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GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il)
Reynolds number: 100,000
Max Cl/Cd: 54.26 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe277-il-100000.txt
Download as CSV file: xf-goe277-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 277 (DAIMLER VIII) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3562   0.10553   0.10066  -0.0242   1.0000   0.0630
  -8.250  -0.3636   0.10454   0.09978  -0.0274   1.0000   0.0635
  -8.000  -0.3652   0.10281   0.09812  -0.0330   1.0000   0.0638
  -7.750  -0.3614   0.09765   0.09303  -0.0326   1.0000   0.0645
  -7.500  -0.3460   0.09219   0.08756  -0.0250   1.0000   0.0672
  -7.250  -0.3415   0.08938   0.08480  -0.0244   1.0000   0.0699
  -7.000  -0.3403   0.08684   0.08231  -0.0252   1.0000   0.0727
  -6.750  -0.3398   0.08443   0.07997  -0.0275   1.0000   0.0757
  -6.500  -0.3359   0.08325   0.07874  -0.0374   1.0000   0.0781
  -6.250  -0.3325   0.07904   0.07454  -0.0385   1.0000   0.0791
  -6.000  -0.3311   0.07520   0.07084  -0.0329   1.0000   0.0808
  -5.750  -0.3271   0.07254   0.06822  -0.0306   1.0000   0.0832
  -5.500  -0.3209   0.06992   0.06561  -0.0307   1.0000   0.0868
  -5.250  -0.2971   0.06761   0.06293  -0.0414   1.0000   0.0938
  -5.000  -0.2969   0.06345   0.05899  -0.0373   1.0000   0.0954
  -4.750  -0.2928   0.06108   0.05671  -0.0345   1.0000   0.0989
  -4.500  -0.2696   0.05844   0.05376  -0.0404   1.0000   0.1095
  -4.250  -0.2665   0.05561   0.05108  -0.0373   1.0000   0.1124
  -4.000  -0.2428   0.05354   0.04869  -0.0414   1.0000   0.1245
  -3.750  -0.2364   0.05065   0.04597  -0.0392   1.0000   0.1278
  -3.500  -0.1975   0.04733   0.04248  -0.0446   0.9953   0.1428
  -3.250  -0.1443   0.04389   0.03881  -0.0523   0.9863   0.1714
  -3.000  -0.0969   0.04069   0.03551  -0.0579   0.9765   0.2027
  -1.750   0.1764   0.02537   0.01753  -0.0836   0.9336   0.1187
  -1.500   0.2318   0.02352   0.01503  -0.0876   0.9274   0.1097
  -1.250   0.2734   0.02211   0.01344  -0.0895   0.9152   0.1070
  -1.000   0.3138   0.02068   0.01188  -0.0911   0.9028   0.1052
  -0.750   0.3523   0.01952   0.01060  -0.0921   0.8894   0.1050
  -0.500   0.3876   0.01854   0.00956  -0.0925   0.8743   0.1064
  -0.250   0.4197   0.01757   0.00866  -0.0924   0.8575   0.1124
   0.000   0.4501   0.01680   0.00790  -0.0918   0.8397   0.1193
   0.250   0.4777   0.01621   0.00726  -0.0907   0.8186   0.1269
   0.500   0.5061   0.01567   0.00668  -0.0897   0.7971   0.1457
   0.750   0.5340   0.01323   0.00619  -0.0884   0.7754   1.0000
   1.000   0.5610   0.01329   0.00584  -0.0872   0.7514   1.0000
   1.250   0.5868   0.01347   0.00573  -0.0861   0.7252   1.0000
   1.500   0.6126   0.01371   0.00570  -0.0851   0.6996   1.0000
   1.750   0.6384   0.01399   0.00572  -0.0842   0.6752   1.0000
   2.000   0.6636   0.01428   0.00583  -0.0833   0.6489   1.0000
   2.250   0.6891   0.01459   0.00594  -0.0826   0.6250   1.0000
   2.500   0.7149   0.01491   0.00607  -0.0819   0.6033   1.0000
   2.750   0.7409   0.01528   0.00626  -0.0813   0.5843   1.0000
   3.000   0.7669   0.01569   0.00654  -0.0809   0.5665   1.0000
   3.250   0.7931   0.01612   0.00685  -0.0805   0.5509   1.0000
   3.500   0.8195   0.01657   0.00719  -0.0802   0.5372   1.0000
