Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

M6 (85%) (m685-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: M6 (85%) (m685-il)
Reynolds number: 50,000
Max Cl/Cd: 33.18 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m685-il-50000.txt
Download as CSV file: xf-m685-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4839   0.12284   0.11553  -0.0063   1.0000   0.2201
 -10.000  -0.4641   0.11768   0.11036  -0.0052   1.0000   0.2308
  -9.750  -0.4894   0.11723   0.11005  -0.0078   1.0000   0.2368
  -9.500  -0.4651   0.11182   0.10462  -0.0062   1.0000   0.2506
  -9.250  -0.4559   0.10773   0.10056  -0.0059   1.0000   0.2600
  -9.000  -0.4847   0.10725   0.10025  -0.0079   1.0000   0.2692
  -8.750  -0.4635   0.10244   0.09542  -0.0064   1.0000   0.2840
  -8.500  -0.4498   0.09838   0.09136  -0.0055   1.0000   0.2972
  -8.250  -0.4449   0.09504   0.08807  -0.0048   1.0000   0.3113
  -8.000  -0.4428   0.09201   0.08511  -0.0040   1.0000   0.3285
  -7.750  -0.4478   0.08953   0.08272  -0.0030   1.0000   0.3478
  -7.500  -0.4339   0.08597   0.07919  -0.0010   1.0000   0.3720
  -7.250  -0.4441   0.08418   0.07751   0.0011   1.0000   0.3977
  -7.000  -0.4358   0.08142   0.07480   0.0040   1.0000   0.4304
  -6.750  -0.4094   0.07770   0.07105   0.0066   1.0000   0.4667
  -6.500  -0.3889   0.07487   0.06823   0.0100   1.0000   0.5147
  -5.250  -0.5229   0.04971   0.04221  -0.0079   1.0000   0.1813
  -5.000  -0.5242   0.04617   0.03777  -0.0042   1.0000   0.1577
  -4.750  -0.5138   0.04327   0.03479  -0.0018   1.0000   0.1535
  -4.500  -0.5064   0.04082   0.03209   0.0012   1.0000   0.1507
  -4.250  -0.4983   0.03864   0.02956   0.0042   1.0000   0.1493
  -4.000  -0.4885   0.03667   0.02725   0.0070   1.0000   0.1489
  -3.750  -0.4765   0.03486   0.02510   0.0095   1.0000   0.1494
  -3.500  -0.4629   0.03330   0.02319   0.0118   1.0000   0.1518
  -3.250  -0.4474   0.03188   0.02138   0.0139   1.0000   0.1548
  -3.000  -0.4297   0.03058   0.01965   0.0158   1.0000   0.1572
  -2.750  -0.0689   0.02009   0.01201  -0.0350   1.0000   1.0000
  -2.500  -0.0665   0.02028   0.01195  -0.0315   1.0000   1.0000
  -2.250  -0.0694   0.02060   0.01209  -0.0273   1.0000   1.0000
  -2.000  -0.0736   0.02100   0.01233  -0.0231   1.0000   1.0000
  -1.750  -0.0764   0.02142   0.01259  -0.0193   1.0000   1.0000
  -1.500  -0.0770   0.02185   0.01284  -0.0158   1.0000   1.0000
  -1.250  -0.0756   0.02227   0.01309  -0.0127   1.0000   1.0000
  -1.000  -0.0724   0.02272   0.01337  -0.0099   1.0000   1.0000
  -0.750  -0.0676   0.02318   0.01367  -0.0074   1.0000   1.0000
  -0.500  -0.0616   0.02366   0.01399  -0.0051   1.0000   1.0000
  -0.250  -0.0117   0.02438   0.01449  -0.0112   0.9872   1.0000
   0.000   0.0411   0.02508   0.01500  -0.0175   0.9727   1.0000
   0.250   0.0884   0.02568   0.01547  -0.0226   0.9575   1.0000
   0.500   0.1341   0.02627   0.01594  -0.0272   0.9427   1.0000
   0.750   0.1795   0.02683   0.01642  -0.0316   0.9281   1.0000
   1.000   0.2257   0.02735   0.01689  -0.0360   0.9139   1.0000
