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E230 (9.96%) (e230-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E230 (9.96%) (e230-il)
Reynolds number: 100,000
Max Cl/Cd: 32.62 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e230-il-100000.txt
Download as CSV file: xf-e230-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E230  (9.96%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.7082   0.08491   0.08067   0.0062   1.0000   0.0562
 -10.500  -0.7321   0.07626   0.07197   0.0015   1.0000   0.0545
 -10.250  -0.8606   0.07511   0.07039  -0.0013   1.0000   0.0561
 -10.000  -0.8778   0.07035   0.06553  -0.0018   1.0000   0.0549
  -9.750  -0.8988   0.06587   0.06089  -0.0008   1.0000   0.0537
  -9.500  -0.9190   0.06088   0.05562   0.0009   1.0000   0.0518
  -9.250  -0.9543   0.05474   0.04845   0.0050   1.0000   0.0475
  -9.000  -0.9463   0.05114   0.04452   0.0066   1.0000   0.0464
  -8.750  -0.9402   0.04665   0.03970   0.0081   1.0000   0.0458
  -8.500  -0.9312   0.04278   0.03542   0.0099   1.0000   0.0453
  -8.250  -0.9194   0.03978   0.03191   0.0118   1.0000   0.0460
  -8.000  -0.9046   0.03751   0.02910   0.0137   1.0000   0.0469
  -7.750  -0.8853   0.03356   0.02486   0.0146   1.0000   0.0479
  -7.500  -0.8622   0.03069   0.02182   0.0153   1.0000   0.0493
  -7.250  -0.8378   0.02842   0.01942   0.0160   1.0000   0.0513
  -7.000  -0.8130   0.02645   0.01732   0.0167   1.0000   0.0542
  -6.750  -0.7883   0.02477   0.01544   0.0177   1.0000   0.0582
  -6.500  -0.7687   0.02290   0.01370   0.0190   1.0000   0.0681
  -6.250  -0.7521   0.02094   0.01193   0.0209   1.0000   0.0881
  -6.000  -0.7402   0.01862   0.01018   0.0234   1.0000   0.1634
  -5.750  -0.7231   0.01757   0.00950   0.0248   1.0000   0.2359
  -5.500  -0.7060   0.01685   0.00909   0.0265   1.0000   0.3010
  -5.250  -0.6872   0.01617   0.00857   0.0281   1.0000   0.3558
  -5.000  -0.6678   0.01553   0.00812   0.0297   1.0000   0.4060
  -4.750  -0.6480   0.01498   0.00771   0.0313   1.0000   0.4567
  -4.500  -0.6279   0.01445   0.00739   0.0331   1.0000   0.5051
  -4.250  -0.6076   0.01399   0.00708   0.0349   1.0000   0.5533
  -4.000  -0.5872   0.01360   0.00685   0.0367   1.0000   0.6015
  -3.750  -0.5668   0.01327   0.00667   0.0387   1.0000   0.6494
  -3.500  -0.5454   0.01302   0.00657   0.0406   1.0000   0.6956
  -3.250  -0.5225   0.01287   0.00651   0.0423   1.0000   0.7401
  -3.000  -0.4971   0.01285   0.00655   0.0437   1.0000   0.7825
  -2.750  -0.4633   0.01302   0.00673   0.0436   1.0000   0.8202
  -2.500  -0.4251   0.01332   0.00697   0.0427   1.0000   0.8536
  -2.250  -0.3759   0.01378   0.00732   0.0397   1.0000   0.8792
  -2.000  -0.3277   0.01421   0.00763   0.0367   1.0000   0.9020
  -1.750  -0.2660   0.01462   0.00789   0.0309   1.0000   0.9176
  -1.500  -0.2080   0.01485   0.00802   0.0254   1.0000   0.9329
  -1.250  -0.1521   0.01492   0.00800   0.0199   1.0000   0.9483
