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SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SD6080 (9.2%) (sd6080-il)
Reynolds number: 50,000
Max Cl/Cd: 39.62 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd6080-il-50000-n5.txt
Download as CSV file: xf-sd6080-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3346   0.09723   0.09077  -0.0330   1.0000   0.1065
  -7.750  -0.3349   0.09442   0.08806  -0.0336   1.0000   0.1066
  -7.500  -0.3395   0.08861   0.08228  -0.0367   1.0000   0.0596
  -7.250  -0.3414   0.08570   0.07948  -0.0361   1.0000   0.0563
  -6.750  -0.3614   0.07899   0.07298  -0.0403   1.0000   0.0487
  -6.500  -0.3658   0.07670   0.07076  -0.0387   1.0000   0.0479
  -6.250  -0.3710   0.07419   0.06832  -0.0377   1.0000   0.0470
  -6.000  -0.3750   0.07144   0.06560  -0.0374   1.0000   0.0461
  -5.750  -0.3699   0.06774   0.06186  -0.0395   0.9977   0.0450
  -5.500  -0.3411   0.06161   0.05554  -0.0474   0.9881   0.0432
  -5.250  -0.3110   0.05540   0.04901  -0.0548   0.9788   0.0419
  -5.000  -0.2785   0.05001   0.04323  -0.0610   0.9707   0.0421
  -4.750  -0.2467   0.04548   0.03824  -0.0657   0.9622   0.0432
  -4.500  -0.2136   0.04132   0.03351  -0.0696   0.9544   0.0444
  -4.250  -0.1786   0.03753   0.02909  -0.0728   0.9473   0.0452
  -4.000  -0.1447   0.03435   0.02529  -0.0749   0.9400   0.0459
  -3.750  -0.1088   0.03165   0.02194  -0.0768   0.9334   0.0473
  -3.500  -0.0734   0.02950   0.01923  -0.0782   0.9268   0.0501
  -3.250  -0.0405   0.02812   0.01768  -0.0795   0.9195   0.0569
  -3.000  -0.0043   0.02656   0.01582  -0.0807   0.9136   0.0642
  -2.750   0.0266   0.02553   0.01467  -0.0813   0.9055   0.0790
  -2.500   0.0621   0.02444   0.01354  -0.0827   0.8994   0.1134
  -2.250   0.0915   0.02342   0.01269  -0.0833   0.8908   0.1733
  -2.000   0.1245   0.02221   0.01207  -0.0846   0.8845   0.3017
  -1.750   0.1461   0.02111   0.01195  -0.0834   0.8757   0.5266
  -1.500   0.1941   0.01986   0.01144  -0.0849   0.8717   1.0000
  -1.250   0.2198   0.02008   0.01124  -0.0848   0.8615   1.0000
  -1.000   0.2508   0.02025   0.01102  -0.0854   0.8536   1.0000
  -0.750   0.2788   0.02046   0.01090  -0.0855   0.8446   1.0000
  -0.500   0.3059   0.02070   0.01086  -0.0854   0.8354   1.0000
  -0.250   0.3371   0.02086   0.01076  -0.0859   0.8280   1.0000
   0.000   0.3616   0.02115   0.01086  -0.0855   0.8180   1.0000
   0.250   0.3929   0.02130   0.01080  -0.0859   0.8110   1.0000
   0.500   0.4171   0.02162   0.01097  -0.0854   0.8009   1.0000
   0.750   0.4436   0.02188   0.01110  -0.0852   0.7921   1.0000
   1.000   0.4722   0.02208   0.01116  -0.0851   0.7841   1.0000
   1.250   0.4963   0.02243   0.01142  -0.0846   0.7741   1.0000
   1.500   0.5272   0.02253   0.01142  -0.0847   0.7674   1.0000
   1.750   0.5497   0.02293   0.01178  -0.0839   0.7565   1.0000
   2.000   0.5751   0.02323   0.01204  -0.0835   0.7471   1.0000
   2.250   0.6040   0.02337   0.01214  -0.0833   0.7391   1.0000
   2.500   0.6270   0.02376   0.01252  -0.0825   0.7282   1.0000
   2.750   0.6530   0.02401   0.01279  -0.0820   0.7187   1.0000
   3.000   0.6811   0.02413   0.01291  -0.0816   0.7098   1.0000
