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SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: SD6080 (9.2%) (sd6080-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.66 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd6080-il-1000000-n5.txt
Download as CSV file: xf-sd6080-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD6080 (9.2%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3137   0.08256   0.08077  -0.0447   0.9153   0.0049
  -8.500  -0.3100   0.07966   0.07779  -0.0459   0.8905   0.0051
  -7.000  -0.3702   0.02004   0.01625  -0.0786   0.7944   0.0046
  -6.750  -0.3482   0.01749   0.01326  -0.0786   0.7859   0.0046
  -6.500  -0.3239   0.01590   0.01137  -0.0785   0.7780   0.0046
  -6.250  -0.2985   0.01473   0.00995  -0.0784   0.7696   0.0047
  -6.000  -0.2725   0.01373   0.00874  -0.0783   0.7618   0.0047
  -5.750  -0.2460   0.01297   0.00781  -0.0782   0.7538   0.0049
  -5.500  -0.2192   0.01226   0.00694  -0.0781   0.7460   0.0050
  -5.000  -0.1651   0.01110   0.00551  -0.0779   0.7306   0.0054
  -4.750  -0.1378   0.01063   0.00492  -0.0778   0.7231   0.0056
  -4.500  -0.1102   0.01023   0.00443  -0.0777   0.7156   0.0060
  -4.250  -0.0826   0.00989   0.00398  -0.0776   0.7080   0.0062
  -4.000  -0.0548   0.00958   0.00361  -0.0776   0.7005   0.0064
  -3.750  -0.0271   0.00932   0.00326  -0.0776   0.6931   0.0065
  -3.500   0.0007   0.00889   0.00275  -0.0775   0.6857   0.0068
  -3.250   0.0285   0.00862   0.00241  -0.0775   0.6786   0.0073
  -3.000   0.0566   0.00842   0.00218  -0.0775   0.6715   0.0079
  -2.750   0.0846   0.00826   0.00196  -0.0775   0.6644   0.0085
  -2.500   0.1128   0.00810   0.00174  -0.0775   0.6575   0.0091
  -2.000   0.1692   0.00783   0.00138  -0.0775   0.6437   0.0116
  -1.750   0.1973   0.00771   0.00124  -0.0775   0.6366   0.0165
  -1.500   0.2254   0.00751   0.00114  -0.0775   0.6300   0.0436
  -1.250   0.2534   0.00736   0.00106  -0.0776   0.6228   0.0743
  -1.000   0.2815   0.00722   0.00100  -0.0777   0.6161   0.1060
  -0.750   0.3094   0.00708   0.00095  -0.0777   0.6086   0.1487
  -0.500   0.3374   0.00692   0.00092  -0.0778   0.6012   0.2045
  -0.250   0.3651   0.00673   0.00090  -0.0779   0.5927   0.2784
   0.000   0.3930   0.00659   0.00090  -0.0780   0.5843   0.3398
   0.250   0.4204   0.00640   0.00091  -0.0780   0.5755   0.4293
   0.500   0.4481   0.00624   0.00093  -0.0781   0.5662   0.5069
   0.750   0.4755   0.00609   0.00096  -0.0781   0.5572   0.5889
   1.000   0.5022   0.00591   0.00101  -0.0779   0.5473   0.6853
   1.250   0.5277   0.00568   0.00107  -0.0774   0.5369   0.7966
   1.500   0.5493   0.00544   0.00113  -0.0757   0.5264   0.9196
   1.750   0.5878   0.00546   0.00114  -0.0780   0.5130   1.0000
   2.000   0.6153   0.00558   0.00119  -0.0779   0.4999   1.0000
   2.250   0.6428   0.00570   0.00124  -0.0779   0.4866   1.0000
   2.500   0.6702   0.00583   0.00132  -0.0778   0.4726   1.0000
   2.750   0.6975   0.00598   0.00139  -0.0777   0.4572   1.0000
   3.000   0.7247   0.00614   0.00148  -0.0776   0.4404   1.0000
   3.250   0.7518   0.00631   0.00159  -0.0775   0.4225   1.0000
   3.750   0.8053   0.00673   0.00183  -0.0773   0.3831   1.0000
   4.000   0.8317   0.00698   0.00198  -0.0772   0.3607   1.0000
   4.250   0.8580   0.00724   0.00215  -0.0770   0.3373   1.0000
   4.500   0.8840   0.00753   0.00234  -0.0768   0.3132   1.0000
   4.750   0.9092   0.00791   0.00257  -0.0765   0.2797   1.0000
   5.000   0.9340   0.00833   0.00283  -0.0762   0.2470   1.0000
