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SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SD8000-089-88 (sd8000-il)
Reynolds number: 100,000
Max Cl/Cd: 49.31 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd8000-il-100000.txt
Download as CSV file: xf-sd8000-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4808   0.09740   0.09237  -0.0167   1.0000   0.1173
  -8.750  -0.4996   0.09415   0.08925  -0.0223   1.0000   0.1221
  -8.500  -0.5347   0.09018   0.08545  -0.0319   1.0000   0.1230
  -8.250  -0.4810   0.08678   0.08192  -0.0206   1.0000   0.1310
  -8.000  -0.4946   0.08327   0.07852  -0.0240   1.0000   0.1351
  -7.750  -0.5274   0.07797   0.07326  -0.0351   1.0000   0.1370
  -7.500  -0.4949   0.07596   0.07133  -0.0253   1.0000   0.1440
  -7.250  -0.5611   0.05052   0.04484  -0.0461   1.0000   0.0677
  -7.000  -0.5558   0.04581   0.03993  -0.0454   1.0000   0.0670
  -6.750  -0.5498   0.04155   0.03521  -0.0444   1.0000   0.0674
  -6.500  -0.5403   0.03792   0.03098  -0.0430   1.0000   0.0681
  -6.250  -0.5287   0.03355   0.02618  -0.0418   1.0000   0.0689
  -6.000  -0.5124   0.03100   0.02360  -0.0407   1.0000   0.0721
  -5.750  -0.4944   0.02914   0.02141  -0.0394   1.0000   0.0778
  -5.500  -0.4749   0.02667   0.01824  -0.0379   1.0000   0.0817
  -5.250  -0.4553   0.02502   0.01666  -0.0370   1.0000   0.0893
  -5.000  -0.4335   0.02317   0.01435  -0.0357   1.0000   0.0961
  -4.750  -0.4122   0.02204   0.01318  -0.0347   1.0000   0.1063
  -4.500  -0.3901   0.02067   0.01173  -0.0337   1.0000   0.1161
  -4.250  -0.3679   0.01965   0.01066  -0.0327   1.0000   0.1294
  -4.000  -0.3455   0.01870   0.00969  -0.0318   1.0000   0.1440
  -3.750  -0.3231   0.01788   0.00889  -0.0309   1.0000   0.1622
  -3.500  -0.3006   0.01709   0.00816  -0.0300   1.0000   0.1843
  -3.250  -0.2781   0.01636   0.00756  -0.0292   1.0000   0.2127
  -3.000  -0.2558   0.01566   0.00708  -0.0284   1.0000   0.2547
  -2.750  -0.2342   0.01484   0.00672  -0.0276   1.0000   0.3199
  -2.500  -0.2136   0.01402   0.00654  -0.0265   1.0000   0.4359
  -2.250  -0.1958   0.01342   0.00658  -0.0245   1.0000   0.5777
  -2.000  -0.1803   0.01312   0.00672  -0.0214   1.0000   0.6980
  -1.750  -0.1676   0.01294   0.00686  -0.0175   1.0000   0.8073
  -1.500  -0.1251   0.01272   0.00677  -0.0193   1.0000   0.9795
  -1.250  -0.1016   0.01282   0.00663  -0.0197   1.0000   1.0000
  -1.000  -0.0807   0.01300   0.00662  -0.0194   1.0000   1.0000
  -0.750  -0.0599   0.01322   0.00668  -0.0191   1.0000   1.0000
  -0.500  -0.0394   0.01350   0.00681  -0.0187   1.0000   1.0000
  -0.250   0.0120   0.01404   0.00720  -0.0241   0.9890   1.0000
   0.000   0.0627   0.01452   0.00756  -0.0292   0.9775   1.0000
   0.250   0.1128   0.01491   0.00786  -0.0340   0.9654   1.0000
   0.500   0.1628   0.01521   0.00809  -0.0386   0.9529   1.0000
   0.750   0.2139   0.01540   0.00825  -0.0432   0.9404   1.0000
