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M6 (85%) (m685-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: M6 (85%) (m685-il)
Reynolds number: 100,000
Max Cl/Cd: 49.51 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m685-il-100000-n5.txt
Download as CSV file: xf-m685-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: M6 (85%)                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4942   0.11975   0.11426  -0.0128   1.0000   0.0381
 -11.000  -0.4902   0.11598   0.11050  -0.0136   1.0000   0.0366
 -10.500  -0.5094   0.10228   0.09690  -0.0215   1.0000   0.0319
 -10.250  -0.5101   0.09795   0.09260  -0.0231   1.0000   0.0317
 -10.000  -0.5130   0.09323   0.08792  -0.0252   1.0000   0.0317
  -9.750  -0.5142   0.08913   0.08387  -0.0269   1.0000   0.0314
  -9.500  -0.5237   0.08317   0.07797  -0.0308   1.0000   0.0314
  -9.250  -0.5377   0.07677   0.07160  -0.0355   1.0000   0.0315
  -9.000  -0.5492   0.07232   0.06715  -0.0367   1.0000   0.0312
  -8.750  -0.5678   0.06761   0.06240  -0.0362   1.0000   0.0312
  -8.500  -0.5824   0.06302   0.05771  -0.0350   1.0000   0.0311
  -8.250  -0.5960   0.05819   0.05272  -0.0332   1.0000   0.0312
  -7.750  -0.6004   0.05254   0.04683  -0.0288   1.0000   0.0335
  -7.500  -0.5986   0.05004   0.04418  -0.0264   1.0000   0.0345
  -7.250  -0.5973   0.04735   0.04129  -0.0236   1.0000   0.0363
  -7.000  -0.6003   0.04367   0.03722  -0.0199   1.0000   0.0378
  -6.750  -0.5995   0.04038   0.03354  -0.0163   1.0000   0.0381
  -6.500  -0.5962   0.03742   0.03020  -0.0126   1.0000   0.0382
  -6.250  -0.5906   0.03486   0.02727  -0.0091   1.0000   0.0383
  -6.000  -0.5833   0.03259   0.02463  -0.0057   1.0000   0.0386
  -5.750  -0.5746   0.03063   0.02230  -0.0024   1.0000   0.0389
  -5.500  -0.5487   0.02842   0.01958  -0.0024   0.9942   0.0394
  -5.250  -0.5146   0.02637   0.01732  -0.0042   0.9857   0.0404
  -5.000  -0.4798   0.02484   0.01562  -0.0059   0.9763   0.0417
  -4.750  -0.4448   0.02355   0.01414  -0.0075   0.9665   0.0437
  -4.500  -0.4088   0.02235   0.01274  -0.0092   0.9569   0.0467
  -4.250  -0.3711   0.02115   0.01143  -0.0113   0.9485   0.0496
  -4.000  -0.3368   0.02030   0.01057  -0.0128   0.9369   0.0534
  -3.750  -0.3017   0.01949   0.00967  -0.0142   0.9257   0.0588
  -3.500  -0.2660   0.01871   0.00891  -0.0159   0.9151   0.0645
  -3.250  -0.2333   0.01795   0.00809  -0.0168   0.9024   0.0711
  -3.000  -0.2019   0.01732   0.00742  -0.0174   0.8890   0.0808
  -2.750  -0.1718   0.01666   0.00679  -0.0177   0.8755   0.0959
  -2.500  -0.1425   0.01604   0.00634  -0.0180   0.8620   0.1288
  -2.250  -0.1138   0.01545   0.00593  -0.0181   0.8488   0.1839
  -2.000  -0.0235   0.01302   0.00621  -0.0300   0.8455   0.8247
  -1.750   0.0272   0.01367   0.00667  -0.0328   0.8337   0.9092
  -1.500   0.0880   0.01420   0.00694  -0.0383   0.8217   0.9447
  -1.250   0.1509   0.01445   0.00696  -0.0448   0.8082   0.9714
  -1.000   0.2257   0.01424   0.00652  -0.0544   0.7946   0.9950
  -0.750   0.2623   0.01406   0.00619  -0.0563   0.7795   1.0000
  -0.500   0.2855   0.01404   0.00605  -0.0555   0.7649   1.0000
  -0.250   0.3087   0.01404   0.00593  -0.0547   0.7511   1.0000
   0.000   0.3315   0.01405   0.00582  -0.0538   0.7381   1.0000
   0.250   0.3542   0.01407   0.00575  -0.0528   0.7255   1.0000
   0.500   0.3767   0.01411   0.00572  -0.0518   0.7126   1.0000
   0.750   0.3991   0.01415   0.00570  -0.0508   0.7007   1.0000
   1.000   0.4216   0.01420   0.00568  -0.0498   0.6895   1.0000
   1.250   0.4440   0.01427   0.00570  -0.0487   0.6780   1.0000
   1.500   0.4663   0.01434   0.00574  -0.0477   0.6664   1.0000
