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SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SD6080 (9.2%) (sd6080-il)
Reynolds number: 500,000
Max Cl/Cd: 104.38 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd6080-il-500000-n5.txt
Download as CSV file: xf-sd6080-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3689   0.10965   0.10733  -0.0247   1.0000   0.0094
 -10.000  -0.3632   0.10634   0.10403  -0.0260   1.0000   0.0094
  -8.500  -0.3399   0.08641   0.08424  -0.0336   1.0000   0.0101
  -8.250  -0.3211   0.08286   0.08069  -0.0384   0.9689   0.0108
  -8.000  -0.3056   0.07619   0.07397  -0.0464   0.9445   0.0084
  -7.250  -0.3014   0.06254   0.06014  -0.0579   0.8731   0.0091
  -7.000  -0.2952   0.05802   0.05554  -0.0624   0.8581   0.0088
  -6.750  -0.2859   0.05276   0.05017  -0.0674   0.8449   0.0085
  -6.500  -0.2991   0.02776   0.02414  -0.0793   0.8317   0.0068
  -6.250  -0.2817   0.02255   0.01820  -0.0800   0.8227   0.0067
  -6.000  -0.2597   0.01981   0.01496  -0.0800   0.8140   0.0067
  -5.750  -0.2360   0.01765   0.01239  -0.0799   0.8057   0.0068
  -5.500  -0.2110   0.01623   0.01065  -0.0797   0.7975   0.0069
  -5.250  -0.1850   0.01512   0.00931  -0.0795   0.7893   0.0071
  -5.000  -0.1588   0.01422   0.00820  -0.0793   0.7815   0.0074
  -4.750  -0.1320   0.01343   0.00724  -0.0792   0.7733   0.0077
  -4.500  -0.1052   0.01276   0.00641  -0.0790   0.7656   0.0081
  -4.250  -0.0782   0.01214   0.00565  -0.0788   0.7576   0.0084
  -4.000  -0.0511   0.01161   0.00499  -0.0786   0.7501   0.0088
  -3.750  -0.0237   0.01121   0.00450  -0.0785   0.7421   0.0092
  -3.500   0.0035   0.01070   0.00389  -0.0784   0.7347   0.0100
  -3.250   0.0310   0.01032   0.00342  -0.0783   0.7269   0.0106
  -3.000   0.0587   0.01000   0.00303  -0.0782   0.7196   0.0113
  -2.750   0.0865   0.00975   0.00269  -0.0781   0.7118   0.0121
  -2.500   0.1144   0.00954   0.00240  -0.0780   0.7046   0.0132
  -2.250   0.1422   0.00932   0.00212  -0.0779   0.6971   0.0160
  -2.000   0.1700   0.00905   0.00192  -0.0779   0.6900   0.0347
  -1.750   0.1978   0.00885   0.00177  -0.0779   0.6826   0.0623
  -1.500   0.2255   0.00864   0.00166  -0.0779   0.6756   0.0991
  -1.250   0.2532   0.00843   0.00157  -0.0779   0.6682   0.1470
  -1.000   0.2806   0.00814   0.00151  -0.0780   0.6613   0.2278
  -0.750   0.3081   0.00792   0.00145  -0.0781   0.6539   0.3000
  -0.500   0.3356   0.00773   0.00142  -0.0781   0.6469   0.3715
  -0.250   0.3625   0.00742   0.00142  -0.0781   0.6394   0.4855
   0.000   0.3890   0.00713   0.00143  -0.0779   0.6323   0.5997
   0.250   0.4143   0.00683   0.00146  -0.0773   0.6244   0.7176
   0.500   0.4364   0.00651   0.00151  -0.0757   0.6167   0.8474
   0.750   0.4762   0.00634   0.00146  -0.0779   0.6074   0.9991
   1.000   0.5039   0.00642   0.00146  -0.0779   0.5985   1.0000
   1.250   0.5314   0.00651   0.00148  -0.0777   0.5898   1.0000
   1.500   0.5589   0.00659   0.00151  -0.0777   0.5801   1.0000
   1.750   0.5864   0.00668   0.00154  -0.0776   0.5705   1.0000
   2.000   0.6138   0.00679   0.00159  -0.0775   0.5602   1.0000
   2.250   0.6411   0.00690   0.00164  -0.0773   0.5487   1.0000
   2.500   0.6685   0.00701   0.00171  -0.0773   0.5367   1.0000
   2.750   0.6957   0.00714   0.00178  -0.0771   0.5241   1.0000
   3.000   0.7228   0.00727   0.00187  -0.0770   0.5109   1.0000
   3.250   0.7498   0.00742   0.00197  -0.0769   0.4971   1.0000
   3.500   0.7766   0.00758   0.00208  -0.0767   0.4822   1.0000
   3.750   0.8033   0.00777   0.00221  -0.0766   0.4657   1.0000
   4.000   0.8297   0.00798   0.00235  -0.0764   0.4474   1.0000
   4.250   0.8559   0.00820   0.00252  -0.0761   0.4280   1.0000
   4.500   0.8819   0.00845   0.00270  -0.0759   0.4065   1.0000
   4.750   0.9075   0.00874   0.00290  -0.0756   0.3840   1.0000
