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NACA M14 AIRFOIL (m14-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA M14 AIRFOIL (m14-il)
Reynolds number: 100,000
Max Cl/Cd: 57.34 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m14-il-100000.txt
Download as CSV file: xf-m14-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3969   0.09495   0.09024  -0.0171   1.0000   0.0747
  -7.500  -0.3954   0.09207   0.08741  -0.0196   1.0000   0.0773
  -7.250  -0.3927   0.08986   0.08523  -0.0281   1.0000   0.0801
  -6.750  -0.3784   0.08148   0.07691  -0.0319   1.0000   0.0829
  -6.500  -0.3691   0.07804   0.07351  -0.0299   1.0000   0.0855
  -6.250  -0.3604   0.07506   0.07054  -0.0308   1.0000   0.0897
  -6.000  -0.3489   0.07532   0.07045  -0.0408   1.0000   0.0957
  -5.750  -0.3479   0.06920   0.06463  -0.0360   1.0000   0.0975
  -5.500  -0.3464   0.06662   0.06214  -0.0328   1.0000   0.1001
  -5.250  -0.3476   0.06473   0.06029  -0.0307   1.0000   0.1032
  -5.000  -0.3416   0.06565   0.06075  -0.0344   1.0000   0.1106
  -4.750  -0.3444   0.06129   0.05662  -0.0312   1.0000   0.1118
  -4.500  -0.3326   0.05797   0.05339  -0.0305   0.9975   0.1149
  -4.250  -0.2865   0.05396   0.04906  -0.0385   0.9894   0.1274
  -4.000  -0.2447   0.05033   0.04522  -0.0443   0.9825   0.1421
  -3.750  -0.2062   0.04700   0.04171  -0.0490   0.9736   0.1570
  -3.500  -0.1674   0.04370   0.03828  -0.0532   0.9657   0.1726
  -3.250  -0.1282   0.04061   0.03509  -0.0571   0.9581   0.1905
  -3.000  -0.0899   0.03798   0.03229  -0.0609   0.9494   0.2178
  -2.750  -0.0509   0.03534   0.02958  -0.0644   0.9428   0.2613
  -2.250   0.0300   0.01333   0.00798  -0.0666   0.8970   0.3751
  -2.000   0.1009   0.02616   0.01799  -0.0740   0.9170   0.1087
  -1.750   0.1392   0.02394   0.01546  -0.0755   0.9084   0.1010
  -1.500   0.1743   0.02259   0.01379  -0.0762   0.8982   0.1004
  -1.250   0.2050   0.02157   0.01253  -0.0762   0.8863   0.1008
  -1.000   0.2356   0.02059   0.01134  -0.0759   0.8750   0.0993
  -0.750   0.2653   0.01975   0.01039  -0.0755   0.8645   0.0998
  -0.500   0.2928   0.01906   0.00967  -0.0747   0.8532   0.1018
  -0.250   0.3183   0.01855   0.00914  -0.0738   0.8407   0.1053
   0.000   0.3436   0.01815   0.00869  -0.0727   0.8289   0.1105
   0.250   0.3688   0.01773   0.00832  -0.0716   0.8177   0.1242
   0.500   0.3951   0.01723   0.00792  -0.0706   0.8078   0.1576
   0.750   0.4447   0.01490   0.00747  -0.0743   0.7964   1.0000
   1.000   0.4688   0.01510   0.00748  -0.0732   0.7845   1.0000
   1.250   0.4933   0.01529   0.00750  -0.0722   0.7735   1.0000
   1.500   0.5180   0.01543   0.00749  -0.0711   0.7635   1.0000
   1.750   0.5424   0.01569   0.00765  -0.0704   0.7514   1.0000
   2.000   0.5670   0.01594   0.00783  -0.0696   0.7399   1.0000
   2.250   0.5919   0.01617   0.00797  -0.0688   0.7294   1.0000
   2.500   0.6172   0.01635   0.00808  -0.0679   0.7197   1.0000
   2.750   0.6419   0.01665   0.00836  -0.0673   0.7078   1.0000
