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SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SD6080 (9.2%) (sd6080-il)
Reynolds number: 200,000
Max Cl/Cd: 80.44 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd6080-il-200000-n5.txt
Download as CSV file: xf-sd6080-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3265   0.08917   0.08580  -0.0339   1.0000   0.0265
  -8.000  -0.3249   0.08606   0.08276  -0.0353   1.0000   0.0269
  -7.750  -0.3260   0.08302   0.07979  -0.0362   1.0000   0.0270
  -7.250  -0.3101   0.06805   0.06486  -0.0547   0.9632   0.0179
  -7.000  -0.2898   0.06480   0.06157  -0.0587   0.9506   0.0166
  -6.750  -0.2708   0.05925   0.05594  -0.0663   0.9353   0.0157
  -6.250  -0.2426   0.03935   0.03536  -0.0823   0.9035   0.0129
  -6.000  -0.2269   0.03438   0.02999  -0.0840   0.8915   0.0127
  -5.750  -0.2093   0.02951   0.02457  -0.0850   0.8811   0.0126
  -5.500  -0.1890   0.02576   0.02022  -0.0851   0.8719   0.0126
  -5.250  -0.1664   0.02278   0.01666  -0.0849   0.8622   0.0127
  -5.000  -0.1420   0.02067   0.01402  -0.0844   0.8541   0.0130
  -4.750  -0.1175   0.01917   0.01226  -0.0842   0.8452   0.0139
  -4.500  -0.0919   0.01832   0.01122  -0.0839   0.8369   0.0152
  -4.250  -0.0660   0.01708   0.00970  -0.0834   0.8289   0.0157
  -4.000  -0.0399   0.01599   0.00840  -0.0829   0.8206   0.0162
  -3.750  -0.0137   0.01511   0.00734  -0.0824   0.8130   0.0167
  -3.500   0.0128   0.01439   0.00647  -0.0820   0.8046   0.0174
  -3.250   0.0390   0.01371   0.00569  -0.0816   0.7973   0.0186
  -3.000   0.0660   0.01326   0.00516  -0.0814   0.7888   0.0208
  -2.750   0.0928   0.01285   0.00466  -0.0811   0.7817   0.0253
  -2.500   0.1200   0.01239   0.00417  -0.0808   0.7733   0.0340
  -2.250   0.1471   0.01198   0.00377  -0.0806   0.7661   0.0620
  -2.000   0.1738   0.01155   0.00357  -0.0805   0.7578   0.1204
  -1.750   0.2002   0.01111   0.00340  -0.0804   0.7506   0.2051
  -1.500   0.2269   0.01077   0.00326  -0.0803   0.7426   0.2832
  -1.250   0.2532   0.01042   0.00315  -0.0801   0.7354   0.3801
  -1.000   0.2783   0.00998   0.00311  -0.0796   0.7275   0.5125
  -0.750   0.3009   0.00948   0.00309  -0.0783   0.7204   0.6710
  -0.500   0.3224   0.00903   0.00307  -0.0761   0.7129   0.8477
  -0.250   0.3691   0.00886   0.00288  -0.0796   0.7056   1.0000
   0.000   0.3961   0.00893   0.00281  -0.0794   0.6977   1.0000
   0.250   0.4232   0.00902   0.00277  -0.0792   0.6901   1.0000
   0.500   0.4503   0.00910   0.00274  -0.0790   0.6823   1.0000
   0.750   0.4774   0.00919   0.00274  -0.0788   0.6744   1.0000
   1.000   0.5045   0.00928   0.00273  -0.0786   0.6665   1.0000
   1.250   0.5317   0.00938   0.00276  -0.0784   0.6579   1.0000
   1.750   0.5858   0.00959   0.00283  -0.0780   0.6400   1.0000
   2.000   0.6128   0.00970   0.00288  -0.0778   0.6309   1.0000
   2.250   0.6397   0.00981   0.00293  -0.0775   0.6217   1.0000
   2.500   0.6666   0.00993   0.00303  -0.0773   0.6114   1.0000
   2.750   0.6935   0.01005   0.00312  -0.0771   0.6013   1.0000
   3.000   0.7202   0.01019   0.00320  -0.0768   0.5908   1.0000
   3.250   0.7468   0.01032   0.00332  -0.0766   0.5790   1.0000
   3.500   0.7734   0.01046   0.00347  -0.0763   0.5667   1.0000
   3.750   0.7998   0.01062   0.00360  -0.0760   0.5539   1.0000
   4.000   0.8261   0.01078   0.00375  -0.0757   0.5404   1.0000
   4.250   0.8522   0.01095   0.00393  -0.0754   0.5261   1.0000
   4.500   0.8781   0.01115   0.00411  -0.0750   0.5106   1.0000
