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NACA M14 AIRFOIL (m14-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA M14 AIRFOIL (m14-il)
Reynolds number: 50,000
Max Cl/Cd: 38.1 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m14-il-50000.txt
Download as CSV file: xf-m14-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4172   0.10773   0.10108  -0.0129   1.0000   0.1572
  -8.000  -0.4070   0.10396   0.09732  -0.0127   1.0000   0.1656
  -7.750  -0.4204   0.10338   0.09689  -0.0173   1.0000   0.1693
  -7.500  -0.4008   0.09754   0.09104  -0.0146   1.0000   0.1762
  -7.250  -0.4054   0.09578   0.08938  -0.0184   1.0000   0.1833
  -7.000  -0.3951   0.09137   0.08500  -0.0177   1.0000   0.1891
  -6.750  -0.3965   0.08961   0.08329  -0.0221   1.0000   0.1985
  -6.500  -0.3838   0.08497   0.07871  -0.0196   1.0000   0.2063
  -6.000  -0.3801   0.08017   0.07401  -0.0247   1.0000   0.2291
  -5.750  -0.3757   0.07731   0.07122  -0.0243   1.0000   0.2436
  -5.500  -0.3713   0.07409   0.06807  -0.0225   1.0000   0.2588
  -5.250  -0.3680   0.07101   0.06509  -0.0202   1.0000   0.2745
  -5.000  -0.3663   0.06829   0.06246  -0.0176   1.0000   0.2909
  -4.750  -0.3666   0.06591   0.06016  -0.0148   1.0000   0.3090
  -4.500   0.0023   0.04287   0.03607  -0.0220   1.0000   1.0000
  -4.250   0.0153   0.04083   0.03409  -0.0235   1.0000   1.0000
  -4.000   0.0283   0.03888   0.03220  -0.0250   1.0000   1.0000
  -3.500  -0.3878   0.05520   0.04990   0.0074   1.0000   0.4724
  -3.250  -0.3932   0.05308   0.04790   0.0140   1.0000   0.5169
  -3.000  -0.3979   0.05097   0.04590   0.0208   1.0000   0.5610
  -2.750  -0.4002   0.04891   0.04391   0.0255   1.0000   0.6009
  -2.500  -0.3991   0.04664   0.04173   0.0311   1.0000   0.6346
  -2.250  -0.3898   0.04432   0.03942   0.0318   1.0000   0.6561
  -2.000  -0.3631   0.04166   0.03663   0.0255   1.0000   0.6593
  -1.750  -0.1746   0.03942   0.03200  -0.0303   1.0000   0.3207
  -1.500  -0.1187   0.03845   0.02958  -0.0356   1.0000   0.1991
  -1.250  -0.0695   0.03641   0.02707  -0.0402   0.9929   0.1830
  -1.000  -0.0139   0.03474   0.02476  -0.0455   0.9833   0.1684
  -0.750   0.0342   0.03328   0.02297  -0.0497   0.9728   0.1619
  -0.500   0.0820   0.03230   0.02154  -0.0536   0.9620   0.1583
  -0.250   0.1290   0.03153   0.02046  -0.0572   0.9512   0.1594
   0.000   0.1816   0.03106   0.01969  -0.0617   0.9409   0.1702
   0.250   0.2222   0.03060   0.01917  -0.0642   0.9288   0.1826
   0.500   0.2620   0.03017   0.01873  -0.0665   0.9170   0.2006
   0.750   0.3036   0.02933   0.01827  -0.0692   0.9060   0.2649
   1.000   0.3605   0.02743   0.01748  -0.0734   0.8965   1.0000
   1.250   0.3943   0.02805   0.01784  -0.0750   0.8828   1.0000
   1.500   0.4270   0.02869   0.01829  -0.0764   0.8693   1.0000
   1.750   0.4588   0.02935   0.01882  -0.0776   0.8560   1.0000
   2.000   0.4895   0.03004   0.01942  -0.0786   0.8429   1.0000
   2.250   0.5194   0.03074   0.02004  -0.0793   0.8300   1.0000
   2.500   0.5498   0.03142   0.02067  -0.0800   0.8175   1.0000