   3.000   0.6669   0.01695   0.00863  -0.0667   0.6967   1.0000
   3.250   0.6923   0.01719   0.00882  -0.0660   0.6868   1.0000
   3.500   0.7177   0.01743   0.00907  -0.0653   0.6763   1.0000
   3.750   0.7426   0.01777   0.00945  -0.0648   0.6646   1.0000
   4.000   0.7678   0.01809   0.00979  -0.0642   0.6538   1.0000
   4.250   0.7939   0.01831   0.00998  -0.0635   0.6445   1.0000
   4.500   0.8189   0.01865   0.01041  -0.0630   0.6329   1.0000
   4.750   0.8437   0.01904   0.01088  -0.0625   0.6214   1.0000
   5.000   0.8691   0.01939   0.01129  -0.0619   0.6108   1.0000
   5.250   0.8957   0.01960   0.01153  -0.0613   0.6015   1.0000
   5.500   0.9201   0.02003   0.01210  -0.0607   0.5894   1.0000
   5.750   0.9448   0.02039   0.01259  -0.0601   0.5772   1.0000
   6.000   0.9697   0.02061   0.01290  -0.0593   0.5641   1.0000
   6.250   0.9947   0.02068   0.01308  -0.0583   0.5495   1.0000
   6.500   1.0199   0.02006   0.01237  -0.0565   0.5275   1.0000
   6.750   1.0407   0.01931   0.01161  -0.0542   0.4925   1.0000
   7.000   1.0619   0.01898   0.01131  -0.0524   0.4604   1.0000
   7.250   1.0815   0.01886   0.01129  -0.0505   0.4199   1.0000
   7.500   1.0923   0.01936   0.01140  -0.0472   0.3122   1.0000
   7.750   1.0793   0.02346   0.01375  -0.0425   0.1024   1.0000
   8.000   1.0855   0.02566   0.01577  -0.0396   0.0799   1.0000
   8.250   1.0949   0.02734   0.01752  -0.0371   0.0713   1.0000
   8.500   1.1005   0.02925   0.01939  -0.0343   0.0657   1.0000
   8.750   1.1121   0.03075   0.02098  -0.0321   0.0606   1.0000
   9.000   1.1250   0.03253   0.02270  -0.0301   0.0574   1.0000
   9.250   1.1511   0.03531   0.02531  -0.0295   0.0546   1.0000
   9.500   1.1766   0.03725   0.02746  -0.0288   0.0530   1.0000
   9.750   1.1992   0.03931   0.02974  -0.0279   0.0504   1.0000
  10.000   1.2222   0.04180   0.03243  -0.0271   0.0486   1.0000
  10.250   1.2432   0.04483   0.03577  -0.0261   0.0483   1.0000
  10.500   1.2584   0.04816   0.03955  -0.0246   0.0487   1.0000
  10.750   1.2675   0.05181   0.04365  -0.0225   0.0496   1.0000
  11.000   1.2721   0.05577   0.04803  -0.0203   0.0508   1.0000
  11.250   1.2723   0.05979   0.05243  -0.0181   0.0518   1.0000
  11.500   1.2679   0.06380   0.05676  -0.0158   0.0525   1.0000
  11.750   1.2590   0.06771   0.06095  -0.0133   0.0530   1.0000
  12.000   1.2470   0.07177   0.06522  -0.0110   0.0535   1.0000
  12.250   1.2375   0.07680   0.07044  -0.0096   0.0542   1.0000
  12.500   1.2356   0.08016   0.07401  -0.0083   0.0556   1.0000
  12.750   1.1713   0.08428   0.07869  -0.0085   0.0581   1.0000
  13.000   1.1289   0.09215   0.08687  -0.0121   0.0606   1.0000
  13.250   1.0971   0.10008   0.09498  -0.0163   0.0620   1.0000
  13.500   1.0665   0.10890   0.10389  -0.0216   0.0632   1.0000
  13.750   0.9319   0.10082   0.09591  -0.0052   0.0575   1.0000
  14.000   0.8793   0.10969   0.10493  -0.0108   0.0580   1.0000
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