   5.250   0.9589   0.00873   0.00309  -0.0758   0.2180   1.0000
   5.500   0.9833   0.00918   0.00339  -0.0755   0.1863   1.0000
   5.750   1.0074   0.00965   0.00370  -0.0750   0.1559   1.0000
   6.000   1.0315   0.01010   0.00403  -0.0746   0.1308   1.0000
   6.250   1.0554   0.01057   0.00437  -0.0742   0.1079   1.0000
   6.500   1.0793   0.01101   0.00471  -0.0737   0.0879   1.0000
   6.750   1.1028   0.01148   0.00509  -0.0732   0.0700   1.0000
   7.000   1.1252   0.01205   0.00554  -0.0726   0.0490   1.0000
   7.250   1.1477   0.01259   0.00600  -0.0719   0.0332   1.0000
   7.500   1.1679   0.01335   0.00662  -0.0709   0.0130   1.0000
   7.750   1.1908   0.01381   0.00707  -0.0703   0.0095   1.0000
   8.000   1.2139   0.01421   0.00751  -0.0697   0.0085   1.0000
   8.250   1.2365   0.01466   0.00798  -0.0691   0.0077   1.0000
   8.500   1.2584   0.01514   0.00849  -0.0683   0.0070   1.0000
   8.750   1.2805   0.01557   0.00897  -0.0676   0.0068   1.0000
   9.000   1.3020   0.01603   0.00948  -0.0668   0.0066   1.0000
   9.250   1.3228   0.01653   0.01003  -0.0659   0.0064   1.0000
   9.500   1.3428   0.01707   0.01062  -0.0649   0.0062   1.0000
   9.750   1.3619   0.01763   0.01123  -0.0638   0.0059   1.0000
  10.000   1.3800   0.01822   0.01188  -0.0625   0.0058   1.0000
  10.250   1.3967   0.01887   0.01259  -0.0611   0.0056   1.0000
  10.500   1.4108   0.01953   0.01331  -0.0592   0.0055   1.0000
  10.750   1.4219   0.02026   0.01411  -0.0569   0.0053   1.0000
  11.000   1.4317   0.02107   0.01499  -0.0545   0.0052   1.0000
  11.250   1.4396   0.02207   0.01606  -0.0521   0.0050   1.0000
  11.500   1.4463   0.02321   0.01728  -0.0498   0.0049   1.0000
  11.750   1.4492   0.02468   0.01886  -0.0473   0.0047   1.0000
  12.000   1.4559   0.02597   0.02024  -0.0455   0.0047   1.0000
  12.250   1.4646   0.02717   0.02151  -0.0440   0.0046   1.0000
  12.500   1.4739   0.02838   0.02281  -0.0427   0.0045   1.0000
  12.750   1.4801   0.02990   0.02442  -0.0413   0.0045   1.0000
  13.000   1.4857   0.03155   0.02616  -0.0401   0.0044   1.0000
  13.250   1.4903   0.03337   0.02807  -0.0390   0.0043   1.0000
  13.500   1.4953   0.03522   0.03001  -0.0381   0.0043   1.0000
  13.750   1.4961   0.03757   0.03247  -0.0373   0.0042   1.0000
  14.000   1.4974   0.03997   0.03497  -0.0366   0.0041   1.0000
  14.250   1.4990   0.04242   0.03753  -0.0362   0.0041   1.0000
  14.500   1.4989   0.04517   0.04039  -0.0360   0.0040   1.0000
  14.750   1.4951   0.04846   0.04379  -0.0359   0.0040   1.0000
  15.000   1.4949   0.05143   0.04686  -0.0361   0.0039   1.0000
  15.250   1.4926   0.05481   0.05036  -0.0365   0.0039   1.0000
  15.500   1.4875   0.05870   0.05437  -0.0372   0.0038   1.0000
  15.750   1.4816   0.06286   0.05866  -0.0381   0.0038   1.0000
  16.000   1.4768   0.06706   0.06297  -0.0393   0.0037   1.0000
  16.250   1.4676   0.07209   0.06813  -0.0409   0.0037   1.0000
  16.500   1.4623   0.07670   0.07285  -0.0426   0.0037   1.0000
  16.750   1.4530   0.08211   0.07839  -0.0447   0.0037   1.0000
  17.000   1.4438   0.08772   0.08412  -0.0471   0.0036   1.0000
  17.250   1.4328   0.09379   0.09031  -0.0497   0.0036   1.0000
  17.500   1.4222   0.09998   0.09662  -0.0526   0.0036   1.0000
  17.750   1.4123   0.10621   0.10297  -0.0557   0.0035   1.0000
  18.000   1.3986   0.11329   0.11018  -0.0593   0.0035   1.0000
  18.250   1.3863   0.12026   0.11727  -0.0629   0.0035   1.0000
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