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NACA M14 AIRFOIL (m14-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M14 AIRFOIL (m14-il)
Reynolds number: 200,000
Max Cl/Cd: 75.43 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m14-il-200000-n5.txt
Download as CSV file: xf-m14-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M14 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4358   0.11723   0.11369  -0.0065   1.0000   0.0247
  -9.500  -0.4326   0.11372   0.11021  -0.0089   1.0000   0.0248
  -9.250  -0.4302   0.11024   0.10676  -0.0116   1.0000   0.0250
  -9.000  -0.4267   0.10659   0.10314  -0.0143   1.0000   0.0251
  -8.750  -0.4228   0.10281   0.09939  -0.0167   1.0000   0.0252
  -8.500  -0.4190   0.09893   0.09554  -0.0188   1.0000   0.0252
  -8.250  -0.4157   0.09504   0.09168  -0.0210   1.0000   0.0252
  -8.000  -0.4125   0.09113   0.08780  -0.0230   1.0000   0.0251
  -7.750  -0.4071   0.08727   0.08396  -0.0231   1.0000   0.0247
  -7.250  -0.3936   0.07729   0.07399  -0.0339   1.0000   0.0257
  -7.000  -0.3846   0.07697   0.07372  -0.0288   1.0000   0.0281
  -6.750  -0.3743   0.07394   0.07070  -0.0312   1.0000   0.0306
  -6.000  -0.2553   0.04123   0.03782  -0.0537   0.9125   0.0359
  -5.500  -0.2530   0.04898   0.04501  -0.0574   0.9274   0.0330
  -5.250  -0.2291   0.04468   0.04048  -0.0596   0.9103   0.0325
  -5.000  -0.2047   0.04024   0.03572  -0.0616   0.8938   0.0361
  -4.750  -0.1776   0.03532   0.03027  -0.0623   0.8784   0.0348
  -4.500  -0.1538   0.03265   0.02726  -0.0621   0.8631   0.0346
  -4.250  -0.1324   0.02903   0.02323  -0.0620   0.8488   0.0349
  -4.000  -0.1103   0.02676   0.02071  -0.0619   0.8347   0.0362
  -3.750  -0.0857   0.02443   0.01797  -0.0615   0.8214   0.0363
  -3.500  -0.0602   0.02229   0.01539  -0.0610   0.8088   0.0361
  -3.250  -0.0344   0.02068   0.01342  -0.0606   0.7966   0.0362
  -3.000  -0.0082   0.01937   0.01178  -0.0602   0.7850   0.0365
  -2.500   0.0450   0.01749   0.00943  -0.0596   0.7622   0.0378
  -2.250   0.0720   0.01682   0.00858  -0.0594   0.7514   0.0390
  -2.000   0.0991   0.01605   0.00758  -0.0591   0.7411   0.0391
  -1.750   0.1263   0.01535   0.00671  -0.0588   0.7308   0.0391
  -1.500   0.1536   0.01474   0.00597  -0.0585   0.7205   0.0391
  -1.250   0.1806   0.01423   0.00534  -0.0582   0.7107   0.0394
  -1.000   0.2076   0.01379   0.00481  -0.0579   0.7009   0.0398
  -0.750   0.2347   0.01340   0.00438  -0.0577   0.6907   0.0403
  -0.500   0.2617   0.01309   0.00400  -0.0575   0.6811   0.0411
  -0.250   0.2887   0.01283   0.00368  -0.0573   0.6714   0.0420
   0.000   0.3159   0.01262   0.00343  -0.0571   0.6614   0.0431
   0.250   0.3432   0.01247   0.00321  -0.0569   0.6523   0.0442
   0.500   0.3705   0.01235   0.00305  -0.0568   0.6428   0.0466
   0.750   0.3978   0.01222   0.00291  -0.0567   0.6336   0.0509
   1.000   0.4252   0.01216   0.00281  -0.0566   0.6250   0.0542
   1.250   0.4527   0.01208   0.00275  -0.0565   0.6156   0.0625
   1.500   0.4794   0.01183   0.00277  -0.0564   0.6070   0.1592
   2.000   0.5487   0.01001   0.00287  -0.0594   0.5886   1.0000
   2.500   0.6015   0.01025   0.00297  -0.0588   0.5710   1.0000
   2.750   0.6279   0.01038   0.00304  -0.0585   0.5624   1.0000
   3.000   0.6543   0.01052   0.00313  -0.0582   0.5535   1.0000
   3.250   0.6809   0.01065   0.00326  -0.0580   0.5445   1.0000