   4.750   0.9037   0.01136   0.00430  -0.0746   0.4936   1.0000
   5.250   0.9540   0.01186   0.00477  -0.0737   0.4546   1.0000
   5.500   0.9783   0.01218   0.00504  -0.0732   0.4323   1.0000
   5.750   1.0023   0.01252   0.00534  -0.0726   0.4073   1.0000
   6.000   1.0256   0.01292   0.00570  -0.0720   0.3808   1.0000
   6.250   1.0483   0.01338   0.00609  -0.0712   0.3527   1.0000
   6.500   1.0702   0.01390   0.00652  -0.0704   0.3228   1.0000
   6.750   1.0913   0.01449   0.00701  -0.0696   0.2918   1.0000
   7.000   1.1112   0.01519   0.00759  -0.0686   0.2585   1.0000
   7.250   1.1296   0.01600   0.00822  -0.0675   0.2198   1.0000
   7.500   1.1477   0.01684   0.00889  -0.0663   0.1846   1.0000
   7.750   1.1660   0.01764   0.00957  -0.0652   0.1566   1.0000
   8.000   1.1838   0.01845   0.01029  -0.0641   0.1316   1.0000
   8.250   1.2014   0.01927   0.01105  -0.0629   0.1103   1.0000
   8.500   1.2176   0.02016   0.01187  -0.0615   0.0881   1.0000
   8.750   1.2327   0.02112   0.01274  -0.0601   0.0686   1.0000
   9.000   1.2453   0.02222   0.01374  -0.0583   0.0486   1.0000
   9.250   1.2559   0.02339   0.01484  -0.0563   0.0328   1.0000
   9.500   1.2639   0.02458   0.01601  -0.0538   0.0240   1.0000
   9.750   1.2730   0.02569   0.01721  -0.0516   0.0201   1.0000
  10.000   1.2802   0.02699   0.01856  -0.0494   0.0180   1.0000
  10.250   1.2887   0.02823   0.01994  -0.0474   0.0168   1.0000
  10.500   1.2964   0.02957   0.02141  -0.0456   0.0160   1.0000
  10.750   1.3027   0.03109   0.02305  -0.0439   0.0153   1.0000
  11.000   1.3077   0.03275   0.02485  -0.0423   0.0147   1.0000
  11.250   1.3104   0.03472   0.02692  -0.0408   0.0141   1.0000
  11.500   1.3105   0.03699   0.02930  -0.0394   0.0136   1.0000
  11.750   1.3145   0.03902   0.03151  -0.0383   0.0132   1.0000
  12.000   1.3176   0.04122   0.03385  -0.0375   0.0127   1.0000
  12.250   1.3191   0.04366   0.03643  -0.0367   0.0124   1.0000
  12.500   1.3201   0.04625   0.03916  -0.0361   0.0121   1.0000
  12.750   1.3203   0.04901   0.04207  -0.0357   0.0119   1.0000
  13.000   1.3197   0.05196   0.04515  -0.0354   0.0117   1.0000
  13.250   1.3189   0.05503   0.04836  -0.0353   0.0114   1.0000
  13.500   1.3181   0.05817   0.05164  -0.0353   0.0113   1.0000
  13.750   1.3163   0.06154   0.05515  -0.0355   0.0111   1.0000
  14.000   1.3143   0.06503   0.05877  -0.0359   0.0109   1.0000
  14.250   1.3118   0.06872   0.06260  -0.0365   0.0108   1.0000
  14.500   1.3088   0.07259   0.06663  -0.0372   0.0106   1.0000
  14.750   1.3057   0.07660   0.07078  -0.0381   0.0106   1.0000
  15.000   1.3018   0.08085   0.07518  -0.0392   0.0104   1.0000
  15.250   1.2973   0.08530   0.07978  -0.0405   0.0104   1.0000
  15.500   1.2919   0.09003   0.08466  -0.0421   0.0102   1.0000
  15.750   1.2858   0.09506   0.08986  -0.0439   0.0102   1.0000
  16.000   1.2780   0.10048   0.09545  -0.0461   0.0101   1.0000
  16.250   1.2698   0.10619   0.10134  -0.0487   0.0101   1.0000
  16.500   1.2597   0.11245   0.10778  -0.0517   0.0100   1.0000
  16.750   1.2490   0.11908   0.11458  -0.0553   0.0099   1.0000
  17.000   1.2372   0.12626   0.12196  -0.0594   0.0099   1.0000
  17.250   1.2254   0.13365   0.12954  -0.0639   0.0099   1.0000
  17.500   1.2133   0.14142   0.13748  -0.0687   0.0099   1.0000
  17.750   1.2000   0.14982   0.14605  -0.0741   0.0099   1.0000
  18.000   1.1867   0.15859   0.15498  -0.0798   0.0099   1.0000
  18.250   1.1732   0.16780   0.16435  -0.0858   0.0100   1.0000
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