   5.000   0.9328   0.00907   0.00314  -0.0753   0.3592   1.0000
   5.250   0.9578   0.00941   0.00340  -0.0750   0.3331   1.0000
   5.500   0.9820   0.00984   0.00369  -0.0745   0.3026   1.0000
   5.750   1.0055   0.01035   0.00404  -0.0740   0.2668   1.0000
   6.000   1.0276   0.01099   0.00446  -0.0734   0.2234   1.0000
   6.250   1.0498   0.01160   0.00489  -0.0728   0.1872   1.0000
   6.500   1.0731   0.01210   0.00528  -0.0722   0.1633   1.0000
   6.750   1.0960   0.01261   0.00569  -0.0717   0.1404   1.0000
   7.000   1.1183   0.01315   0.00615  -0.0710   0.1185   1.0000
   7.250   1.1394   0.01381   0.00666  -0.0702   0.0927   1.0000
   7.500   1.1603   0.01445   0.00719  -0.0694   0.0717   1.0000
   7.750   1.1813   0.01506   0.00773  -0.0686   0.0548   1.0000
   8.000   1.2000   0.01586   0.00841  -0.0675   0.0348   1.0000
   8.250   1.2182   0.01667   0.00914  -0.0663   0.0191   1.0000
   8.500   1.2366   0.01743   0.00987  -0.0651   0.0127   1.0000
   8.750   1.2560   0.01805   0.01054  -0.0640   0.0112   1.0000
   9.000   1.2742   0.01874   0.01129  -0.0628   0.0100   1.0000
   9.250   1.2927   0.01935   0.01197  -0.0616   0.0096   1.0000
   9.500   1.3098   0.02002   0.01273  -0.0602   0.0091   1.0000
   9.750   1.3249   0.02072   0.01351  -0.0585   0.0086   1.0000
  10.000   1.3371   0.02149   0.01436  -0.0564   0.0083   1.0000
  10.250   1.3478   0.02235   0.01530  -0.0542   0.0080   1.0000
  10.500   1.3576   0.02329   0.01633  -0.0521   0.0078   1.0000
  10.750   1.3656   0.02442   0.01754  -0.0500   0.0076   1.0000
  11.000   1.3721   0.02570   0.01893  -0.0479   0.0074   1.0000
  11.250   1.3754   0.02730   0.02064  -0.0457   0.0071   1.0000
  11.500   1.3779   0.02906   0.02250  -0.0438   0.0070   1.0000
  11.750   1.3842   0.03059   0.02414  -0.0423   0.0069   1.0000
  12.000   1.3898   0.03227   0.02592  -0.0410   0.0068   1.0000
  12.250   1.3933   0.03420   0.02796  -0.0398   0.0068   1.0000
  12.500   1.3969   0.03623   0.03010  -0.0388   0.0067   1.0000
  12.750   1.3989   0.03849   0.03248  -0.0379   0.0066   1.0000
  13.000   1.4009   0.04085   0.03496  -0.0372   0.0065   1.0000
  13.250   1.4018   0.04341   0.03765  -0.0367   0.0064   1.0000
  13.500   1.4046   0.04583   0.04019  -0.0364   0.0062   1.0000
  13.750   1.4028   0.04890   0.04338  -0.0362   0.0061   1.0000
  14.000   1.4018   0.05195   0.04655  -0.0362   0.0060   1.0000
  14.250   1.4008   0.05511   0.04983  -0.0365   0.0059   1.0000
  14.500   1.3983   0.05859   0.05344  -0.0369   0.0057   1.0000
  14.750   1.3944   0.06240   0.05738  -0.0375   0.0057   1.0000
  15.000   1.3913   0.06625   0.06135  -0.0385   0.0056   1.0000
  15.250   1.3869   0.07043   0.06566  -0.0396   0.0056   1.0000
  15.500   1.3814   0.07492   0.07028  -0.0410   0.0055   1.0000
  15.750   1.3754   0.07963   0.07513  -0.0426   0.0055   1.0000
  16.000   1.3689   0.08462   0.08025  -0.0445   0.0054   1.0000
  16.250   1.3616   0.08985   0.08561  -0.0466   0.0054   1.0000
  16.500   1.3543   0.09529   0.09118  -0.0490   0.0053   1.0000
  16.750   1.3463   0.10096   0.09699  -0.0515   0.0053   1.0000
  17.000   1.3376   0.10692   0.10308  -0.0544   0.0052   1.0000
  17.250   1.3287   0.11304   0.10933  -0.0574   0.0052   1.0000
  17.500   1.3198   0.11930   0.11573  -0.0607   0.0052   1.0000
  17.750   1.3103   0.12584   0.12240  -0.0642   0.0051   1.0000
  18.000   1.3011   0.13245   0.12915  -0.0679   0.0051   1.0000
  18.250   1.2916   0.13924   0.13607  -0.0718   0.0051   1.0000
  18.500   1.2822   0.14614   0.14310  -0.0758   0.0051   1.0000
  18.750   1.2730   0.15319   0.15027  -0.0801   0.0051   1.0000
  19.000   1.2635   0.16047   0.15767  -0.0846   0.0051   1.0000
  19.250   1.2539   0.16790   0.16523  -0.0893   0.0050   1.0000
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