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M6 (85%) (m685-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: M6 (85%) (m685-il)
Reynolds number: 100,000
Max Cl/Cd: 50.6 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m685-il-100000.txt
Download as CSV file: xf-m685-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4722   0.10212   0.09697  -0.0179   1.0000   0.1075
  -9.250  -0.4967   0.09875   0.09371  -0.0244   1.0000   0.1103
  -9.000  -0.5237   0.09510   0.09016  -0.0297   1.0000   0.1107
  -8.750  -0.4748   0.09106   0.08607  -0.0214   1.0000   0.1177
  -8.500  -0.4822   0.08746   0.08253  -0.0238   1.0000   0.1218
  -8.250  -0.5044   0.08376   0.07890  -0.0270   1.0000   0.1237
  -8.000  -0.5479   0.08179   0.07685  -0.0283   1.0000   0.1254
  -7.750  -0.5097   0.07680   0.07204  -0.0251   1.0000   0.1320
  -7.500  -0.5176   0.07381   0.06905  -0.0249   1.0000   0.1370
  -7.250  -0.5572   0.07288   0.06778  -0.0244   1.0000   0.1410
  -7.000  -0.5241   0.06735   0.06259  -0.0226   1.0000   0.1484
  -6.750  -0.5592   0.06768   0.06245  -0.0200   1.0000   0.1572
  -6.500  -0.5289   0.06153   0.05672  -0.0190   1.0000   0.1637
  -6.250  -0.5442   0.05966   0.05461  -0.0164   1.0000   0.1746
  -6.000  -0.5289   0.05628   0.05140  -0.0143   1.0000   0.1802
  -5.500  -0.5300   0.05175   0.04679  -0.0081   1.0000   0.1976
  -5.250  -0.5365   0.04990   0.04487  -0.0042   1.0000   0.2091
  -5.000  -0.5446   0.04879   0.04364   0.0002   1.0000   0.2229
  -4.750  -0.5415   0.04036   0.03399   0.0034   1.0000   0.1288
  -4.500  -0.5343   0.03391   0.02655   0.0083   1.0000   0.0884
  -4.250  -0.5261   0.03217   0.02392   0.0128   1.0000   0.0822
  -4.000  -0.4919   0.02926   0.02067   0.0111   0.9943   0.0813
  -3.750  -0.4492   0.02729   0.01821   0.0083   0.9859   0.0824
  -3.500  -0.4083   0.02500   0.01579   0.0053   0.9779   0.0863
  -3.250  -0.3644   0.02364   0.01427   0.0021   0.9693   0.0916
  -3.000  -0.3167   0.02228   0.01282  -0.0018   0.9623   0.1011
  -2.750  -0.2750   0.02135   0.01174  -0.0043   0.9521   0.1108
  -2.500  -0.2319   0.02021   0.01073  -0.0073   0.9435   0.1263
  -2.250  -0.1895   0.01893   0.00970  -0.0101   0.9352   0.1571
  -2.000   0.0214   0.01655   0.01029  -0.0408   0.9763   1.0000
  -1.750   0.0769   0.01629   0.00978  -0.0468   0.9640   1.0000
  -1.500   0.1316   0.01597   0.00926  -0.0526   0.9520   1.0000
  -1.250   0.1832   0.01566   0.00879  -0.0576   0.9388   1.0000
  -1.000   0.2314   0.01536   0.00835  -0.0619   0.9242   1.0000
  -0.750   0.2745   0.01512   0.00799  -0.0650   0.9084   1.0000
  -0.500   0.3106   0.01498   0.00774  -0.0667   0.8912   1.0000
  -0.250   0.3407   0.01493   0.00759  -0.0671   0.8738   1.0000
   0.000   0.3663   0.01496   0.00752  -0.0666   0.8567   1.0000
   0.250   0.3892   0.01504   0.00752  -0.0655   0.8405   1.0000
   0.500   0.4107   0.01515   0.00756  -0.0641   0.8247   1.0000
   0.750   0.4317   0.01529   0.00764  -0.0627   0.8097   1.0000
   1.000   0.4525   0.01544   0.00774  -0.0612   0.7951   1.0000
   1.250   0.4734   0.01560   0.00787  -0.0597   0.7813   1.0000
   1.500   0.4944   0.01577   0.00799  -0.0582   0.7680   1.0000
