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RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il)
Reynolds number: 100,000
Max Cl/Cd: 46.81 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-amsoil1-il-100000-n5.txt
Download as CSV file: xf-amsoil1-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RUTAN CANARD 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5270   0.08543   0.07991  -0.0396   1.0000   0.0475
  -9.500  -0.5360   0.07857   0.07309  -0.0453   1.0000   0.0473
  -9.250  -0.5537   0.07162   0.06611  -0.0507   1.0000   0.0470
  -9.000  -0.5743   0.06563   0.06002  -0.0530   1.0000   0.0469
  -8.750  -0.5950   0.05979   0.05402  -0.0535   1.0000   0.0469
  -8.500  -0.6215   0.05473   0.04870  -0.0508   1.0000   0.0471
  -8.250  -0.6375   0.04957   0.04313  -0.0489   0.9968   0.0477
  -8.000  -0.6095   0.04857   0.04213  -0.0507   0.9910   0.0487
  -7.750  -0.5878   0.04523   0.03850  -0.0530   0.9844   0.0498
  -7.500  -0.5685   0.04099   0.03378  -0.0548   0.9773   0.0508
  -7.250  -0.5449   0.03692   0.02911  -0.0566   0.9719   0.0522
  -7.000  -0.5229   0.03339   0.02487  -0.0574   0.9647   0.0543
  -6.750  -0.4924   0.03215   0.02356  -0.0589   0.9599   0.0556
  -6.500  -0.4641   0.03059   0.02178  -0.0598   0.9544   0.0570
  -6.250  -0.4361   0.02890   0.01977  -0.0604   0.9483   0.0587
  -6.000  -0.4053   0.02717   0.01757  -0.0614   0.9438   0.0614
  -5.750  -0.3784   0.02633   0.01674  -0.0617   0.9374   0.0631
  -5.500  -0.3493   0.02535   0.01564  -0.0622   0.9318   0.0652
  -5.250  -0.3181   0.02428   0.01436  -0.0630   0.9276   0.0678
  -5.000  -0.2924   0.02347   0.01345  -0.0627   0.9207   0.0706
  -4.750  -0.2641   0.02283   0.01281  -0.0630   0.9152   0.0735
  -4.500  -0.2339   0.02207   0.01194  -0.0634   0.9110   0.0769
  -4.250  -0.2086   0.02146   0.01131  -0.0630   0.9041   0.0804
  -4.000  -0.1812   0.02096   0.01083  -0.0631   0.8985   0.0849
  -3.750  -0.1523   0.02040   0.01019  -0.0631   0.8942   0.0899
  -3.500  -0.1275   0.01995   0.00984  -0.0627   0.8878   0.0951
  -3.250  -0.1009   0.01956   0.00941  -0.0624   0.8820   0.1021
  -3.000  -0.0738   0.01912   0.00905  -0.0623   0.8774   0.1098
  -2.750  -0.0483   0.01878   0.00875  -0.0619   0.8716   0.1189
  -2.500  -0.0226   0.01852   0.00849  -0.0615   0.8655   0.1305
  -2.250   0.0041   0.01816   0.00822  -0.0612   0.8608   0.1447
  -2.000   0.0306   0.01785   0.00798  -0.0610   0.8562   0.1634
  -1.750   0.0551   0.01754   0.00784  -0.0606   0.8496   0.1902
  -1.500   0.0807   0.01704   0.00762  -0.0603   0.8445   0.2473
  -1.250   0.0951   0.01540   0.00777  -0.0575   0.8405   0.6571
  -1.000   0.1139   0.01547   0.00812  -0.0546   0.8342   0.7693
  -0.750   0.1353   0.01558   0.00829  -0.0523   0.8285   0.8232
  -0.500   0.1588   0.01565   0.00836  -0.0503   0.8242   0.8620
  -0.250   0.1837   0.01575   0.00846  -0.0489   0.8195   0.8944
   0.000   0.2130   0.01590   0.00860  -0.0485   0.8135   0.9227
   0.250   0.2532   0.01597   0.00864  -0.0503   0.8093   0.9495
   0.500   0.3087   0.01599   0.00862  -0.0552   0.8064   0.9742
   0.750   0.3595   0.01596   0.00855  -0.0597   0.8033   0.9867
   1.000   0.3957   0.01608   0.00868  -0.0620   0.7965   0.9943
   1.250   0.4300   0.01610   0.00869  -0.0636   0.7912   1.0000
   1.500   0.4519   0.01610   0.00866  -0.0625   0.7866   1.0000
   1.750   0.4704   0.01630   0.00889  -0.0612   0.7790   1.0000
