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GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il)
Reynolds number: 100,000
Max Cl/Cd: 55.54 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe280-il-100000.txt
Download as CSV file: xf-goe280-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 280 (DAIMLER XI) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3340   0.09563   0.09108  -0.0216   1.0000   0.0451
  -7.250  -0.3339   0.09320   0.08872  -0.0225   1.0000   0.0464
  -7.000  -0.3324   0.09086   0.08645  -0.0246   1.0000   0.0476
  -6.750  -0.3291   0.08892   0.08456  -0.0284   1.0000   0.0486
  -6.500  -0.3210   0.08735   0.08296  -0.0340   1.0000   0.0493
  -6.250  -0.3099   0.08559   0.08110  -0.0383   1.0000   0.0496
  -6.000  -0.3082   0.08022   0.07584  -0.0366   1.0000   0.0503
  -5.750  -0.3092   0.07597   0.07171  -0.0323   1.0000   0.0515
  -5.500  -0.3049   0.07290   0.06869  -0.0308   1.0000   0.0530
  -5.250  -0.2969   0.07001   0.06580  -0.0309   1.0000   0.0550
  -5.000  -0.2852   0.06708   0.06283  -0.0322   1.0000   0.0576
  -4.750  -0.2522   0.06553   0.06093  -0.0392   1.0000   0.0626
  -4.500  -0.2385   0.06134   0.05669  -0.0406   1.0000   0.0640
  -4.250  -0.2359   0.05768   0.05319  -0.0382   1.0000   0.0665
  -4.000  -0.2219   0.05519   0.05067  -0.0385   1.0000   0.0723
  -3.750  -0.1945   0.05241   0.04760  -0.0421   1.0000   0.0791
  -3.500  -0.1831   0.04963   0.04489  -0.0414   1.0000   0.0835
  -3.250  -0.1552   0.04746   0.04239  -0.0442   1.0000   0.0932
  -3.000  -0.1405   0.04489   0.03986  -0.0441   1.0000   0.1002
  -2.750  -0.0881   0.04159   0.03618  -0.0512   0.9944   0.1224
  -2.500  -0.0462   0.03838   0.03291  -0.0562   0.9875   0.1542
  -1.750   0.0700   0.02994   0.02467  -0.0669   0.9671   0.3782
  -1.500   0.1090   0.02743   0.02228  -0.0687   0.9587   0.4496
  -1.250   0.1832   0.02547   0.01949  -0.0785   0.9504   0.3860
  -1.000   0.2675   0.02501   0.01727  -0.0842   0.9424   0.1585
  -0.750   0.3167   0.02365   0.01545  -0.0866   0.9320   0.1277
  -0.500   0.3741   0.02215   0.01361  -0.0909   0.9264   0.1113
  -0.250   0.4174   0.02130   0.01254  -0.0927   0.9138   0.1048
   0.000   0.4579   0.02018   0.01141  -0.0943   0.9006   0.1042
   0.250   0.4951   0.01914   0.01042  -0.0951   0.8862   0.1075
   0.500   0.5287   0.01827   0.00958  -0.0951   0.8704   0.1077
   0.750   0.5581   0.01761   0.00888  -0.0942   0.8515   0.1092
   1.000   0.5864   0.01709   0.00829  -0.0932   0.8306   0.1127
   1.250   0.6149   0.01665   0.00771  -0.0921   0.8104   0.1193
   1.500   0.6420   0.01626   0.00730  -0.0909   0.7873   0.1379
   1.750   0.6630   0.01418   0.00699  -0.0883   0.7655   1.0000
   2.000   0.6893   0.01420   0.00664  -0.0867   0.7411   1.0000
   2.250   0.7145   0.01433   0.00649  -0.0854   0.7137   1.0000
   2.500   0.7396   0.01452   0.00644  -0.0842   0.6862   1.0000
   2.750   0.7649   0.01473   0.00646  -0.0833   0.6598   1.0000
   3.000   0.7905   0.01496   0.00652  -0.0825   0.6359   1.0000
