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NACA M17 AIRFOIL (m17-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M17 AIRFOIL (m17-il)
Reynolds number: 200,000
Max Cl/Cd: 74.21 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m17-il-200000-n5.txt
Download as CSV file: xf-m17-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M17 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4614   0.10770   0.10453   0.0076   1.0000   0.0189
  -8.750  -0.4569   0.10392   0.10078   0.0057   1.0000   0.0188
  -8.500  -0.4549   0.09981   0.09671   0.0019   1.0000   0.0193
  -7.250  -0.4270   0.08273   0.07949  -0.0088   0.8536   0.0227
  -7.000  -0.4197   0.07793   0.07459  -0.0125   0.8357   0.0218
  -6.750  -0.4091   0.07354   0.07009  -0.0157   0.8205   0.0217
  -6.500  -0.3954   0.07036   0.06679  -0.0177   0.8063   0.0228
  -6.250  -0.3792   0.06669   0.06299  -0.0204   0.7934   0.0247
  -6.000  -0.3619   0.06235   0.05846  -0.0232   0.7819   0.0252
  -5.750  -0.3434   0.05793   0.05386  -0.0255   0.7714   0.0253
  -5.500  -0.3223   0.05334   0.04903  -0.0277   0.7614   0.0260
  -5.250  -0.3004   0.04878   0.04422  -0.0297   0.7517   0.0292
  -5.000  -0.2819   0.04764   0.04300  -0.0295   0.7415   0.0312
  -4.750  -0.2591   0.04361   0.03869  -0.0304   0.7327   0.0311
  -4.500  -0.2358   0.04037   0.03520  -0.0309   0.7238   0.0318
  -4.000  -0.1870   0.03442   0.02864  -0.0312   0.7073   0.0348
  -3.750  -0.1621   0.03114   0.02497  -0.0309   0.7000   0.0350
  -3.500  -0.1362   0.02825   0.02169  -0.0306   0.6921   0.0363
  -3.250  -0.1103   0.02569   0.01868  -0.0300   0.6852   0.0371
  -3.000  -0.0841   0.02339   0.01599  -0.0296   0.6776   0.0372
  -2.750  -0.0577   0.02161   0.01379  -0.0292   0.6710   0.0375
  -2.500  -0.0304   0.02020   0.01205  -0.0289   0.6634   0.0379
  -2.250  -0.0031   0.01921   0.01076  -0.0286   0.6570   0.0384
  -2.000   0.0246   0.01834   0.00964  -0.0285   0.6498   0.0394
  -1.750   0.0520   0.01729   0.00834  -0.0283   0.6433   0.0397
  -1.500   0.0798   0.01650   0.00739  -0.0282   0.6368   0.0396
  -1.250   0.1074   0.01577   0.00653  -0.0280   0.6304   0.0398
  -1.000   0.1348   0.01511   0.00575  -0.0279   0.6245   0.0401
  -0.750   0.1622   0.01453   0.00511  -0.0277   0.6179   0.0407
  -0.500   0.1891   0.01408   0.00460  -0.0275   0.6124   0.0415
  -0.250   0.2164   0.01371   0.00422  -0.0274   0.6061   0.0426
   0.000   0.2435   0.01343   0.00392  -0.0272   0.6002   0.0440
   0.250   0.2707   0.01322   0.00367  -0.0270   0.5945   0.0455
   0.500   0.2981   0.01305   0.00348  -0.0270   0.5884   0.0473
   0.750   0.3254   0.01294   0.00332  -0.0268   0.5833   0.0505
   1.000   0.3529   0.01281   0.00321  -0.0268   0.5773   0.0554
   1.250   0.3803   0.01271   0.00312  -0.0267   0.5715   0.0617
   1.500   0.4074   0.01259   0.00306  -0.0266   0.5666   0.0878
   1.750   0.4340   0.01233   0.00310  -0.0265   0.5607   0.1887
   2.250   0.5396   0.01078   0.00338  -0.0373   0.5483   1.0000
   2.500   0.5658   0.01087   0.00344  -0.0370   0.5428   1.0000
   2.750   0.5917   0.01098   0.00347  -0.0366   0.5380   1.0000
   3.000   0.6179   0.01108   0.00358  -0.0364   0.5319   1.0000
   3.250   0.6439   0.01119   0.00367  -0.0360   0.5265   1.0000
   3.500   0.6699   0.01131   0.00379  -0.0357   0.5213   1.0000
   3.750   0.6959   0.01143   0.00393  -0.0354   0.5152   1.0000
