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


Details Polar file
Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il)
Reynolds number: 100,000
Max Cl/Cd: 50.92 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe100-il-100000-n5.txt
Download as CSV file: xf-goe100-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3786   0.09488   0.09031  -0.0218   1.0000   0.0377
  -7.250  -0.3814   0.09234   0.08786  -0.0217   1.0000   0.0380
  -7.000  -0.3815   0.08950   0.08509  -0.0224   1.0000   0.0383
  -6.750  -0.3805   0.08655   0.08220  -0.0234   1.0000   0.0385
  -6.500  -0.3788   0.08353   0.07924  -0.0244   1.0000   0.0385
  -6.250  -0.3764   0.08045   0.07620  -0.0253   1.0000   0.0382
  -6.000  -0.3731   0.07725   0.07303  -0.0263   1.0000   0.0376
  -5.500  -0.3597   0.06871   0.06442  -0.0295   1.0000   0.0233
  -5.250  -0.3517   0.06538   0.06107  -0.0299   1.0000   0.0222
  -5.000  -0.3403   0.06174   0.05738  -0.0311   1.0000   0.0213
  -4.750  -0.3256   0.05789   0.05344  -0.0326   1.0000   0.0208
  -4.500  -0.3078   0.05391   0.04934  -0.0344   1.0000   0.0208
  -4.250  -0.2825   0.04943   0.04467  -0.0373   0.9991   0.0212
  -4.000  -0.2447   0.04405   0.03898  -0.0422   0.9960   0.0213
  -3.750  -0.2069   0.03865   0.03316  -0.0463   0.9930   0.0208
  -3.500  -0.1688   0.03311   0.02708  -0.0495   0.9904   0.0204
  -3.250  -0.1302   0.02804   0.02125  -0.0519   0.9885   0.0203
  -3.000  -0.0923   0.02412   0.01649  -0.0536   0.9871   0.0209
  -2.750  -0.0572   0.02160   0.01329  -0.0546   0.9846   0.0236
  -2.500  -0.0217   0.02011   0.01152  -0.0560   0.9814   0.0274
  -2.250   0.0176   0.01885   0.00996  -0.0579   0.9779   0.0347
  -2.000   0.0539   0.01786   0.00886  -0.0595   0.9717   0.0579
  -1.750   0.0917   0.01752   0.00856  -0.0619   0.9660   0.0986
  -1.500   0.1256   0.01709   0.00801  -0.0631   0.9596   0.1114
  -1.250   0.1637   0.01673   0.00759  -0.0652   0.9554   0.1303
  -1.000   0.1952   0.01639   0.00724  -0.0659   0.9473   0.1585
  -0.750   0.2365   0.01594   0.00675  -0.0685   0.9397   0.2001
  -0.500   0.2765   0.01541   0.00632  -0.0708   0.9297   0.2544
   0.250   0.3869   0.01306   0.00543  -0.0748   0.9005   1.0000
   0.500   0.4194   0.01295   0.00518  -0.0754   0.8868   1.0000
   0.750   0.4507   0.01284   0.00495  -0.0756   0.8711   1.0000
   1.000   0.4793   0.01277   0.00479  -0.0753   0.8523   1.0000
   1.250   0.5091   0.01268   0.00462  -0.0752   0.8325   1.0000
   1.500   0.5362   0.01265   0.00453  -0.0746   0.8093   1.0000
   1.750   0.5633   0.01263   0.00444  -0.0739   0.7831   1.0000
   2.000   0.5900   0.01263   0.00437  -0.0732   0.7503   1.0000
   2.250   0.6168   0.01266   0.00430  -0.0725   0.7062   1.0000
   2.500   0.6436   0.01278   0.00418  -0.0716   0.6468   1.0000
   2.750   0.6681   0.01312   0.00416  -0.0705   0.5793   1.0000
   3.000   0.6909   0.01361   0.00433  -0.0693   0.5212   1.0000
   3.250   0.7135   0.01413   0.00464  -0.0682   0.4714   1.0000
   3.500   0.7363   0.01463   0.00496  -0.0673   0.4267   1.0000
   3.750   0.7593   0.01514   0.00532  -0.0664   0.3883   1.0000
   4.000   0.7804   0.01582   0.00574  -0.0653   0.3339   1.0000
   4.250   0.8019   0.01649   0.00614  -0.0644   0.2867   1.0000
   4.500   0.8229   0.01727   0.00652  -0.0636   0.2241   1.0000
   4.750   0.8447   0.01802   0.00695  -0.0628   0.1747   1.0000
   5.000   0.8670   0.01876   0.00746  -0.0620   0.1318   1.0000
   5.250   0.8840   0.02043   0.00851  -0.0606   0.0254   1.0000
   5.500   0.9059   0.02139   0.00961  -0.0594   0.0204   1.0000
   5.750   0.9285   0.02226   0.01073  -0.0583   0.0188   1.0000
   6.000   0.9508   0.02317   0.01189  -0.0572   0.0181   1.0000
   6.250   0.9724   0.02420   0.01318  -0.0561   0.0167   1.0000
   6.500   0.9928   0.02538   0.01463  -0.0548   0.0154   1.0000
   6.750   1.0119   0.02664   0.01622  -0.0534   0.0150   1.0000
   7.000   1.0292   0.02799   0.01782  -0.0517   0.0147   1.0000
   7.250   1.0445   0.02942   0.01946  -0.0498   0.0146   1.0000
   7.500   1.0583   0.03093   0.02114  -0.0477   0.0146   1.0000
   7.750   1.0715   0.03252   0.02285  -0.0455   0.0147   1.0000
   8.000   1.0852   0.03425   0.02467  -0.0434   0.0144   1.0000
   8.250   1.1003   0.03618   0.02666  -0.0416   0.0139   1.0000
   8.500   1.1176   0.03842   0.02894  -0.0402   0.0131   1.0000
   8.750   1.1372   0.04081   0.03142  -0.0391   0.0128   1.0000
   9.000   1.1554   0.04291   0.03379  -0.0376   0.0133   1.0000
   9.250   1.1713   0.04520   0.03640  -0.0358   0.0139   1.0000
   9.500   1.1846   0.04777   0.03942  -0.0338   0.0147   1.0000
   9.750   1.1949   0.05066   0.04263  -0.0317   0.0155   1.0000
  10.000   1.2018   0.05387   0.04615  -0.0296   0.0163   1.0000
  10.250   1.2052   0.05755   0.05011  -0.0274   0.0172   1.0000
  10.500   1.2197   0.05887   0.05180  -0.0249   0.0210   1.0000
  10.750   1.2089   0.06149   0.05482  -0.0210   0.0223   1.0000
  11.000   1.1997   0.06484   0.05847  -0.0183   0.0235   1.0000
  11.250   1.1909   0.06870   0.06255  -0.0165   0.0244   1.0000
  12.750   0.9143   0.09118   0.08612  -0.0109   0.0171   1.0000
  13.000   0.8862   0.09655   0.09165  -0.0139   0.0169   1.0000
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