   1.250   0.2757   0.02782   0.01733  -0.0408   0.9002   1.0000
   1.500   0.3158   0.02829   0.01781  -0.0438   0.8854   1.0000
   1.750   0.3533   0.02878   0.01831  -0.0461   0.8706   1.0000
   2.000   0.3895   0.02929   0.01885  -0.0482   0.8560   1.0000
   2.250   0.4240   0.02980   0.01941  -0.0498   0.8412   1.0000
   2.500   0.4549   0.03034   0.02001  -0.0506   0.8263   1.0000
   2.750   0.4835   0.03091   0.02064  -0.0510   0.8114   1.0000
   3.000   0.5111   0.03148   0.02128  -0.0511   0.7963   1.0000
   3.250   0.5382   0.03203   0.02191  -0.0509   0.7808   1.0000
   3.500   0.5642   0.03256   0.02253  -0.0503   0.7651   1.0000
   3.750   0.5893   0.03307   0.02315  -0.0495   0.7490   1.0000
   4.000   0.6130   0.03361   0.02378  -0.0483   0.7328   1.0000
   4.250   0.6360   0.03413   0.02440  -0.0470   0.7163   1.0000
   4.500   0.6587   0.03462   0.02503  -0.0454   0.6996   1.0000
   4.750   0.6810   0.03510   0.02563  -0.0437   0.6828   1.0000
   5.000   0.7040   0.03549   0.02614  -0.0420   0.6657   1.0000
   5.250   0.7272   0.03582   0.02663  -0.0401   0.6485   1.0000
   5.500   0.7520   0.03598   0.02695  -0.0381   0.6311   1.0000
   5.750   0.7807   0.03580   0.02693  -0.0362   0.6132   1.0000
   6.000   0.7942   0.03630   0.02758  -0.0330   0.5909   1.0000
   6.250   0.8357   0.03385   0.02524  -0.0300   0.5633   1.0000
   6.500   0.8670   0.03191   0.02338  -0.0264   0.5327   1.0000
   6.750   0.8899   0.03069   0.02223  -0.0227   0.4998   1.0000
   7.000   0.9111   0.02908   0.02059  -0.0185   0.4582   1.0000
   7.250   0.9241   0.02795   0.01932  -0.0135   0.4049   1.0000
   7.500   0.9255   0.02789   0.01879  -0.0074   0.3300   1.0000
   7.750   0.9199   0.02953   0.01964  -0.0015   0.2531   1.0000
   8.000   0.9220   0.03169   0.02129   0.0026   0.2036   1.0000
   8.250   0.9335   0.03381   0.02312   0.0053   0.1732   1.0000
   8.500   0.9541   0.03598   0.02500   0.0067   0.1531   1.0000
   8.750   0.9743   0.03811   0.02713   0.0080   0.1391   1.0000
   9.000   0.9940   0.04061   0.02990   0.0095   0.1307   1.0000
   9.250   1.0161   0.04323   0.03247   0.0103   0.1232   1.0000
   9.500   1.0245   0.04579   0.03551   0.0129   0.1187   1.0000
   9.750   1.0362   0.04857   0.03858   0.0148   0.1154   1.0000
  10.000   1.0473   0.05168   0.04193   0.0166   0.1136   1.0000
  10.250   1.0549   0.05503   0.04552   0.0186   0.1124   1.0000
  10.500   1.0607   0.05881   0.04949   0.0204   0.1112   1.0000
  10.750   1.0544   0.06249   0.05346   0.0232   0.1107   1.0000
  11.000   1.0464   0.06621   0.05746   0.0258   0.1108   1.0000
  11.250   1.0319   0.06992   0.06142   0.0285   0.1109   1.0000
  11.500   0.9358   0.07466   0.06670   0.0336   0.1169   1.0000
  11.750   0.8931   0.08138   0.07355   0.0319   0.1193   1.0000
  12.000   0.8585   0.08912   0.08131   0.0285   0.1217   1.0000
  12.250   0.8389   0.09644   0.08864   0.0256   0.1234   1.0000
<< Back to M6 (85%) (m685-il)

Polar data table (+)

Polar graphs


<< Back to M6 (85%) (m685-il)