   1.000   0.2672   0.01544   0.00829  -0.0479   0.9280   1.0000
   1.250   0.3172   0.01534   0.00822  -0.0518   0.9140   1.0000
   1.500   0.3652   0.01514   0.00806  -0.0550   0.8995   1.0000
   1.750   0.4087   0.01486   0.00783  -0.0571   0.8842   1.0000
   2.000   0.4448   0.01459   0.00761  -0.0576   0.8664   1.0000
   2.250   0.4764   0.01431   0.00737  -0.0572   0.8460   1.0000
   2.500   0.5085   0.01395   0.00703  -0.0566   0.8259   1.0000
   2.750   0.5350   0.01372   0.00683  -0.0550   0.8010   1.0000
   3.000   0.5615   0.01349   0.00660  -0.0535   0.7743   1.0000
   3.250   0.5870   0.01335   0.00643  -0.0518   0.7437   1.0000
   3.500   0.6120   0.01329   0.00632  -0.0500   0.7092   1.0000
   3.750   0.6359   0.01337   0.00629  -0.0483   0.6694   1.0000
   4.000   0.6593   0.01355   0.00633  -0.0466   0.6258   1.0000
   4.250   0.6820   0.01385   0.00645  -0.0449   0.5786   1.0000
   4.500   0.7042   0.01428   0.00666  -0.0433   0.5297   1.0000
   4.750   0.7258   0.01480   0.00697  -0.0418   0.4786   1.0000
   5.000   0.7471   0.01543   0.00735  -0.0404   0.4294   1.0000
   5.250   0.7682   0.01615   0.00781  -0.0390   0.3833   1.0000
   5.500   0.7895   0.01693   0.00840  -0.0378   0.3406   1.0000
   5.750   0.8109   0.01778   0.00905  -0.0367   0.3030   1.0000
   6.000   0.8325   0.01865   0.00976  -0.0357   0.2698   1.0000
   6.250   0.8544   0.01957   0.01055  -0.0347   0.2413   1.0000
   6.500   0.8766   0.02056   0.01144  -0.0338   0.2170   1.0000
   6.750   0.8988   0.02155   0.01236  -0.0330   0.1952   1.0000
   7.000   0.9212   0.02268   0.01340  -0.0322   0.1762   1.0000
   7.250   0.9432   0.02376   0.01455  -0.0312   0.1580   1.0000
   7.500   0.9651   0.02493   0.01576  -0.0303   0.1418   1.0000
   7.750   0.9862   0.02612   0.01696  -0.0294   0.1266   1.0000
   8.000   1.0071   0.02744   0.01832  -0.0285   0.1127   1.0000
   8.250   1.0275   0.02895   0.01993  -0.0274   0.1004   1.0000
   8.500   1.0477   0.03069   0.02177  -0.0264   0.0898   1.0000
   8.750   1.0691   0.03294   0.02396  -0.0258   0.0817   1.0000
   9.000   1.0862   0.03465   0.02612  -0.0241   0.0747   1.0000
   9.250   1.1060   0.03748   0.02888  -0.0236   0.0694   1.0000
   9.500   1.1181   0.04029   0.03234  -0.0215   0.0667   1.0000
   9.750   1.1281   0.04337   0.03591  -0.0196   0.0640   1.0000
  10.000   1.1413   0.04565   0.03836  -0.0183   0.0608   1.0000
  10.250   1.1524   0.04944   0.04217  -0.0175   0.0580   1.0000
  10.500   1.1497   0.05341   0.04663  -0.0152   0.0575   1.0000
  10.750   1.1418   0.05747   0.05115  -0.0128   0.0572   1.0000
  11.000   1.1297   0.06173   0.05577  -0.0105   0.0572   1.0000
  11.250   1.1126   0.06580   0.06011  -0.0082   0.0573   1.0000
  11.500   1.0927   0.07010   0.06460  -0.0066   0.0575   1.0000
  11.750   1.0723   0.07502   0.06970  -0.0063   0.0577   1.0000
  12.000   1.0477   0.07967   0.07458  -0.0075   0.0582   1.0000
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