   1.750   0.4887   0.01442   0.00579  -0.0466   0.6554   1.0000
   2.000   0.5112   0.01450   0.00583  -0.0455   0.6448   1.0000
   2.250   0.5334   0.01460   0.00594  -0.0444   0.6330   1.0000
   2.500   0.5557   0.01470   0.00604  -0.0433   0.6215   1.0000
   2.750   0.5779   0.01480   0.00612  -0.0422   0.6096   1.0000
   3.000   0.5999   0.01490   0.00620  -0.0409   0.5970   1.0000
   3.250   0.6217   0.01501   0.00635  -0.0397   0.5832   1.0000
   3.500   0.6435   0.01513   0.00649  -0.0385   0.5695   1.0000
   3.750   0.6654   0.01526   0.00664  -0.0373   0.5562   1.0000
   4.000   0.6872   0.01540   0.00683  -0.0360   0.5432   1.0000
   4.250   0.7090   0.01556   0.00701  -0.0348   0.5306   1.0000
   4.500   0.7305   0.01572   0.00721  -0.0335   0.5166   1.0000
   4.750   0.7516   0.01589   0.00743  -0.0321   0.5006   1.0000
   5.000   0.7720   0.01606   0.00765  -0.0306   0.4809   1.0000
   5.250   0.7918   0.01625   0.00785  -0.0290   0.4591   1.0000
   5.500   0.8110   0.01647   0.00808  -0.0272   0.4341   1.0000
   5.750   0.8293   0.01675   0.00832  -0.0254   0.4052   1.0000
   6.000   0.8466   0.01710   0.00859  -0.0234   0.3694   1.0000
   6.250   0.8625   0.01758   0.00894  -0.0213   0.3283   1.0000
   6.500   0.8773   0.01819   0.00937  -0.0191   0.2813   1.0000
   6.750   0.8896   0.01902   0.00994  -0.0167   0.2278   1.0000
   7.000   0.9000   0.02008   0.01069  -0.0141   0.1721   1.0000
   7.250   0.9089   0.02131   0.01159  -0.0113   0.1191   1.0000
   7.500   0.9172   0.02256   0.01261  -0.0085   0.0890   1.0000
   7.750   0.9258   0.02375   0.01370  -0.0056   0.0734   1.0000
   8.000   0.9351   0.02483   0.01479  -0.0028   0.0626   1.0000
   8.250   0.9440   0.02588   0.01589   0.0000   0.0559   1.0000
   8.500   0.9524   0.02691   0.01695   0.0028   0.0512   1.0000
   8.750   0.9587   0.02804   0.01813   0.0059   0.0480   1.0000
   9.000   0.9659   0.02911   0.01929   0.0088   0.0452   1.0000
   9.250   0.9720   0.03019   0.02041   0.0118   0.0424   1.0000
   9.750   0.9767   0.03254   0.02286   0.0186   0.0391   1.0000
  10.000   0.9820   0.03374   0.02416   0.0214   0.0377   1.0000
  10.250   0.9884   0.03503   0.02554   0.0238   0.0366   1.0000
  10.500   0.9955   0.03643   0.02702   0.0260   0.0355   1.0000
  10.750   1.0033   0.03789   0.02856   0.0280   0.0345   1.0000
  11.000   1.0124   0.03941   0.03015   0.0297   0.0339   1.0000
  11.250   1.0216   0.04105   0.03184   0.0312   0.0331   1.0000
  11.500   1.0331   0.04291   0.03374   0.0325   0.0325   1.0000
  11.750   1.0429   0.04489   0.03588   0.0339   0.0320   1.0000
  12.000   1.0501   0.04695   0.03817   0.0354   0.0317   1.0000
  12.250   1.0540   0.04926   0.04074   0.0368   0.0314   1.0000
  12.500   1.0555   0.05176   0.04346   0.0380   0.0311   1.0000
  12.750   1.0535   0.05454   0.04649   0.0391   0.0309   1.0000
  13.000   1.0481   0.05762   0.04982   0.0399   0.0307   1.0000
  13.250   1.0399   0.06100   0.05344   0.0402   0.0305   1.0000
  13.500   1.0292   0.06480   0.05747   0.0401   0.0305   1.0000
  13.750   1.0156   0.06906   0.06196   0.0394   0.0303   1.0000
  14.000   0.9992   0.07391   0.06704   0.0380   0.0303   1.0000
  14.250   0.9801   0.07942   0.07277   0.0359   0.0302   1.0000
  14.500   0.9585   0.08572   0.07928   0.0329   0.0303   1.0000
  14.750   0.9346   0.09294   0.08669   0.0291   0.0306   1.0000
  15.000   0.9065   0.10164   0.09557   0.0241   0.0308   1.0000
  15.250   0.8744   0.11230   0.10636   0.0176   0.0312   1.0000
  15.500   0.8417   0.12446   0.11862   0.0105   0.0317   1.0000
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