   3.250   0.7042   0.02450   0.01331  -0.0808   0.6982   1.0000
   3.500   0.7291   0.02476   0.01362  -0.0801   0.6874   1.0000
   3.750   0.7577   0.02481   0.01372  -0.0796   0.6780   1.0000
   4.000   0.7823   0.02504   0.01402  -0.0787   0.6662   1.0000
   4.250   0.8060   0.02533   0.01438  -0.0778   0.6536   1.0000
   4.500   0.8303   0.02555   0.01469  -0.0769   0.6410   1.0000
   4.750   0.8551   0.02573   0.01500  -0.0760   0.6281   1.0000
   5.000   0.8801   0.02586   0.01523  -0.0750   0.6147   1.0000
   5.250   0.9048   0.02599   0.01547  -0.0740   0.6005   1.0000
   5.500   0.9289   0.02613   0.01577  -0.0729   0.5853   1.0000
   5.750   0.9527   0.02626   0.01603  -0.0717   0.5691   1.0000
   6.000   0.9764   0.02637   0.01627  -0.0705   0.5521   1.0000
   6.250   1.0008   0.02642   0.01643  -0.0693   0.5345   1.0000
   6.500   1.0219   0.02668   0.01687  -0.0678   0.5142   1.0000
   6.750   1.0437   0.02687   0.01719  -0.0664   0.4929   1.0000
   7.000   1.0641   0.02716   0.01759  -0.0648   0.4696   1.0000
   7.250   1.0849   0.02742   0.01791  -0.0632   0.4451   1.0000
   7.500   1.1034   0.02785   0.01846  -0.0615   0.4183   1.0000
   7.750   1.1204   0.02844   0.01909  -0.0596   0.3902   1.0000
   8.000   1.1358   0.02916   0.01983  -0.0577   0.3613   1.0000
   8.250   1.1495   0.03006   0.02071  -0.0558   0.3326   1.0000
   8.500   1.1613   0.03112   0.02177  -0.0537   0.3046   1.0000
   8.750   1.1713   0.03234   0.02301  -0.0516   0.2779   1.0000
   9.000   1.1795   0.03370   0.02436  -0.0495   0.2529   1.0000
   9.250   1.1851   0.03517   0.02576  -0.0471   0.2309   1.0000
   9.500   1.1890   0.03679   0.02744  -0.0448   0.2087   1.0000
   9.750   1.1916   0.03858   0.02919  -0.0427   0.1896   1.0000
  10.000   1.1937   0.04057   0.03124  -0.0408   0.1698   1.0000
  10.250   1.1935   0.04279   0.03346  -0.0391   0.1514   1.0000
  10.500   1.1906   0.04529   0.03588  -0.0377   0.1342   1.0000
  10.750   1.1868   0.04807   0.03873  -0.0368   0.1152   1.0000
  11.000   1.1827   0.05107   0.04176  -0.0362   0.0995   1.0000
  11.250   1.1786   0.05433   0.04501  -0.0358   0.0860   1.0000
  11.500   1.1762   0.05762   0.04837  -0.0353   0.0758   1.0000
  11.750   1.1737   0.06107   0.05186  -0.0350   0.0679   1.0000
  12.000   1.1717   0.06453   0.05538  -0.0348   0.0616   1.0000
  12.250   1.1714   0.06801   0.05901  -0.0346   0.0561   1.0000
  12.500   1.1704   0.07157   0.06270  -0.0347   0.0519   1.0000
  12.750   1.1694   0.07514   0.06629  -0.0348   0.0489   1.0000
  13.000   1.1714   0.07887   0.07037  -0.0347   0.0462   1.0000
  13.250   1.1712   0.08287   0.07464  -0.0349   0.0442   1.0000
  13.500   1.1693   0.08713   0.07913  -0.0356   0.0429   1.0000
  13.750   1.1655   0.09169   0.08389  -0.0366   0.0418   1.0000
  14.000   1.1608   0.09647   0.08884  -0.0380   0.0409   1.0000
  14.250   1.1560   0.10138   0.09393  -0.0395   0.0401   1.0000
  14.500   1.1466   0.10735   0.10005  -0.0419   0.0396   1.0000
  14.750   1.1317   0.11471   0.10767  -0.0458   0.0395   1.0000
  15.000   1.1155   0.12284   0.11598  -0.0504   0.0395   1.0000
  15.250   1.0988   0.13157   0.12490  -0.0555   0.0397   1.0000
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