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SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD6080 (9.2%) (sd6080-il)
Reynolds number: 50,000
Max Cl/Cd: 36.09 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd6080-il-50000.txt
Download as CSV file: xf-sd6080-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3457   0.10530   0.09886  -0.0273   1.0000   0.1955
  -8.000  -0.3247   0.09986   0.09342  -0.0258   1.0000   0.2036
  -7.750  -0.3427   0.09981   0.09356  -0.0271   1.0000   0.2103
  -7.500  -0.3220   0.09473   0.08849  -0.0256   1.0000   0.2191
  -7.250  -0.3457   0.09500   0.08899  -0.0253   1.0000   0.2251
  -7.000  -0.3279   0.09045   0.08447  -0.0235   1.0000   0.2349
  -6.750  -0.3600   0.09118   0.08545  -0.0223   1.0000   0.2401
  -6.500  -0.3461   0.08716   0.08145  -0.0190   1.0000   0.2496
  -6.250  -0.3791   0.08788   0.08240  -0.0181   1.0000   0.2552
  -6.000  -0.3690   0.08422   0.07877  -0.0138   1.0000   0.2650
  -5.750  -0.3911   0.08345   0.07815  -0.0127   1.0000   0.2723
  -5.500  -0.3979   0.08185   0.07661  -0.0103   1.0000   0.2842
  -5.250  -0.3977   0.07922   0.07406  -0.0068   1.0000   0.2946
  -5.000  -0.4043   0.07723   0.07215  -0.0048   1.0000   0.3069
  -4.750  -0.4090   0.07517   0.07016  -0.0026   1.0000   0.3225
  -4.500  -0.4149   0.07349   0.06855  -0.0014   1.0000   0.3437
  -4.250  -0.4159   0.07104   0.06617   0.0020   1.0000   0.3645
  -4.000  -0.4188   0.06923   0.06441   0.0040   1.0000   0.3921
  -3.750  -0.4188   0.06697   0.06223   0.0098   1.0000   0.4244
  -3.250  -0.2608   0.04402   0.03661  -0.0477   1.0000   0.1363
  -3.000  -0.2356   0.04052   0.03287  -0.0487   1.0000   0.1288
  -2.750  -0.2031   0.03718   0.02871  -0.0505   1.0000   0.1198
  -2.500  -0.1758   0.03472   0.02574  -0.0512   1.0000   0.1179
  -2.250  -0.1489   0.03292   0.02336  -0.0514   1.0000   0.1210
  -2.000  -0.1252   0.03137   0.02165  -0.0514   1.0000   0.1287
  -1.750  -0.0992   0.03015   0.01990  -0.0511   1.0000   0.1369
  -1.500  -0.0763   0.02899   0.01879  -0.0508   1.0000   0.1562
  -1.250  -0.0525   0.02805   0.01781  -0.0504   1.0000   0.1937
  -1.000  -0.0244   0.02686   0.01695  -0.0506   1.0000   0.2816
  -0.750   0.0083   0.02344   0.01596  -0.0496   0.9954   1.0000
  -0.500   0.0529   0.02451   0.01621  -0.0537   0.9854   1.0000
  -0.250   0.0920   0.02546   0.01663  -0.0570   0.9752   1.0000
   0.000   0.1291   0.02642   0.01720  -0.0599   0.9648   1.0000
   0.250   0.1672   0.02743   0.01787  -0.0630   0.9545   1.0000
   0.500   0.2082   0.02851   0.01864  -0.0665   0.9441   1.0000
   0.750   0.2378   0.02936   0.01928  -0.0680   0.9328   1.0000
   1.000   0.2690   0.03029   0.02002  -0.0697   0.9218   1.0000
   1.250   0.3027   0.03128   0.02084  -0.0718   0.9108   1.0000
   1.500   0.3409   0.03232   0.02173  -0.0746   0.8997   1.0000
   1.750   0.3688   0.03323   0.02255  -0.0756   0.8877   1.0000
   2.000   0.3955   0.03417   0.02342  -0.0765   0.8754   1.0000
   2.250   0.4239   0.03516   0.02433  -0.0775   0.8632   1.0000
