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Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il)
Reynolds number: 100,000
Max Cl/Cd: 29.88 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eiffel10-il-100000-n5.txt
Download as CSV file: xf-eiffel10-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Eiffel 10 (Wright) - 1903 Wright Flyer airfoil  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3907   0.11113   0.10566  -0.0095   1.0000   0.0218
  -8.500  -0.3828   0.10873   0.10330  -0.0111   1.0000   0.0218
  -8.000  -0.3667   0.10303   0.09769  -0.0131   1.0000   0.0221
  -7.750  -0.3577   0.10017   0.09489  -0.0142   1.0000   0.0224
  -7.500  -0.3471   0.09740   0.09216  -0.0159   1.0000   0.0228
  -7.250  -0.3357   0.09468   0.08949  -0.0178   1.0000   0.0231
  -7.000  -0.3235   0.09198   0.08684  -0.0199   1.0000   0.0236
  -6.750  -0.3106   0.08931   0.08422  -0.0222   1.0000   0.0240
  -6.500  -0.2968   0.08670   0.08167  -0.0247   1.0000   0.0245
  -6.250  -0.2812   0.08431   0.07932  -0.0280   1.0000   0.0250
  -5.750  -0.2586   0.07919   0.07434  -0.0307   1.0000   0.0259
  -5.500  -0.2489   0.07694   0.07216  -0.0315   1.0000   0.0267
  -5.250  -0.2384   0.07485   0.07012  -0.0326   1.0000   0.0276
  -5.000  -0.2104   0.07203   0.06730  -0.0382   0.9970   0.0287
  -4.750  -0.1688   0.06831   0.06355  -0.0466   0.9915   0.0293
  -4.500  -0.1337   0.06444   0.05969  -0.0520   0.9849   0.0307
  -4.250  -0.0595   0.06000   0.05510  -0.0672   0.9722   0.0333
  -4.000  -0.0148   0.05550   0.05058  -0.0737   0.9475   0.0349
  -3.750   0.0345   0.05236   0.04734  -0.0816   0.9307   0.0380
  -3.500   0.0760   0.04902   0.04392  -0.0871   0.9062   0.0395
  -3.250   0.1101   0.04638   0.04122  -0.0905   0.8862   0.0425
  -3.000   0.1531   0.04394   0.03846  -0.0951   0.8363   0.0452
  -2.750   0.1768   0.04164   0.03603  -0.0954   0.7961   0.0482
  -2.500   0.2162   0.03968   0.03368  -0.0988   0.7358   0.0528
  -2.000   0.2646   0.03899   0.03012  -0.1003   0.0476   0.0632
  -1.750   0.3045   0.03733   0.02827  -0.1036   0.0437   0.0720
  -1.500   0.3423   0.03601   0.02680  -0.1062   0.0415   0.0832
  -1.000   0.4025   0.03270   0.02352  -0.1088   0.0373   0.1037
   0.000   0.5488   0.02737   0.01730  -0.1137   0.0330   0.0580
   0.250   0.5829   0.02625   0.01586  -0.1139   0.0328   0.0435
   0.500   0.6126   0.02573   0.01519  -0.1139   0.0327   0.0421
   0.750   0.6416   0.02540   0.01465  -0.1136   0.0327   0.0410
   1.000   0.6700   0.02528   0.01419  -0.1130   0.0328   0.0383
   1.250   0.6964   0.02528   0.01405  -0.1123   0.0330   0.0372
   1.500   0.7232   0.02545   0.01405  -0.1115   0.0333   0.0362
   1.750   0.7502   0.02576   0.01425  -0.1107   0.0337   0.0357
   2.000   0.7775   0.02626   0.01467  -0.1100   0.0342   0.0356
   2.250   0.8043   0.02694   0.01527  -0.1091   0.0349   0.0372
   2.500   0.8313   0.02782   0.01608  -0.1082   0.0357   0.0395
   2.750   0.8587   0.02893   0.01713  -0.1074   0.0365   0.0410
   3.000   0.8862   0.03035   0.01846  -0.1068   0.0373   0.0429
   3.250   0.9135   0.03172   0.01984  -0.1061   0.0375   0.0464
   3.500   0.9405   0.03281   0.02114  -0.1052   0.0369   0.0582
   3.750   0.9638   0.03290   0.02277  -0.1040   0.0366   1.0000
   4.000   0.9898   0.03521   0.02499  -0.1033   0.0376   1.0000
   4.250   1.0178   0.03663   0.02686  -0.1016   0.0425   1.0000
   4.500   1.0427   0.04013   0.03023  -0.1012   0.0452   1.0000
   5.000   1.1318   0.04425   0.03663  -0.0948   0.1639   1.0000
   5.500   1.1694   0.05013   0.04271  -0.0929   0.1430   1.0000
   6.000   1.1956   0.05635   0.04914  -0.0910   0.1121   1.0000
   7.500   1.2392   0.07791   0.07189  -0.0839   0.0716   1.0000
   7.750   1.2431   0.08164   0.07573  -0.0828   0.0691   1.0000
   8.000   1.2512   0.08590   0.07995  -0.0821   0.0673   1.0000
   8.250   1.2719   0.09525   0.08890  -0.0835   0.0655   1.0000
   8.500   1.2488   0.09728   0.09147  -0.0809   0.0651   1.0000
   8.750   1.2186   0.10025   0.09484  -0.0792   0.0644   1.0000
   9.000   1.1936   0.10435   0.09908  -0.0783   0.0642   1.0000
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