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SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SD6080 (9.2%) (sd6080-il)
Reynolds number: 200,000
Max Cl/Cd: 83.56 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd6080-il-200000.txt
Download as CSV file: xf-sd6080-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2644   0.09377   0.09061  -0.0358   1.0000   0.0411
  -9.000  -0.2684   0.09071   0.08760  -0.0387   1.0000   0.0415
  -8.750  -0.2699   0.08741   0.08434  -0.0407   1.0000   0.0416
  -8.500  -0.2641   0.08143   0.07841  -0.0392   1.0000   0.0427
  -8.250  -0.2554   0.07833   0.07534  -0.0377   1.0000   0.0437
  -8.000  -0.2563   0.07592   0.07299  -0.0363   1.0000   0.0446
  -7.750  -0.2758   0.07555   0.07274  -0.0319   1.0000   0.0448
  -7.500  -0.2677   0.07172   0.06893  -0.0345   0.9959   0.0462
  -7.250  -0.2547   0.06686   0.06406  -0.0393   0.9898   0.0480
  -7.000  -0.3608   0.07857   0.07568  -0.0354   0.9955   0.0437
  -6.750  -0.3349   0.07432   0.07141  -0.0408   0.9892   0.0457
  -6.500  -0.3043   0.06890   0.06594  -0.0507   0.9823   0.0483
  -6.250  -0.2499   0.05943   0.05596  -0.0763   0.9721   0.0532
  -6.000  -0.2329   0.05304   0.04968  -0.0789   0.9652   0.0548
  -5.750  -0.2038   0.05000   0.04664  -0.0817   0.9604   0.0570
  -5.500  -0.1743   0.04615   0.04264  -0.0863   0.9522   0.0608
  -5.250  -0.1412   0.04006   0.03603  -0.0934   0.9443   0.0681
  -5.000  -0.1188   0.03767   0.03362  -0.0939   0.9343   0.0707
  -4.750  -0.0930   0.03452   0.02990  -0.0958   0.9244   0.0812
  -4.500  -0.0651   0.02514   0.01954  -0.0953   0.9163   0.0380
  -4.250  -0.0398   0.02146   0.01492  -0.0940   0.9066   0.0325
  -4.000  -0.0145   0.01958   0.01283  -0.0936   0.8995   0.0343
  -3.750   0.0103   0.01841   0.01147  -0.0928   0.8898   0.0360
  -3.500   0.0363   0.01699   0.00979  -0.0918   0.8820   0.0362
  -3.250   0.0620   0.01590   0.00855  -0.0908   0.8737   0.0373
  -3.000   0.0875   0.01503   0.00757  -0.0900   0.8653   0.0397
  -2.750   0.1127   0.01405   0.00653  -0.0890   0.8578   0.0446
  -2.500   0.1382   0.01340   0.00590  -0.0884   0.8489   0.0595
  -2.250   0.1635   0.01239   0.00516  -0.0877   0.8420   0.1352
  -2.000   0.1879   0.01167   0.00500  -0.0874   0.8329   0.2720
  -1.750   0.2109   0.01086   0.00486  -0.0865   0.8263   0.4734
  -1.500   0.2301   0.01015   0.00488  -0.0844   0.8171   0.6859
  -1.250   0.2686   0.00948   0.00465  -0.0848   0.8119   0.9613
  -1.000   0.3048   0.00948   0.00447  -0.0866   0.8029   1.0000
  -0.750   0.3307   0.00954   0.00432  -0.0860   0.7958   1.0000
  -0.500   0.3567   0.00962   0.00426  -0.0856   0.7870   1.0000
  -0.250   0.3830   0.00970   0.00418  -0.0851   0.7795   1.0000
   0.000   0.4094   0.00977   0.00413  -0.0847   0.7713   1.0000
   0.250   0.4359   0.00987   0.00411  -0.0843   0.7633   1.0000
   0.500   0.4626   0.00995   0.00407  -0.0839   0.7555   1.0000
   0.750   0.4892   0.01005   0.00409  -0.0836   0.7470   1.0000
   1.000   0.5162   0.01013   0.00405  -0.0832   0.7396   1.0000
   1.250   0.5427   0.01024   0.00411  -0.0829   0.7302   1.0000
   1.500   0.5697   0.01032   0.00410  -0.0825   0.7225   1.0000
   1.750   0.5963   0.01042   0.00415  -0.0822   0.7130   1.0000
   2.000   0.6231   0.01052   0.00421  -0.0818   0.7039   1.0000
   2.250   0.6502   0.01061   0.00421  -0.0815   0.6955   1.0000
   2.500   0.6767   0.01072   0.00433  -0.0811   0.6852   1.0000
   2.750   0.7034   0.01082   0.00439  -0.0808   0.6758   1.0000
