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GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il)
Reynolds number: 50,000
Max Cl/Cd: 38.01 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe100-il-50000-n5.txt
Download as CSV file: xf-goe100-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 100 (SOPWITH) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3893   0.10338   0.09693  -0.0214   1.0000   0.0796
  -7.500  -0.3956   0.10180   0.09549  -0.0238   1.0000   0.0811
  -7.250  -0.3969   0.09971   0.09348  -0.0274   1.0000   0.0817
  -7.000  -0.3948   0.09717   0.09100  -0.0305   1.0000   0.0819
  -6.750  -0.3879   0.09215   0.08607  -0.0278   1.0000   0.0829
  -6.500  -0.3821   0.08837   0.08234  -0.0266   1.0000   0.0841
  -6.250  -0.3770   0.08508   0.07909  -0.0267   1.0000   0.0852
  -6.000  -0.3714   0.08186   0.07591  -0.0275   1.0000   0.0858
  -5.750  -0.3588   0.07660   0.07055  -0.0304   1.0000   0.0521
  -5.500  -0.3431   0.07179   0.06562  -0.0353   1.0000   0.0423
  -5.250  -0.3364   0.06835   0.06221  -0.0342   1.0000   0.0408
  -5.000  -0.3253   0.06471   0.05852  -0.0348   1.0000   0.0394
  -4.750  -0.3107   0.06089   0.05462  -0.0362   1.0000   0.0384
  -4.500  -0.2935   0.05704   0.05062  -0.0377   1.0000   0.0383
  -4.250  -0.2738   0.05318   0.04657  -0.0392   1.0000   0.0388
  -4.000  -0.2518   0.04926   0.04241  -0.0408   1.0000   0.0394
  -3.750  -0.2280   0.04532   0.03812  -0.0421   1.0000   0.0397
  -3.500  -0.2023   0.04138   0.03380  -0.0433   1.0000   0.0397
  -3.250  -0.1745   0.03751   0.02942  -0.0444   1.0000   0.0399
  -3.000  -0.1450   0.03388   0.02518  -0.0452   1.0000   0.0407
  -2.750  -0.1151   0.03082   0.02146  -0.0457   1.0000   0.0441
  -2.500  -0.0885   0.02903   0.01933  -0.0458   1.0000   0.0508
  -2.250  -0.0568   0.02653   0.01610  -0.0459   1.0000   0.0563
  -2.000  -0.0298   0.02525   0.01463  -0.0459   1.0000   0.0729
  -1.750  -0.0023   0.02433   0.01353  -0.0456   1.0000   0.1016
  -1.500   0.0240   0.02392   0.01289  -0.0454   1.0000   0.1327
  -1.250   0.0512   0.02338   0.01200  -0.0451   1.0000   0.1525
  -1.000   0.0773   0.02286   0.01136  -0.0448   1.0000   0.1715
  -0.750   0.1033   0.02239   0.01080  -0.0447   1.0000   0.1979
  -0.500   0.1293   0.02193   0.01048  -0.0449   1.0000   0.2462
   0.000   0.1910   0.01979   0.01001  -0.0467   0.9895   1.0000
   0.250   0.2361   0.02014   0.00992  -0.0505   0.9786   1.0000
   0.500   0.2801   0.02036   0.00982  -0.0540   0.9640   1.0000
   0.750   0.3241   0.02050   0.00974  -0.0573   0.9480   1.0000
   1.000   0.3682   0.02057   0.00965  -0.0605   0.9320   1.0000
   1.250   0.4118   0.02056   0.00953  -0.0634   0.9163   1.0000
   1.500   0.4564   0.02046   0.00937  -0.0664   0.9004   1.0000
   1.750   0.4930   0.02033   0.00925  -0.0675   0.8806   1.0000
   2.000   0.5316   0.02009   0.00902  -0.0688   0.8603   1.0000
   2.250   0.5639   0.01989   0.00885  -0.0688   0.8357   1.0000
   2.500   0.5948   0.01967   0.00871  -0.0684   0.8079   1.0000
   2.750   0.6243   0.01947   0.00856  -0.0677   0.7759   1.0000
   3.000   0.6512   0.01934   0.00848  -0.0666   0.7363   1.0000
   3.250   0.6801   0.01920   0.00837  -0.0657   0.6891   1.0000
   3.500   0.7098   0.01916   0.00818  -0.0647   0.6311   1.0000
   3.750   0.7365   0.01942   0.00816  -0.0635   0.5691   1.0000
   4.000   0.7595   0.01998   0.00845  -0.0620   0.5144   1.0000
   4.250   0.7815   0.02068   0.00901  -0.0606   0.4664   1.0000
   4.500   0.8033   0.02141   0.00964  -0.0595   0.4265   1.0000
   4.750   0.8242   0.02219   0.01028  -0.0582   0.3880   1.0000
   5.000   0.8413   0.02304   0.01084  -0.0566   0.3348   1.0000
   5.250   0.8596   0.02388   0.01144  -0.0552   0.2886   1.0000
   5.500   0.8794   0.02467   0.01214  -0.0542   0.2469   1.0000
   5.750   0.9014   0.02537   0.01289  -0.0533   0.2205   1.0000
   6.000   0.9223   0.02617   0.01360  -0.0524   0.1838   1.0000
   6.250   0.9446   0.02692   0.01436  -0.0515   0.1531   1.0000
   6.500   0.9636   0.02836   0.01526  -0.0506   0.0467   1.0000
   6.750   0.9821   0.03039   0.01712  -0.0494   0.0306   1.0000
   7.000   1.0021   0.03197   0.01908  -0.0482   0.0277   1.0000
   7.250   1.0205   0.03366   0.02108  -0.0468   0.0265   1.0000
   7.500   1.0370   0.03538   0.02310  -0.0452   0.0258   1.0000
   7.750   1.0516   0.03711   0.02516  -0.0435   0.0253   1.0000
   8.000   1.0633   0.03899   0.02734  -0.0415   0.0245   1.0000
   8.250   1.0722   0.04099   0.02964  -0.0394   0.0237   1.0000
   8.500   1.0784   0.04311   0.03202  -0.0370   0.0229   1.0000
   8.750   1.0827   0.04530   0.03445  -0.0346   0.0223   1.0000
   9.000   1.0848   0.04748   0.03684  -0.0319   0.0220   1.0000
   9.250   1.0870   0.04971   0.03927  -0.0294   0.0220   1.0000
   9.500   1.0903   0.05203   0.04181  -0.0272   0.0220   1.0000
   9.750   1.0947   0.05447   0.04446  -0.0252   0.0221   1.0000
  10.000   1.1002   0.05702   0.04725  -0.0234   0.0222   1.0000
  10.250   1.1058   0.05974   0.05022  -0.0218   0.0223   1.0000
  10.500   1.1102   0.06270   0.05360  -0.0204   0.0225   1.0000
  10.750   1.1120   0.06595   0.05715  -0.0193   0.0227   1.0000
  11.000   1.1105   0.06954   0.06102  -0.0186   0.0229   1.0000
  11.250   1.1059   0.07352   0.06528  -0.0184   0.0231   1.0000
  11.500   1.0985   0.07791   0.06994  -0.0189   0.0233   1.0000
  11.750   1.0889   0.08280   0.07508  -0.0202   0.0235   1.0000
  12.000   1.0776   0.08822   0.08072  -0.0224   0.0237   1.0000
  12.250   1.0651   0.09421   0.08693  -0.0254   0.0238   1.0000
  12.500   1.0522   0.10072   0.09363  -0.0291   0.0239   1.0000
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