   3.750   0.8462   0.01705   0.00757  -0.0799   0.5256   1.0000
   4.000   0.8726   0.01754   0.00805  -0.0797   0.5144   1.0000
   4.250   0.8989   0.01807   0.00858  -0.0795   0.5042   1.0000
   4.500   0.9258   0.01859   0.00905  -0.0793   0.4958   1.0000
   4.750   0.9517   0.01913   0.00968  -0.0791   0.4867   1.0000
   5.000   0.9784   0.01972   0.01026  -0.0790   0.4796   1.0000
   5.250   1.0041   0.02028   0.01093  -0.0788   0.4714   1.0000
   5.500   1.0303   0.02086   0.01156  -0.0785   0.4640   1.0000
   5.750   1.0558   0.02137   0.01214  -0.0782   0.4551   1.0000
   6.000   1.0806   0.02190   0.01278  -0.0778   0.4459   1.0000
   6.250   1.1072   0.02233   0.01316  -0.0774   0.4373   1.0000
   6.500   1.1306   0.02279   0.01384  -0.0768   0.4267   1.0000
   6.750   1.1549   0.02325   0.01439  -0.0762   0.4166   1.0000
   7.000   1.1813   0.02365   0.01476  -0.0759   0.4080   1.0000
   7.250   1.2040   0.02423   0.01564  -0.0751   0.3984   1.0000
   7.500   1.2279   0.02466   0.01617  -0.0745   0.3879   1.0000
   7.750   1.2508   0.02480   0.01638  -0.0735   0.3735   1.0000
   8.000   1.2722   0.02484   0.01649  -0.0723   0.3568   1.0000
   8.250   1.2933   0.02493   0.01670  -0.0711   0.3405   1.0000
   8.500   1.3137   0.02505   0.01693  -0.0697   0.3240   1.0000
   8.750   1.3325   0.02504   0.01696  -0.0682   0.3048   1.0000
   9.000   1.3466   0.02500   0.01720  -0.0659   0.2792   1.0000
   9.250   1.3604   0.02507   0.01745  -0.0637   0.2446   1.0000
   9.500   1.3640   0.02623   0.01825  -0.0605   0.1583   1.0000
   9.750   1.3515   0.02970   0.02105  -0.0561   0.0973   1.0000
  10.000   1.3432   0.03252   0.02373  -0.0520   0.0762   1.0000
  10.250   1.3385   0.03464   0.02590  -0.0482   0.0662   1.0000
  10.500   1.3324   0.03700   0.02829  -0.0449   0.0613   1.0000
  10.750   1.3305   0.03924   0.03067  -0.0424   0.0572   1.0000
  11.000   1.3275   0.04171   0.03322  -0.0403   0.0543   1.0000
  11.250   1.3225   0.04456   0.03606  -0.0384   0.0522   1.0000
  11.500   1.3257   0.04690   0.03853  -0.0367   0.0502   1.0000
  11.750   1.3300   0.04925   0.04099  -0.0353   0.0479   1.0000
  12.000   1.3341   0.05164   0.04344  -0.0341   0.0456   1.0000
  12.250   1.3400   0.05402   0.04581  -0.0327   0.0435   1.0000
  12.500   1.3576   0.05623   0.04803  -0.0306   0.0421   1.0000
  12.750   1.3691   0.05887   0.05091  -0.0291   0.0414   1.0000
  13.000   1.3775   0.06196   0.05426  -0.0278   0.0409   1.0000
  13.250   1.3799   0.06554   0.05812  -0.0268   0.0406   1.0000
  13.500   1.3764   0.06955   0.06242  -0.0262   0.0405   1.0000
  13.750   1.3678   0.07395   0.06711  -0.0261   0.0404   1.0000
  14.000   1.3553   0.07876   0.07221  -0.0266   0.0404   1.0000
  14.250   1.3399   0.08404   0.07776  -0.0277   0.0404   1.0000
  14.500   1.3225   0.08979   0.08377  -0.0295   0.0405   1.0000
  14.750   1.3035   0.09604   0.09026  -0.0320   0.0407   1.0000
  15.000   1.2827   0.10284   0.09728  -0.0352   0.0409   1.0000
  15.250   1.2617   0.11011   0.10476  -0.0391   0.0413   1.0000
  15.500   1.2404   0.11796   0.11279  -0.0435   0.0416   1.0000
  15.750   1.2193   0.12627   0.12126  -0.0485   0.0420   1.0000
  16.000   1.1999   0.13484   0.12994  -0.0535   0.0424   1.0000
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