  -1.000  -0.0968   0.01484   0.00788   0.0142   1.0000   0.9635
  -0.750  -0.0408   0.01460   0.00763   0.0081   1.0000   0.9781
  -0.500   0.0165   0.01421   0.00726   0.0014   1.0000   0.9920
  -0.250   0.0589   0.01385   0.00695  -0.0032   1.0000   1.0000
   0.000   0.0525   0.01408   0.00722   0.0001   1.0000   1.0000
   0.250   0.1068   0.01400   0.00720  -0.0065   0.9781   1.0000
   0.500   0.1678   0.01383   0.00710  -0.0135   0.9505   1.0000
   0.750   0.2035   0.01378   0.00704  -0.0150   0.9163   1.0000
   1.000   0.2184   0.01380   0.00704  -0.0123   0.8817   1.0000
   1.250   0.2303   0.01381   0.00702  -0.0089   0.8514   1.0000
   1.500   0.2426   0.01381   0.00699  -0.0054   0.8232   1.0000
   1.750   0.2563   0.01379   0.00694  -0.0022   0.7964   1.0000
   2.000   0.2716   0.01377   0.00687   0.0008   0.7697   1.0000
   2.250   0.2889   0.01376   0.00682   0.0033   0.7414   1.0000
   2.500   0.3072   0.01377   0.00678   0.0056   0.7128   1.0000
   2.750   0.3265   0.01379   0.00678   0.0077   0.6834   1.0000
   3.000   0.3466   0.01383   0.00676   0.0097   0.6528   1.0000
   3.250   0.3671   0.01390   0.00676   0.0115   0.6210   1.0000
   3.500   0.3884   0.01401   0.00682   0.0131   0.5862   1.0000
   3.750   0.4101   0.01416   0.00693   0.0147   0.5495   1.0000
   4.000   0.4320   0.01436   0.00705   0.0161   0.5105   1.0000
   4.250   0.4540   0.01462   0.00720   0.0174   0.4686   1.0000
   4.500   0.4761   0.01494   0.00742   0.0186   0.4226   1.0000
   4.750   0.4981   0.01536   0.00773   0.0197   0.3729   1.0000
   5.000   0.5197   0.01593   0.00811   0.0207   0.3208   1.0000
   5.250   0.5408   0.01663   0.00858   0.0217   0.2632   1.0000
   5.500   0.5614   0.01736   0.00906   0.0223   0.1983   1.0000
   5.750   0.5807   0.01860   0.00997   0.0232   0.1374   1.0000
   6.000   0.5981   0.02060   0.01165   0.0246   0.0878   1.0000
   6.250   0.6171   0.02209   0.01302   0.0260   0.0719   1.0000
   6.500   0.6372   0.02384   0.01479   0.0275   0.0651   1.0000
   6.750   0.6584   0.02544   0.01647   0.0288   0.0607   1.0000
   7.000   0.6792   0.02753   0.01857   0.0300   0.0579   1.0000
   7.250   0.6994   0.03011   0.02137   0.0313   0.0562   1.0000
   7.500   0.7182   0.03208   0.02380   0.0328   0.0541   1.0000
   7.750   0.7347   0.03450   0.02663   0.0342   0.0523   1.0000
   8.000   0.7479   0.03761   0.03020   0.0358   0.0522   1.0000
   8.250   0.7572   0.04120   0.03424   0.0375   0.0528   1.0000
   8.500   0.7620   0.04516   0.03862   0.0391   0.0536   1.0000
   8.750   0.7637   0.04927   0.04306   0.0406   0.0547   1.0000
   9.000   0.7636   0.05361   0.04762   0.0418   0.0558   1.0000
   9.250   0.7678   0.05748   0.05172   0.0429   0.0578   1.0000
   9.500   0.7037   0.06491   0.05981   0.0431   0.0622   1.0000
   9.750   0.6692   0.07082   0.06580   0.0404   0.0636   1.0000
  10.000   0.6428   0.07885   0.07383   0.0345   0.0658   1.0000
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