Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SD8000-089-88 (sd8000-il)
Reynolds number: 200,000
Max Cl/Cd: 64.17 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd8000-il-200000.txt
Download as CSV file: xf-sd8000-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD8000-089-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5121   0.10357   0.09995  -0.0210   1.0000   0.0555
  -9.750  -0.5171   0.09868   0.09511  -0.0252   1.0000   0.0557
  -9.500  -0.5202   0.09368   0.09015  -0.0289   1.0000   0.0558
  -9.250  -0.5174   0.08852   0.08501  -0.0271   1.0000   0.0570
  -9.000  -0.5092   0.08576   0.08227  -0.0262   1.0000   0.0580
  -8.750  -0.5052   0.08259   0.07912  -0.0267   1.0000   0.0590
  -8.500  -0.5060   0.07880   0.07537  -0.0283   1.0000   0.0599
  -8.250  -0.5919   0.05172   0.04797  -0.0489   1.0000   0.0339
  -8.000  -0.5989   0.04653   0.04257  -0.0491   1.0000   0.0329
  -7.750  -0.6065   0.04070   0.03636  -0.0484   1.0000   0.0318
  -7.500  -0.6106   0.03483   0.02993  -0.0467   1.0000   0.0310
  -7.250  -0.6055   0.03059   0.02515  -0.0448   1.0000   0.0310
  -7.000  -0.5929   0.02818   0.02233  -0.0430   1.0000   0.0327
  -6.750  -0.5776   0.02629   0.01997  -0.0412   1.0000   0.0345
  -6.500  -0.5626   0.02335   0.01657  -0.0396   1.0000   0.0359
  -6.250  -0.5444   0.02165   0.01478  -0.0383   1.0000   0.0381
  -6.000  -0.5244   0.02055   0.01353  -0.0370   1.0000   0.0411
  -5.750  -0.5037   0.01961   0.01230  -0.0357   1.0000   0.0452
  -5.500  -0.4834   0.01830   0.01099  -0.0347   1.0000   0.0498
  -5.250  -0.4616   0.01779   0.01029  -0.0335   1.0000   0.0554
  -5.000  -0.4406   0.01662   0.00914  -0.0326   1.0000   0.0617
  -4.750  -0.4184   0.01611   0.00849  -0.0315   1.0000   0.0688
  -4.500  -0.3965   0.01532   0.00776  -0.0307   1.0000   0.0772
  -4.250  -0.3741   0.01469   0.00712  -0.0299   1.0000   0.0869
  -4.000  -0.3516   0.01419   0.00659  -0.0290   1.0000   0.0978
  -3.750  -0.3291   0.01379   0.00620  -0.0283   1.0000   0.1111
  -3.500  -0.3068   0.01337   0.00585  -0.0276   1.0000   0.1267
  -3.250  -0.2838   0.01301   0.00556  -0.0270   0.9998   0.1464
  -3.000  -0.2441   0.01259   0.00531  -0.0298   0.9951   0.1840
  -2.750  -0.2059   0.01210   0.00513  -0.0324   0.9898   0.2457
  -2.500  -0.1667   0.01159   0.00507  -0.0352   0.9848   0.3490
  -2.250  -0.1308   0.01112   0.00507  -0.0372   0.9786   0.4663
  -2.000  -0.0928   0.01076   0.00514  -0.0393   0.9727   0.5820
  -1.750  -0.0588   0.01049   0.00520  -0.0402   0.9657   0.6760
  -1.500  -0.0224   0.01027   0.00525  -0.0414   0.9593   0.7611
  -1.250   0.0103   0.01010   0.00528  -0.0415   0.9518   0.8318
  -1.000   0.0501   0.00998   0.00525  -0.0430   0.9459   0.8987
  -0.750   0.1094   0.00988   0.00514  -0.0486   0.9441   0.9525
  -0.500   0.1750   0.00972   0.00492  -0.0559   0.9426   0.9835
  -0.250   0.2272   0.00954   0.00469  -0.0607   0.9353   1.0000
   0.000   0.2668   0.00932   0.00442  -0.0628   0.9265   1.0000
   0.250   0.2964   0.00915   0.00420  -0.0627   0.9138   1.0000
   0.500   0.3214   0.00901   0.00401  -0.0617   0.8995   1.0000
   0.750   0.3450   0.00889   0.00385  -0.0604   0.8845   1.0000
   1.000   0.3682   0.00879   0.00369  -0.0589   0.8690   1.0000
   1.250   0.3907   0.00872   0.00358  -0.0573   0.8510   1.0000