   4.000   0.7217   0.01156   0.00403  -0.0351   0.5091   1.0000
   4.250   0.7475   0.01166   0.00418  -0.0348   0.4995   1.0000
   4.500   0.7731   0.01177   0.00430  -0.0344   0.4892   1.0000
   4.750   0.7987   0.01190   0.00442  -0.0340   0.4805   1.0000
   5.000   0.8245   0.01204   0.00466  -0.0337   0.4729   1.0000
   5.250   0.8501   0.01221   0.00485  -0.0334   0.4663   1.0000
   5.500   0.8759   0.01237   0.00511  -0.0331   0.4589   1.0000
   5.750   0.9013   0.01255   0.00533  -0.0327   0.4511   1.0000
   6.000   0.9265   0.01271   0.00557  -0.0323   0.4374   1.0000
   6.250   0.9513   0.01289   0.00579  -0.0318   0.4183   1.0000
   6.500   0.9751   0.01314   0.00600  -0.0313   0.3851   1.0000
   6.750   0.9972   0.01362   0.00629  -0.0306   0.3337   1.0000
   7.000   1.0151   0.01472   0.00695  -0.0298   0.2454   1.0000
   7.250   1.0287   0.01644   0.00811  -0.0286   0.1530   1.0000
   7.500   1.0355   0.01888   0.00979  -0.0269   0.0413   1.0000
   7.750   1.0520   0.02004   0.01092  -0.0257   0.0282   1.0000
   8.000   1.0705   0.02089   0.01188  -0.0246   0.0236   1.0000
   8.250   1.0870   0.02191   0.01301  -0.0234   0.0208   1.0000
   8.500   1.0996   0.02324   0.01448  -0.0218   0.0190   1.0000
   8.750   1.1140   0.02428   0.01567  -0.0204   0.0179   1.0000
   9.000   1.1264   0.02541   0.01693  -0.0189   0.0166   1.0000
   9.250   1.1363   0.02667   0.01829  -0.0172   0.0154   1.0000
   9.500   1.1410   0.02810   0.01982  -0.0150   0.0148   1.0000
   9.750   1.1437   0.02977   0.02158  -0.0130   0.0143   1.0000
  10.000   1.1466   0.03169   0.02359  -0.0116   0.0138   1.0000
  10.250   1.1490   0.03385   0.02582  -0.0103   0.0133   1.0000
  10.500   1.1508   0.03618   0.02826  -0.0089   0.0129   1.0000
  10.750   1.1547   0.03846   0.03061  -0.0074   0.0124   1.0000
  11.000   1.1640   0.04015   0.03243  -0.0066   0.0120   1.0000
  11.250   1.1727   0.04194   0.03436  -0.0058   0.0114   1.0000
  11.500   1.1806   0.04388   0.03642  -0.0049   0.0109   1.0000
  11.750   1.1880   0.04595   0.03863  -0.0039   0.0105   1.0000
  12.000   1.1949   0.04815   0.04098  -0.0029   0.0102   1.0000
  12.250   1.2005   0.05052   0.04350  -0.0021   0.0100   1.0000
  12.500   1.2046   0.05309   0.04624  -0.0014   0.0098   1.0000
  12.750   1.2070   0.05587   0.04919  -0.0009   0.0096   1.0000
  13.000   1.2076   0.05889   0.05243  -0.0007   0.0094   1.0000
  13.250   1.2061   0.06218   0.05591  -0.0006   0.0093   1.0000
  13.500   1.2025   0.06576   0.05968  -0.0008   0.0092   1.0000
  13.750   1.1970   0.06965   0.06376  -0.0013   0.0091   1.0000
  14.000   1.1897   0.07382   0.06812  -0.0020   0.0091   1.0000
  14.250   1.1810   0.07825   0.07273  -0.0031   0.0090   1.0000
  14.500   1.1710   0.08299   0.07765  -0.0045   0.0089   1.0000
  14.750   1.1598   0.08813   0.08297  -0.0063   0.0088   1.0000
  15.000   1.1477   0.09369   0.08870  -0.0086   0.0088   1.0000
  15.250   1.1346   0.09969   0.09487  -0.0113   0.0087   1.0000
  15.500   1.1201   0.10624   0.10162  -0.0145   0.0087   1.0000
  15.750   1.1050   0.11332   0.10888  -0.0182   0.0087   1.0000
  16.000   1.0887   0.12113   0.11688  -0.0227   0.0088   1.0000
  16.250   1.0696   0.13024   0.12620  -0.0281   0.0089   1.0000
  16.500   1.0435   0.14222   0.13841  -0.0353   0.0091   1.0000
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