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SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SD6080 (9.2%) (sd6080-il)
Reynolds number: 500,000
Max Cl/Cd: 115.29 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd6080-il-500000.txt
Download as CSV file: xf-sd6080-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3282   0.08563   0.08350  -0.0348   1.0000   0.0173
  -8.000  -0.3302   0.08174   0.07967  -0.0375   1.0000   0.0180
  -7.750  -0.3366   0.07839   0.07641  -0.0395   0.9979   0.0183
  -7.500  -0.3121   0.07180   0.06981  -0.0508   0.9814   0.0184
  -7.250  -0.2960   0.06499   0.06298  -0.0595   0.9691   0.0190
  -7.000  -0.2734   0.06125   0.05920  -0.0652   0.9554   0.0195
  -6.750  -0.2576   0.05767   0.05555  -0.0693   0.9371   0.0203
  -6.500  -0.2463   0.05347   0.05123  -0.0730   0.9190   0.0210
  -6.250  -0.2339   0.04874   0.04635  -0.0766   0.9037   0.0219
  -6.000  -0.2124   0.04168   0.03880  -0.0814   0.8896   0.0242
  -5.750  -0.2053   0.03528   0.03217  -0.0833   0.8782   0.0253
  -5.500  -0.1860   0.03382   0.03063  -0.0834   0.8689   0.0262
  -5.250  -0.1651   0.03154   0.02818  -0.0837   0.8591   0.0274
  -5.000  -0.1422   0.02866   0.02498  -0.0840   0.8498   0.0296
  -4.500  -0.0956   0.01706   0.01176  -0.0828   0.8331   0.0175
  -4.250  -0.0702   0.01461   0.00887  -0.0822   0.8256   0.0163
  -4.000  -0.0434   0.01318   0.00718  -0.0817   0.8169   0.0161
  -3.750  -0.0166   0.01225   0.00608  -0.0813   0.8092   0.0166
  -3.500   0.0104   0.01153   0.00523  -0.0809   0.8008   0.0173
  -3.250   0.0375   0.01097   0.00456  -0.0806   0.7929   0.0179
  -3.000   0.0643   0.01032   0.00382  -0.0804   0.7849   0.0197
  -2.750   0.0918   0.00992   0.00337  -0.0802   0.7769   0.0214
  -2.500   0.1193   0.00959   0.00293  -0.0800   0.7693   0.0236
  -2.250   0.1472   0.00919   0.00250  -0.0798   0.7613   0.0315
  -2.000   0.1744   0.00869   0.00219  -0.0797   0.7540   0.0938
  -1.750   0.2018   0.00837   0.00207  -0.0797   0.7460   0.1555
  -1.500   0.2289   0.00804   0.00196  -0.0797   0.7389   0.2436
  -1.250   0.2555   0.00754   0.00192  -0.0798   0.7309   0.3906
  -1.000   0.2815   0.00713   0.00189  -0.0796   0.7241   0.5339
  -0.750   0.3064   0.00666   0.00189  -0.0789   0.7161   0.6885
  -0.500   0.3264   0.00622   0.00191  -0.0767   0.7094   0.8593
  -0.250   0.3718   0.00601   0.00180  -0.0801   0.7014   1.0000
   0.000   0.3990   0.00609   0.00175  -0.0798   0.6943   1.0000
   0.250   0.4265   0.00614   0.00174  -0.0797   0.6860   1.0000
   0.500   0.4538   0.00622   0.00172  -0.0795   0.6785   1.0000
   0.750   0.4813   0.00628   0.00171  -0.0794   0.6699   1.0000
   1.000   0.5088   0.00636   0.00171  -0.0793   0.6619   1.0000
   1.250   0.5363   0.00643   0.00172  -0.0791   0.6535   1.0000
   1.500   0.5639   0.00650   0.00175  -0.0790   0.6450   1.0000
   1.750   0.5912   0.00661   0.00177  -0.0789   0.6367   1.0000
   2.000   0.6188   0.00667   0.00182  -0.0788   0.6273   1.0000
   2.250   0.6463   0.00676   0.00186  -0.0787   0.6183   1.0000
   2.500   0.6736   0.00686   0.00192  -0.0786   0.6087   1.0000
   2.750   0.7011   0.00694   0.00199  -0.0785   0.5985   1.0000
   3.000   0.7284   0.00705   0.00206  -0.0783   0.5887   1.0000
   3.500   0.7828   0.00727   0.00223  -0.0781   0.5667   1.0000