   1.500   0.4139   0.00867   0.00348  -0.0558   0.8315   1.0000
   1.750   0.4382   0.00862   0.00337  -0.0545   0.8114   1.0000
   2.000   0.4624   0.00862   0.00331  -0.0532   0.7877   1.0000
   2.250   0.4870   0.00864   0.00325  -0.0520   0.7626   1.0000
   2.500   0.5116   0.00872   0.00322  -0.0509   0.7343   1.0000
   2.750   0.5361   0.00884   0.00324  -0.0498   0.7024   1.0000
   3.000   0.5604   0.00901   0.00328  -0.0487   0.6672   1.0000
   3.250   0.5846   0.00924   0.00336  -0.0477   0.6295   1.0000
   3.500   0.6084   0.00953   0.00348  -0.0466   0.5889   1.0000
   3.750   0.6321   0.00985   0.00363  -0.0456   0.5459   1.0000
   4.000   0.6555   0.01022   0.00382  -0.0446   0.5016   1.0000
   4.250   0.6787   0.01065   0.00404  -0.0437   0.4565   1.0000
   4.500   0.7017   0.01111   0.00432  -0.0428   0.4117   1.0000
   4.750   0.7247   0.01160   0.00463  -0.0419   0.3684   1.0000
   5.000   0.7478   0.01211   0.00497  -0.0411   0.3271   1.0000
   5.250   0.7708   0.01266   0.00535  -0.0404   0.2897   1.0000
   5.500   0.7939   0.01322   0.00578  -0.0397   0.2558   1.0000
   5.750   0.8169   0.01381   0.00625  -0.0389   0.2264   1.0000
   6.000   0.8399   0.01442   0.00675  -0.0382   0.2006   1.0000
   6.250   0.8625   0.01509   0.00729  -0.0375   0.1788   1.0000
   6.500   0.8857   0.01571   0.00789  -0.0368   0.1593   1.0000
   6.750   0.9086   0.01634   0.00850  -0.0360   0.1418   1.0000
   7.000   0.9311   0.01701   0.00913  -0.0353   0.1262   1.0000
   7.250   0.9535   0.01768   0.00977  -0.0346   0.1117   1.0000
   7.500   0.9757   0.01838   0.01049  -0.0338   0.0986   1.0000
   7.750   0.9974   0.01915   0.01127  -0.0329   0.0868   1.0000
   8.000   1.0182   0.02003   0.01217  -0.0320   0.0758   1.0000
   8.250   1.0382   0.02103   0.01318  -0.0309   0.0658   1.0000
   8.500   1.0564   0.02235   0.01445  -0.0297   0.0574   1.0000
   8.750   1.0772   0.02327   0.01553  -0.0286   0.0510   1.0000
   9.000   1.0944   0.02498   0.01721  -0.0273   0.0462   1.0000
   9.250   1.1144   0.02600   0.01842  -0.0262   0.0422   1.0000
   9.500   1.1331   0.02730   0.01977  -0.0251   0.0395   1.0000
   9.750   1.1500   0.03013   0.02267  -0.0240   0.0371   1.0000
  10.000   1.1677   0.03164   0.02448  -0.0226   0.0357   1.0000
  10.250   1.1836   0.03327   0.02637  -0.0212   0.0339   1.0000
  10.500   1.1980   0.03484   0.02811  -0.0198   0.0322   1.0000
  10.750   1.2110   0.03668   0.03010  -0.0183   0.0310   1.0000
  11.000   1.2220   0.03902   0.03259  -0.0169   0.0300   1.0000
  11.250   1.2268   0.04258   0.03641  -0.0151   0.0293   1.0000
  11.500   1.2218   0.04699   0.04119  -0.0127   0.0290   1.0000
  11.750   1.2106   0.04996   0.04447  -0.0094   0.0287   1.0000
  12.000   1.1980   0.05281   0.04760  -0.0066   0.0286   1.0000
  12.250   1.1833   0.05575   0.05080  -0.0047   0.0284   1.0000
  12.500   1.1653   0.05977   0.05507  -0.0039   0.0284   1.0000
  12.750   1.1461   0.06445   0.05998  -0.0044   0.0284   1.0000
  13.000   1.1245   0.06996   0.06570  -0.0063   0.0285   1.0000
  13.250   1.1014   0.07651   0.07244  -0.0095   0.0286   1.0000
  13.500   1.0761   0.08443   0.08053  -0.0141   0.0288   1.0000
<< Back to SD8000-089-88 (sd8000-il)

Polar data table (+)

Polar graphs


<< Back to SD8000-089-88 (sd8000-il)