   3.000   0.7304   0.01091   0.00442  -0.0804   0.6663   1.0000
   3.250   0.7568   0.01101   0.00454  -0.0801   0.6552   1.0000
   3.500   0.7833   0.01112   0.00465  -0.0797   0.6443   1.0000
   3.750   0.8099   0.01123   0.00473  -0.0793   0.6335   1.0000
   4.000   0.8365   0.01133   0.00480  -0.0789   0.6224   1.0000
   4.250   0.8626   0.01144   0.00494  -0.0785   0.6096   1.0000
   4.500   0.8887   0.01156   0.00510  -0.0781   0.5965   1.0000
   4.750   0.9147   0.01168   0.00523  -0.0776   0.5828   1.0000
   5.000   0.9404   0.01181   0.00538  -0.0771   0.5681   1.0000
   5.250   0.9660   0.01195   0.00553  -0.0766   0.5524   1.0000
   5.500   0.9913   0.01211   0.00570  -0.0760   0.5356   1.0000
   5.750   1.0162   0.01228   0.00592  -0.0754   0.5165   1.0000
   6.000   1.0406   0.01249   0.00613  -0.0747   0.4952   1.0000
   6.250   1.0645   0.01274   0.00640  -0.0740   0.4717   1.0000
   6.500   1.0877   0.01306   0.00668  -0.0732   0.4453   1.0000
   6.750   1.1099   0.01345   0.00703  -0.0723   0.4147   1.0000
   7.000   1.1309   0.01395   0.00743  -0.0712   0.3803   1.0000
   7.250   1.1505   0.01456   0.00794  -0.0700   0.3420   1.0000
   7.500   1.1685   0.01531   0.00852  -0.0687   0.3018   1.0000
   7.750   1.1852   0.01618   0.00919  -0.0673   0.2614   1.0000
   8.000   1.2020   0.01704   0.00991  -0.0659   0.2242   1.0000
   8.250   1.2184   0.01793   0.01068  -0.0645   0.1935   1.0000
   8.500   1.2341   0.01886   0.01151  -0.0631   0.1647   1.0000
   8.750   1.2492   0.01980   0.01237  -0.0616   0.1381   1.0000
   9.000   1.2623   0.02088   0.01332  -0.0599   0.1088   1.0000
   9.250   1.2690   0.02244   0.01461  -0.0574   0.0687   1.0000
   9.500   1.2665   0.02444   0.01639  -0.0535   0.0439   1.0000
   9.750   1.2672   0.02614   0.01812  -0.0502   0.0370   1.0000
  10.000   1.2700   0.02776   0.01980  -0.0476   0.0333   1.0000
  10.250   1.2669   0.02995   0.02206  -0.0447   0.0312   1.0000
  10.500   1.2727   0.03163   0.02388  -0.0427   0.0299   1.0000
  10.750   1.2781   0.03343   0.02579  -0.0409   0.0284   1.0000
  11.000   1.2840   0.03526   0.02772  -0.0394   0.0270   1.0000
  11.250   1.2894   0.03720   0.02972  -0.0380   0.0257   1.0000
  11.500   1.2933   0.03956   0.03211  -0.0366   0.0244   1.0000
  11.750   1.3026   0.04207   0.03470  -0.0350   0.0237   1.0000
  12.000   1.3131   0.04409   0.03690  -0.0338   0.0232   1.0000
  12.250   1.3238   0.04634   0.03934  -0.0327   0.0228   1.0000
  12.500   1.3331   0.04885   0.04208  -0.0316   0.0225   1.0000
  12.750   1.3398   0.05166   0.04512  -0.0305   0.0222   1.0000
  13.000   1.3426   0.05482   0.04854  -0.0296   0.0221   1.0000
  13.250   1.3417   0.05838   0.05237  -0.0288   0.0220   1.0000
  13.500   1.3365   0.06231   0.05657  -0.0283   0.0220   1.0000
  13.750   1.3279   0.06658   0.06111  -0.0283   0.0220   1.0000
  14.000   1.3166   0.07112   0.06591  -0.0287   0.0218   1.0000
  14.250   1.3027   0.07627   0.07131  -0.0297   0.0219   1.0000
  14.500   1.2868   0.08180   0.07709  -0.0313   0.0219   1.0000
  14.750   1.2695   0.08777   0.08329  -0.0335   0.0219   1.0000
  15.000   1.2502   0.09452   0.09027  -0.0366   0.0220   1.0000
  15.250   1.2292   0.10206   0.09802  -0.0404   0.0222   1.0000
  15.500   1.2087   0.11002   0.10619  -0.0449   0.0224   1.0000
  15.750   1.1866   0.11895   0.11530  -0.0505   0.0226   1.0000
  16.000   1.1644   0.12857   0.12508  -0.0566   0.0230   1.0000
  16.250   1.1417   0.13904   0.13567  -0.0633   0.0234   1.0000
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