   3.750   0.8100   0.00738   0.00233  -0.0780   0.5548   1.0000
   4.000   0.8370   0.00751   0.00244  -0.0778   0.5422   1.0000
   4.250   0.8638   0.00765   0.00255  -0.0776   0.5285   1.0000
   4.500   0.8905   0.00781   0.00270  -0.0774   0.5137   1.0000
   4.750   0.9170   0.00798   0.00284  -0.0772   0.4972   1.0000
   5.000   0.9431   0.00818   0.00301  -0.0770   0.4795   1.0000
   5.250   0.9691   0.00841   0.00319  -0.0767   0.4599   1.0000
   5.500   0.9947   0.00866   0.00340  -0.0764   0.4373   1.0000
   5.750   1.0196   0.00898   0.00364  -0.0760   0.4103   1.0000
   6.000   1.0432   0.00942   0.00393  -0.0754   0.3737   1.0000
   6.250   1.0659   0.00996   0.00429  -0.0748   0.3314   1.0000
   6.500   1.0884   0.01053   0.00468  -0.0741   0.2922   1.0000
   6.750   1.1109   0.01109   0.00509  -0.0735   0.2585   1.0000
   7.000   1.1327   0.01170   0.00555  -0.0728   0.2237   1.0000
   7.250   1.1540   0.01235   0.00605  -0.0720   0.1913   1.0000
   7.500   1.1755   0.01297   0.00654  -0.0713   0.1635   1.0000
   7.750   1.1962   0.01364   0.00707  -0.0704   0.1359   1.0000
   8.000   1.2163   0.01434   0.00764  -0.0695   0.1096   1.0000
   8.250   1.2355   0.01510   0.00828  -0.0685   0.0844   1.0000
   8.500   1.2521   0.01605   0.00905  -0.0671   0.0543   1.0000
   8.750   1.2633   0.01746   0.01020  -0.0649   0.0236   1.0000
   9.250   1.2961   0.01914   0.01197  -0.0618   0.0163   1.0000
   9.500   1.3118   0.01994   0.01284  -0.0602   0.0152   1.0000
   9.750   1.3233   0.02088   0.01386  -0.0580   0.0142   1.0000
  10.000   1.3290   0.02203   0.01511  -0.0550   0.0136   1.0000
  10.250   1.3323   0.02337   0.01655  -0.0519   0.0131   1.0000
  10.500   1.3400   0.02450   0.01779  -0.0496   0.0129   1.0000
  10.750   1.3463   0.02580   0.01920  -0.0474   0.0127   1.0000
  11.000   1.3516   0.02727   0.02076  -0.0454   0.0124   1.0000
  11.250   1.3561   0.02888   0.02249  -0.0435   0.0122   1.0000
  11.500   1.3602   0.03063   0.02435  -0.0418   0.0119   1.0000
  11.750   1.3639   0.03251   0.02634  -0.0402   0.0117   1.0000
  12.000   1.3678   0.03445   0.02839  -0.0389   0.0113   1.0000
  12.250   1.3719   0.03644   0.03046  -0.0378   0.0110   1.0000
  12.500   1.3749   0.03862   0.03272  -0.0369   0.0107   1.0000
  12.750   1.3768   0.04101   0.03522  -0.0359   0.0105   1.0000
  13.000   1.3778   0.04358   0.03789  -0.0351   0.0104   1.0000
  13.250   1.3783   0.04632   0.04073  -0.0344   0.0102   1.0000
  13.500   1.3782   0.04925   0.04378  -0.0337   0.0100   1.0000
  13.750   1.3785   0.05224   0.04690  -0.0332   0.0100   1.0000
  14.000   1.3768   0.05570   0.05051  -0.0325   0.0098   1.0000
  14.250   1.3761   0.05903   0.05399  -0.0323   0.0098   1.0000
  14.500   1.3721   0.06305   0.05820  -0.0322   0.0097   1.0000
  14.750   1.3647   0.06763   0.06299  -0.0324   0.0096   1.0000
  15.000   1.3567   0.07231   0.06787  -0.0332   0.0096   1.0000
  15.500   1.3374   0.08243   0.07836  -0.0362   0.0096   1.0000
  15.750   1.3260   0.08797   0.08409  -0.0387   0.0096   1.0000
  16.000   1.3125   0.09429   0.09060  -0.0412   0.0096   1.0000
  16.250   1.2976   0.10108   0.09758  -0.0444   0.0096   1.0000
  16.500   1.2844   0.10784   0.10451  -0.0480   0.0096   1.0000
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