   2.500   0.4540   0.03615   0.02529  -0.0787   0.8507   1.0000
   2.750   0.4858   0.03713   0.02624  -0.0801   0.8379   1.0000
   3.000   0.5187   0.03807   0.02718  -0.0815   0.8248   1.0000
   3.250   0.5533   0.03896   0.02808  -0.0830   0.8116   1.0000
   3.500   0.5820   0.03986   0.02902  -0.0836   0.7977   1.0000
   3.750   0.6101   0.04075   0.02998  -0.0840   0.7832   1.0000
   4.000   0.6392   0.04160   0.03089  -0.0845   0.7685   1.0000
   4.250   0.6697   0.04237   0.03173  -0.0849   0.7536   1.0000
   4.500   0.6979   0.04313   0.03258  -0.0850   0.7380   1.0000
   4.750   0.7177   0.04412   0.03369  -0.0841   0.7211   1.0000
   5.000   0.7416   0.04495   0.03463  -0.0836   0.7040   1.0000
   5.250   0.7704   0.04553   0.03534  -0.0833   0.6868   1.0000
   5.500   0.8057   0.04566   0.03564  -0.0832   0.6697   1.0000
   5.750   0.8498   0.04510   0.03533  -0.0833   0.6530   1.0000
   6.000   0.8958   0.04391   0.03438  -0.0827   0.6369   1.0000
   6.250   0.9080   0.04499   0.03560  -0.0806   0.6155   1.0000
   6.500   0.9498   0.04360   0.03450  -0.0792   0.5973   1.0000
   6.750   1.0037   0.04081   0.03199  -0.0777   0.5796   1.0000
   7.000   1.0295   0.04034   0.03172  -0.0754   0.5564   1.0000
   7.250   1.0851   0.03692   0.02855  -0.0736   0.5337   1.0000
   7.500   1.1242   0.03497   0.02673  -0.0714   0.5058   1.0000
   7.750   1.1495   0.03436   0.02626  -0.0688   0.4741   1.0000
   8.000   1.1754   0.03379   0.02573  -0.0663   0.4395   1.0000
   8.250   1.2020   0.03337   0.02518  -0.0639   0.4027   1.0000
   8.500   1.2208   0.03383   0.02556  -0.0614   0.3651   1.0000
   8.750   1.2372   0.03476   0.02639  -0.0589   0.3282   1.0000
   9.000   1.2538   0.03589   0.02726  -0.0566   0.2912   1.0000
   9.250   1.2640   0.03765   0.02897  -0.0539   0.2567   1.0000
   9.500   1.2737   0.03945   0.03053  -0.0513   0.2215   1.0000
   9.750   1.2761   0.04130   0.03218  -0.0483   0.1890   1.0000
  10.000   1.2754   0.04337   0.03412  -0.0452   0.1609   1.0000
  10.250   1.2811   0.04603   0.03657  -0.0429   0.1355   1.0000
  10.500   1.2886   0.04935   0.04013  -0.0406   0.1184   1.0000
  10.750   1.2993   0.05274   0.04364  -0.0390   0.1065   1.0000
  11.000   1.3158   0.05625   0.04712  -0.0381   0.0968   1.0000
  11.250   1.3112   0.06007   0.05151  -0.0355   0.0941   1.0000
  11.500   1.3043   0.06398   0.05584  -0.0330   0.0921   1.0000
  11.750   1.2933   0.06796   0.06017  -0.0308   0.0909   1.0000
  12.000   1.2773   0.07220   0.06473  -0.0290   0.0904   1.0000
  12.250   1.2555   0.07690   0.06973  -0.0280   0.0907   1.0000
  12.500   1.2290   0.08229   0.07539  -0.0282   0.0914   1.0000
  12.750   1.2001   0.08853   0.08187  -0.0297   0.0925   1.0000
  13.000   1.1705   0.09565   0.08917  -0.0324   0.0939   1.0000
  13.250   1.1423   0.10358   0.09722  -0.0362   0.0952   1.0000
  13.500   1.1175   0.11204   0.10575  -0.0405   0.0964   1.0000
  13.750   1.0984   0.12062   0.11436  -0.0448   0.0973   1.0000
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