   3.500   0.7073   0.01081   0.00337  -0.0577   0.5362   1.0000
   3.750   0.7339   0.01096   0.00353  -0.0575   0.5267   1.0000
   4.000   0.7603   0.01112   0.00370  -0.0573   0.5178   1.0000
   4.250   0.7867   0.01130   0.00387  -0.0571   0.5090   1.0000
   4.500   0.8132   0.01147   0.00408  -0.0569   0.4995   1.0000
   4.750   0.8395   0.01166   0.00428  -0.0566   0.4904   1.0000
   5.000   0.8658   0.01185   0.00453  -0.0564   0.4808   1.0000
   5.250   0.8920   0.01205   0.00479  -0.0562   0.4707   1.0000
   5.500   0.9177   0.01226   0.00502  -0.0558   0.4557   1.0000
   5.750   0.9423   0.01251   0.00524  -0.0553   0.4325   1.0000
   6.000   0.9663   0.01281   0.00547  -0.0547   0.4010   1.0000
   6.250   0.9890   0.01326   0.00576  -0.0540   0.3613   1.0000
   6.500   1.0109   0.01383   0.00616  -0.0533   0.3149   1.0000
   6.750   1.0313   0.01459   0.00670  -0.0524   0.2575   1.0000
   7.000   1.0443   0.01625   0.00770  -0.0509   0.1455   1.0000
   7.250   1.0548   0.01822   0.00906  -0.0490   0.0528   1.0000
   7.500   1.0723   0.01933   0.01009  -0.0477   0.0326   1.0000
   7.750   1.0909   0.02024   0.01105  -0.0466   0.0261   1.0000
   8.000   1.1095   0.02110   0.01201  -0.0454   0.0226   1.0000
   8.250   1.1272   0.02200   0.01305  -0.0441   0.0201   1.0000
   8.500   1.1421   0.02311   0.01426  -0.0425   0.0185   1.0000
   8.750   1.1515   0.02462   0.01589  -0.0403   0.0173   1.0000
   9.000   1.1637   0.02578   0.01718  -0.0384   0.0166   1.0000
   9.250   1.1752   0.02693   0.01845  -0.0364   0.0156   1.0000
   9.500   1.1834   0.02813   0.01975  -0.0341   0.0147   1.0000
   9.750   1.1896   0.02952   0.02127  -0.0316   0.0140   1.0000
  10.000   1.1957   0.03107   0.02291  -0.0295   0.0135   1.0000
  10.250   1.2018   0.03273   0.02467  -0.0276   0.0131   1.0000
  10.500   1.2080   0.03453   0.02656  -0.0259   0.0127   1.0000
  10.750   1.2140   0.03647   0.02859  -0.0243   0.0123   1.0000
  11.000   1.2201   0.03864   0.03085  -0.0227   0.0119   1.0000
  11.250   1.2271   0.04121   0.03353  -0.0209   0.0115   1.0000
  11.500   1.2351   0.04303   0.03554  -0.0198   0.0111   1.0000
  11.750   1.2420   0.04505   0.03776  -0.0188   0.0107   1.0000
  12.000   1.2475   0.04732   0.04023  -0.0177   0.0103   1.0000
  12.250   1.2512   0.04990   0.04305  -0.0168   0.0100   1.0000
  12.500   1.2529   0.05276   0.04613  -0.0159   0.0098   1.0000
  12.750   1.2522   0.05590   0.04949  -0.0152   0.0096   1.0000
  13.000   1.2493   0.05933   0.05315  -0.0149   0.0095   1.0000
  13.250   1.2440   0.06309   0.05714  -0.0148   0.0094   1.0000
  13.500   1.2365   0.06720   0.06148  -0.0151   0.0093   1.0000
  13.750   1.2268   0.07169   0.06620  -0.0158   0.0092   1.0000
  14.000   1.2151   0.07661   0.07134  -0.0169   0.0092   1.0000
  14.250   1.2015   0.08200   0.07695  -0.0186   0.0091   1.0000
  14.500   1.1862   0.08786   0.08303  -0.0207   0.0091   1.0000
  14.750   1.1695   0.09435   0.08974  -0.0235   0.0091   1.0000
  15.000   1.1517   0.10148   0.09708  -0.0270   0.0092   1.0000
  15.250   1.1325   0.10935   0.10515  -0.0312   0.0092   1.0000
  15.500   1.1123   0.11809   0.11408  -0.0363   0.0093   1.0000
  15.750   1.0907   0.12789   0.12406  -0.0422   0.0094   1.0000
  16.000   1.0673   0.13908   0.13543  -0.0491   0.0096   1.0000
  16.250   1.0407   0.15271   0.14919  -0.0574   0.0098   1.0000
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