   1.750   0.5160   0.01592   0.00809  -0.0568   0.7553   1.0000
   2.000   0.5371   0.01608   0.00823  -0.0553   0.7420   1.0000
   2.250   0.5577   0.01628   0.00844  -0.0538   0.7282   1.0000
   2.500   0.5785   0.01646   0.00862  -0.0523   0.7143   1.0000
   2.750   0.5995   0.01662   0.00878  -0.0507   0.7005   1.0000
   3.000   0.6207   0.01677   0.00892  -0.0492   0.6867   1.0000
   3.250   0.6423   0.01690   0.00905  -0.0476   0.6732   1.0000
   3.500   0.6645   0.01702   0.00914  -0.0461   0.6603   1.0000
   3.750   0.6853   0.01721   0.00936  -0.0446   0.6458   1.0000
   4.000   0.7062   0.01741   0.00963  -0.0430   0.6315   1.0000
   4.250   0.7272   0.01762   0.00989  -0.0416   0.6175   1.0000
   4.500   0.7483   0.01778   0.01009  -0.0399   0.6026   1.0000
   4.750   0.7694   0.01787   0.01023  -0.0382   0.5865   1.0000
   5.000   0.7904   0.01787   0.01023  -0.0364   0.5686   1.0000
   5.250   0.8117   0.01782   0.01016  -0.0345   0.5498   1.0000
   5.500   0.8306   0.01783   0.01024  -0.0324   0.5279   1.0000
   5.750   0.8501   0.01775   0.01015  -0.0303   0.5046   1.0000
   6.000   0.8678   0.01772   0.01014  -0.0279   0.4776   1.0000
   6.250   0.8850   0.01774   0.01018  -0.0255   0.4483   1.0000
   6.500   0.9011   0.01785   0.01029  -0.0230   0.4149   1.0000
   6.750   0.9153   0.01809   0.01048  -0.0202   0.3727   1.0000
   7.000   0.9252   0.01865   0.01082  -0.0169   0.3082   1.0000
   7.250   0.9232   0.02030   0.01174  -0.0122   0.1994   1.0000
   7.500   0.9198   0.02249   0.01328  -0.0075   0.1328   1.0000
   7.750   0.9227   0.02417   0.01467  -0.0036   0.1087   1.0000
   8.000   0.9285   0.02568   0.01607  -0.0001   0.0941   1.0000
   8.250   0.9372   0.02719   0.01744   0.0028   0.0858   1.0000
   8.500   0.9520   0.02864   0.01894   0.0051   0.0795   1.0000
   8.750   0.9684   0.03014   0.02035   0.0067   0.0741   1.0000
   9.000   0.9899   0.03210   0.02232   0.0077   0.0699   1.0000
   9.250   1.0099   0.03374   0.02413   0.0090   0.0670   1.0000
   9.500   1.0308   0.03563   0.02618   0.0101   0.0649   1.0000
   9.750   1.0504   0.03768   0.02838   0.0113   0.0636   1.0000
  10.000   1.0680   0.03992   0.03080   0.0126   0.0626   1.0000
  10.250   1.0827   0.04234   0.03346   0.0142   0.0621   1.0000
  10.500   1.0937   0.04498   0.03639   0.0163   0.0619   1.0000
  10.750   1.1000   0.04778   0.03951   0.0188   0.0620   1.0000
  11.000   1.0977   0.05061   0.04276   0.0222   0.0627   1.0000
  11.250   1.0866   0.05369   0.04626   0.0262   0.0634   1.0000
  11.500   1.0707   0.05688   0.04982   0.0302   0.0643   1.0000
  11.750   1.0494   0.05980   0.05299   0.0346   0.0648   1.0000
  12.000   1.0257   0.06313   0.05657   0.0377   0.0656   1.0000
  12.250   1.0005   0.06701   0.06067   0.0393   0.0661   1.0000
  12.500   0.9738   0.07177   0.06563   0.0394   0.0673   1.0000
  12.750   0.9458   0.07727   0.07130   0.0382   0.0682   1.0000
  13.000   0.9169   0.08368   0.07784   0.0357   0.0691   1.0000
  13.250   0.8900   0.09083   0.08508   0.0324   0.0700   1.0000
  13.500   0.8857   0.09668   0.09093   0.0315   0.0714   1.0000
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