   2.750   0.5833   0.03198   0.02121  -0.0810   0.8058   1.0000
   3.000   0.6133   0.03261   0.02186  -0.0814   0.7937   1.0000
   3.250   0.6341   0.03358   0.02284  -0.0808   0.7804   1.0000
   3.500   0.6552   0.03458   0.02386  -0.0802   0.7673   1.0000
   3.750   0.6762   0.03565   0.02496  -0.0796   0.7547   1.0000
   4.000   0.6987   0.03666   0.02605  -0.0792   0.7424   1.0000
   4.250   0.7265   0.03743   0.02690  -0.0791   0.7314   1.0000
   4.500   0.7526   0.03826   0.02781  -0.0788   0.7200   1.0000
   4.750   0.7668   0.03980   0.02943  -0.0778   0.7070   1.0000
   5.000   0.7810   0.04142   0.03117  -0.0769   0.6945   1.0000
   5.250   0.7971   0.04297   0.03282  -0.0760   0.6825   1.0000
   5.500   0.8205   0.04408   0.03407  -0.0755   0.6716   1.0000
   5.750   0.8482   0.04485   0.03500  -0.0751   0.6608   1.0000
   6.000   0.8567   0.04698   0.03725  -0.0740   0.6477   1.0000
   6.250   0.8661   0.04907   0.03950  -0.0729   0.6348   1.0000
   6.500   0.8789   0.05089   0.04147  -0.0718   0.6216   1.0000
   6.750   0.8943   0.05247   0.04323  -0.0707   0.6081   1.0000
   7.000   0.9118   0.05382   0.04477  -0.0695   0.5940   1.0000
   7.250   0.9306   0.05497   0.04614  -0.0681   0.5791   1.0000
   7.500   0.9522   0.05575   0.04721  -0.0665   0.5635   1.0000
   7.750   1.0321   0.04786   0.03990  -0.0608   0.5349   1.0000
   8.000   1.1178   0.02934   0.02135  -0.0456   0.4210   1.0000
   8.250   1.1021   0.02970   0.02073  -0.0374   0.2556   1.0000
   8.500   1.0860   0.03335   0.02318  -0.0326   0.1738   1.0000
   8.750   1.0820   0.03637   0.02576  -0.0291   0.1464   1.0000
   9.000   1.0871   0.03888   0.02804  -0.0262   0.1291   1.0000
   9.250   1.1048   0.04109   0.03018  -0.0244   0.1139   1.0000
   9.500   1.1481   0.04361   0.03260  -0.0244   0.1026   1.0000
   9.750   1.1825   0.04636   0.03560  -0.0241   0.0961   1.0000
  10.000   1.2137   0.04996   0.03921  -0.0243   0.0903   1.0000
  10.250   1.2305   0.05330   0.04306  -0.0228   0.0886   1.0000
  10.500   1.2437   0.05713   0.04734  -0.0213   0.0882   1.0000
  10.750   1.2509   0.06118   0.05184  -0.0195   0.0883   1.0000
  11.000   1.2528   0.06540   0.05651  -0.0176   0.0888   1.0000
  11.250   1.2492   0.06966   0.06114  -0.0156   0.0893   1.0000
  11.500   1.2411   0.07395   0.06575  -0.0137   0.0898   1.0000
  11.750   1.2291   0.07820   0.07026  -0.0118   0.0902   1.0000
  12.000   1.2150   0.08260   0.07486  -0.0102   0.0907   1.0000
  12.250   1.2024   0.08750   0.07993  -0.0094   0.0912   1.0000
  12.500   1.1243   0.09321   0.08610  -0.0122   0.0944   1.0000
  12.750   1.0740   0.10273   0.09579  -0.0183   0.0965   1.0000
  13.000   1.0279   0.11468   0.10780  -0.0265   0.0994   1.0000
  13.250   1.0058   0.12454   0.11765  -0.0319   0.1021   1.0000
  13.500   1.0072   0.13037   0.12348  -0.0329   0.1039   1.0000
  13.750   0.9588   0.14966   0.14258  -0.0471   0.1160   1.0000
  14.000   0.7616   0.14325   0.13651  -0.0291   0.1308   1.0000
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