  -2.250   0.1146   0.03354   0.02752  -0.0503   0.6140   0.0383
  -2.000   0.1536   0.03334   0.02686  -0.0508   0.6087   0.0462
  -1.750   0.1771   0.02962   0.02301  -0.0516   0.6027   0.0478
  -1.500   0.2017   0.02802   0.02131  -0.0519   0.5970   0.0501
  -1.250   0.2347   0.02713   0.02002  -0.0521   0.5914   0.0604
  -1.000   0.2592   0.02533   0.01818  -0.0526   0.5852   0.0625
  -0.750   0.2913   0.02279   0.01518  -0.0522   0.5806   0.0440
  -0.500   0.3200   0.02113   0.01329  -0.0523   0.5745   0.0413
  -0.250   0.3493   0.01954   0.01137  -0.0521   0.5690   0.0398
   0.000   0.3782   0.01827   0.00981  -0.0520   0.5638   0.0398
   0.250   0.4068   0.01730   0.00861  -0.0520   0.5576   0.0405
   0.500   0.4348   0.01664   0.00774  -0.0519   0.5523   0.0421
   0.750   0.4631   0.01618   0.00713  -0.0519   0.5463   0.0446
   1.000   0.4910   0.01554   0.00634  -0.0519   0.5406   0.0439
   1.250   0.5188   0.01502   0.00569  -0.0518   0.5355   0.0431
   1.500   0.5465   0.01457   0.00518  -0.0518   0.5292   0.0424
   1.750   0.5738   0.01421   0.00474  -0.0517   0.5238   0.0418
   2.000   0.6011   0.01391   0.00443  -0.0516   0.5180   0.0413
   2.250   0.6282   0.01369   0.00420  -0.0516   0.5124   0.0410
   2.500   0.6551   0.01353   0.00402  -0.0515   0.5075   0.0407
   2.750   0.6824   0.01341   0.00393  -0.0515   0.5014   0.0407
   3.000   0.7095   0.01336   0.00385  -0.0514   0.4959   0.0407
   3.250   0.7367   0.01334   0.00383  -0.0514   0.4903   0.0411
   3.500   0.7638   0.01335   0.00386  -0.0514   0.4846   0.0417
   3.750   0.7909   0.01341   0.00389  -0.0513   0.4800   0.0428
   4.000   0.8183   0.01348   0.00401  -0.0514   0.4744   0.0450
   4.250   0.8455   0.01355   0.00418  -0.0514   0.4692   0.0591
   4.500   0.8871   0.01225   0.00450  -0.0547   0.4624   1.0000
   4.750   0.9129   0.01235   0.00454  -0.0545   0.4427   1.0000
   5.000   0.9383   0.01252   0.00463  -0.0543   0.4216   1.0000
   5.250   0.9635   0.01277   0.00482  -0.0540   0.3940   1.0000
   5.500   0.9881   0.01315   0.00508  -0.0538   0.3548   1.0000
   5.750   1.0013   0.01557   0.00632  -0.0533   0.1613   1.0000
   6.000   1.0149   0.01791   0.00804  -0.0525   0.0231   1.0000
   6.250   1.0373   0.01861   0.00890  -0.0520   0.0185   1.0000
   6.500   1.0586   0.01943   0.00989  -0.0513   0.0164   1.0000
   6.750   1.0775   0.02054   0.01126  -0.0505   0.0149   1.0000
   7.000   1.0961   0.02155   0.01242  -0.0496   0.0135   1.0000
   7.250   1.1128   0.02270   0.01373  -0.0487   0.0124   1.0000
   7.500   1.1256   0.02414   0.01532  -0.0474   0.0119   1.0000
   7.750   1.1350   0.02577   0.01711  -0.0459   0.0114   1.0000
   8.000   1.1413   0.02752   0.01896  -0.0441   0.0111   1.0000
   8.250   1.1435   0.02936   0.02089  -0.0421   0.0109   1.0000
   8.500   1.1462   0.03138   0.02298  -0.0405   0.0106   1.0000
   8.750   1.1512   0.03334   0.02499  -0.0392   0.0099   1.0000
   9.000   1.1563   0.03534   0.02700  -0.0379   0.0092   1.0000
   9.250   1.1626   0.03746   0.02905  -0.0355   0.0085   1.0000
   9.500   1.1826   0.03920   0.03077  -0.0328   0.0082   1.0000
   9.750   1.1995   0.04078   0.03248  -0.0314   0.0081   1.0000
  10.000   1.2191   0.04258   0.03448  -0.0299   0.0079   1.0000
  10.250   1.2392   0.04473   0.03680  -0.0286   0.0079   1.0000
  10.500   1.2582   0.04732   0.03959  -0.0275   0.0079   1.0000
  10.750   1.2741   0.05038   0.04288  -0.0263   0.0079   1.0000
  11.750   1.2824   0.06331   0.05676  -0.0212   0.0080   1.0000
  12.000   1.2733   0.06601   0.05969  -0.0205   0.0079   1.0000
  12.250   1.2641   0.06894   0.06287  -0.0202   0.0076   1.0000
  12.500   1.2548   0.07253   0.06669  -0.0201   0.0075   1.0000
  12.750   1.2445   0.07638   0.07076  -0.0205   0.0073   1.0000
  13.000   1.2331   0.08068   0.07528  -0.0212   0.0071   1.0000
  13.250   1.2206   0.08534   0.08015  -0.0222   0.0071   1.0000
  13.500   1.2068   0.09032   0.08532  -0.0236   0.0070   1.0000
  13.750   1.1923   0.09564   0.09083  -0.0253   0.0071   1.0000
  14.000   1.1770   0.10127   0.09663  -0.0275   0.0071   1.0000
  14.250   1.1616   0.10727   0.10280  -0.0301   0.0071   1.0000
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