   3.250   0.8161   0.01520   0.00661  -0.0817   0.6122   1.0000
   3.500   0.8415   0.01546   0.00678  -0.0810   0.5881   1.0000
   3.750   0.8669   0.01577   0.00693  -0.0803   0.5652   1.0000
   4.000   0.8922   0.01612   0.00716  -0.0797   0.5414   1.0000
   4.250   0.9172   0.01652   0.00746  -0.0790   0.5172   1.0000
   4.500   0.9419   0.01696   0.00781  -0.0783   0.4929   1.0000
   4.750   0.9662   0.01741   0.00816  -0.0776   0.4668   1.0000
   5.000   0.9901   0.01786   0.00854  -0.0769   0.4388   1.0000
   5.250   1.0135   0.01836   0.00894  -0.0760   0.4097   1.0000
   5.500   1.0366   0.01894   0.00942  -0.0752   0.3804   1.0000
   5.750   1.0583   0.01946   0.00982  -0.0742   0.3480   1.0000
   6.000   1.0792   0.01992   0.01014  -0.0733   0.3147   1.0000
   6.250   1.1012   0.02057   0.01066  -0.0725   0.2922   1.0000
   6.500   1.1236   0.02119   0.01128  -0.0718   0.2722   1.0000
   6.750   1.1449   0.02177   0.01177  -0.0710   0.2529   1.0000
   7.000   1.1663   0.02231   0.01228  -0.0703   0.2329   1.0000
   7.250   1.1882   0.02292   0.01289  -0.0696   0.2195   1.0000
   7.500   1.2098   0.02353   0.01351  -0.0689   0.2064   1.0000
   7.750   1.2309   0.02411   0.01416  -0.0681   0.1921   1.0000
   8.000   1.2519   0.02475   0.01484  -0.0673   0.1818   1.0000
   8.250   1.2742   0.02533   0.01559  -0.0665   0.1737   1.0000
   8.500   1.2948   0.02595   0.01630  -0.0656   0.1639   1.0000
   8.750   1.3147   0.02661   0.01701  -0.0647   0.1532   1.0000
   9.000   1.3345   0.02726   0.01780  -0.0637   0.1411   1.0000
   9.250   1.3542   0.02796   0.01862  -0.0626   0.1290   1.0000
   9.500   1.3736   0.02870   0.01955  -0.0614   0.1192   1.0000
   9.750   1.3908   0.02960   0.02054  -0.0600   0.1012   1.0000
  10.000   1.3994   0.03132   0.02196  -0.0579   0.0548   1.0000
  10.250   1.4053   0.03325   0.02392  -0.0552   0.0425   1.0000
  10.500   1.4109   0.03501   0.02587  -0.0525   0.0372   1.0000
  10.750   1.4118   0.03691   0.02790  -0.0492   0.0351   1.0000
  11.000   1.4130   0.03886   0.03007  -0.0464   0.0340   1.0000
  11.250   1.4122   0.04105   0.03248  -0.0438   0.0330   1.0000
  11.500   1.4094   0.04353   0.03518  -0.0416   0.0321   1.0000
  11.750   1.4046   0.04635   0.03822  -0.0398   0.0313   1.0000
  12.000   1.3978   0.04959   0.04166  -0.0386   0.0306   1.0000
  12.250   1.3891   0.05331   0.04558  -0.0380   0.0301   1.0000
  12.500   1.3786   0.05756   0.05004  -0.0381   0.0296   1.0000
  12.750   1.3668   0.06233   0.05499  -0.0389   0.0293   1.0000
  13.000   1.3547   0.06742   0.06028  -0.0401   0.0292   1.0000
  13.250   1.3424   0.07279   0.06583  -0.0417   0.0291   1.0000
  13.500   1.3303   0.07829   0.07150  -0.0434   0.0290   1.0000
  13.750   1.3199   0.08357   0.07693  -0.0450   0.0290   1.0000
  14.000   1.3116   0.08844   0.08194  -0.0462   0.0291   1.0000
  14.250   1.3067   0.09268   0.08631  -0.0469   0.0291   1.0000
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