   2.000   0.4912   0.01633   0.00891  -0.0599   0.7720   1.0000
   2.250   0.5109   0.01624   0.00882  -0.0581   0.7609   1.0000
   2.500   0.5325   0.01591   0.00843  -0.0561   0.7471   1.0000
   2.750   0.5541   0.01561   0.00807  -0.0541   0.7310   1.0000
   3.000   0.5762   0.01540   0.00783  -0.0524   0.7142   1.0000
   3.250   0.5980   0.01526   0.00768  -0.0508   0.6938   1.0000
   3.500   0.6208   0.01515   0.00754  -0.0493   0.6707   1.0000
   3.750   0.6448   0.01505   0.00741  -0.0481   0.6475   1.0000
   4.000   0.6683   0.01507   0.00742  -0.0470   0.6205   1.0000
   4.250   0.6918   0.01511   0.00738  -0.0457   0.5836   1.0000
   4.500   0.7139   0.01525   0.00728  -0.0441   0.5203   1.0000
   4.750   0.7285   0.01604   0.00729  -0.0415   0.3863   1.0000
   5.250   0.7531   0.01873   0.00872  -0.0373   0.1998   1.0000
   5.500   0.7715   0.01961   0.00939  -0.0361   0.1695   1.0000
   5.750   0.7910   0.02038   0.01003  -0.0350   0.1495   1.0000
   6.000   0.8106   0.02112   0.01068  -0.0339   0.1351   1.0000
   6.250   0.8299   0.02188   0.01136  -0.0328   0.1243   1.0000
   6.500   0.8494   0.02263   0.01206  -0.0317   0.1151   1.0000
   6.750   0.8690   0.02338   0.01280  -0.0306   0.1076   1.0000
   7.000   0.8877   0.02420   0.01355  -0.0294   0.1013   1.0000
   7.250   0.9075   0.02498   0.01437  -0.0284   0.0956   1.0000
   7.500   0.9267   0.02581   0.01517  -0.0273   0.0909   1.0000
   7.750   0.9461   0.02672   0.01606  -0.0263   0.0868   1.0000
   8.000   0.9663   0.02757   0.01697  -0.0253   0.0826   1.0000
   8.250   0.9858   0.02850   0.01785  -0.0244   0.0794   1.0000
   8.500   1.0067   0.02952   0.01890  -0.0236   0.0765   1.0000
   8.750   1.0277   0.03048   0.01996  -0.0228   0.0733   1.0000
   9.000   1.0476   0.03146   0.02093  -0.0220   0.0707   1.0000
   9.250   1.0686   0.03261   0.02203  -0.0213   0.0686   1.0000
   9.500   1.0904   0.03381   0.02343  -0.0207   0.0663   1.0000
   9.750   1.1106   0.03499   0.02472  -0.0199   0.0641   1.0000
  10.000   1.1295   0.03610   0.02586  -0.0191   0.0622   1.0000
  10.250   1.1496   0.03738   0.02709  -0.0185   0.0607   1.0000
  10.500   1.1680   0.03899   0.02900  -0.0175   0.0590   1.0000
  10.750   1.1845   0.04060   0.03083  -0.0165   0.0574   1.0000
  11.000   1.1986   0.04205   0.03243  -0.0151   0.0559   1.0000
  11.250   1.2117   0.04340   0.03385  -0.0138   0.0547   1.0000
  11.500   1.2263   0.04480   0.03527  -0.0128   0.0536   1.0000
  11.750   1.2326   0.04701   0.03780  -0.0108   0.0526   1.0000
  12.000   1.2354   0.04945   0.04058  -0.0088   0.0516   1.0000
  12.250   1.2360   0.05191   0.04333  -0.0068   0.0507   1.0000
  12.500   1.2354   0.05434   0.04600  -0.0050   0.0498   1.0000
  12.750   1.2340   0.05677   0.04862  -0.0035   0.0490   1.0000
  13.000   1.2329   0.05915   0.05117  -0.0022   0.0483   1.0000
  13.250   1.2327   0.06152   0.05366  -0.0011   0.0476   1.0000
  13.500   1.2338   0.06391   0.05612  -0.0003   0.0471   1.0000
  13.750   1.2206   0.06779   0.06026   0.0004   0.0467   1.0000
  14.000   1.1960   0.07306   0.06588   0.0005   0.0465   1.0000
  14.250   1.1681   0.07916   0.07230  -0.0005   0.0463   1.0000
  14.500   1.1358   0.08642   0.07987  -0.0029   0.0463   1.0000
  14.750   1.0981   0.09539   0.08912  -0.0072   0.0464   1.0000
  15.000   1.0513   0.10765   0.10165  -0.0146   0.0466   1.0000
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