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GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il)
Reynolds number: 200,000
Max Cl/Cd: 73.5 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe277-il-200000.txt
Download as CSV file: xf-goe277-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3377   0.09090   0.08752  -0.0246   1.0000   0.0368
  -7.500  -0.3429   0.08888   0.08558  -0.0254   1.0000   0.0377
  -7.250  -0.3450   0.08678   0.08354  -0.0299   1.0000   0.0384
  -7.000  -0.3428   0.08432   0.08110  -0.0342   1.0000   0.0388
  -6.750  -0.3386   0.08143   0.07819  -0.0371   1.0000   0.0390
  -6.500  -0.3326   0.07840   0.07512  -0.0387   1.0000   0.0391
  -6.250  -0.3385   0.07291   0.06974  -0.0360   1.0000   0.0398
  -6.000  -0.3376   0.07026   0.06713  -0.0331   1.0000   0.0404
  -5.750  -0.3346   0.06787   0.06477  -0.0315   1.0000   0.0412
  -5.500  -0.3299   0.06547   0.06238  -0.0308   1.0000   0.0422
  -5.250  -0.3007   0.06160   0.05844  -0.0360   0.9968   0.0450
  -5.000  -0.2245   0.05674   0.05291  -0.0529   0.9902   0.0505
  -4.750  -0.2021   0.04944   0.04577  -0.0567   0.9859   0.0525
  -4.500  -0.0893   0.03047   0.02640  -0.0711   0.9608   0.0640
  -4.250  -0.0647   0.02371   0.01985  -0.0746   0.9578   0.0670
  -4.000  -0.0312   0.02086   0.01691  -0.0775   0.9507   0.0719
  -3.750   0.0081   0.01724   0.01286  -0.0818   0.9450   0.0811
  -3.500   0.0398   0.01514   0.01073  -0.0837   0.9377   0.0879
  -3.250   0.0725   0.01280   0.00817  -0.0858   0.9294   0.0989
  -3.000   0.1023   0.01107   0.00620  -0.0869   0.9185   0.1120
  -2.750   0.1313   0.00960   0.00455  -0.0876   0.9077   0.1268
  -2.500   0.1585   0.00833   0.00319  -0.0879   0.8959   0.1429
  -2.250   0.1836   0.00746   0.00224  -0.0876   0.8813   0.1643
  -2.000   0.2070   0.00656   0.00130  -0.0872   0.8651   0.1921
  -1.750   0.2613   0.01776   0.01079  -0.0907   0.8870   0.0772
  -1.500   0.2899   0.01604   0.00889  -0.0903   0.8711   0.0724
  -1.250   0.3183   0.01503   0.00764  -0.0895   0.8539   0.0701
  -1.000   0.3453   0.01436   0.00685  -0.0887   0.8339   0.0716
  -0.750   0.3722   0.01367   0.00601  -0.0879   0.8127   0.0709
  -0.500   0.3989   0.01310   0.00531  -0.0870   0.7907   0.0707
  -0.250   0.4253   0.01267   0.00477  -0.0862   0.7679   0.0716
   0.000   0.4516   0.01236   0.00434  -0.0855   0.7453   0.0733
   0.250   0.4780   0.01215   0.00402  -0.0848   0.7231   0.0758
   0.500   0.5043   0.01197   0.00375  -0.0843   0.7008   0.0812
   0.750   0.5308   0.01187   0.00355  -0.0837   0.6778   0.0892
   1.000   0.5574   0.01175   0.00338  -0.0832   0.6536   0.1090
   1.250   0.5807   0.00970   0.00331  -0.0820   0.6304   1.0000
   1.500   0.6068   0.00990   0.00326  -0.0814   0.6038   1.0000
   1.750   0.6327   0.01013   0.00328  -0.0809   0.5780   1.0000
   2.000   0.6584   0.01041   0.00333  -0.0804   0.5538   1.0000
   2.250   0.6843   0.01072   0.00344  -0.0799   0.5307   1.0000
   2.500   0.7102   0.01106   0.00358  -0.0795   0.5107   1.0000
   2.750   0.7364   0.01136   0.00377  -0.0792   0.4921   1.0000
   3.000   0.7627   0.01168   0.00396  -0.0789   0.4766   1.0000
   3.250   0.7891   0.01200   0.00417  -0.0786   0.4638   1.0000
   3.500   0.8156   0.01233   0.00440  -0.0784   0.4527   1.0000
   3.750   0.8423   0.01261   0.00465  -0.0782   0.4421   1.0000
   4.000   0.8689   0.01293   0.00491  -0.0780   0.4330   1.0000
   4.250   0.8955   0.01324   0.00516  -0.0778   0.4243   1.0000
   4.500   0.9221   0.01354   0.00548  -0.0777   0.4157   1.0000
   4.750   0.9485   0.01389   0.00575  -0.0775   0.4082   1.0000
   5.000   0.9749   0.01416   0.00608  -0.0773   0.4001   1.0000
   5.250   1.0014   0.01453   0.00640  -0.0771   0.3935   1.0000
   5.500   1.0278   0.01482   0.00679  -0.0769   0.3866   1.0000
   5.750   1.0539   0.01517   0.00710  -0.0767   0.3796   1.0000
   6.000   1.0798   0.01547   0.00749  -0.0764   0.3719   1.0000
   6.250   1.1057   0.01582   0.00784  -0.0761   0.3647   1.0000
   6.500   1.1308   0.01607   0.00821  -0.0757   0.3556   1.0000
   6.750   1.1556   0.01638   0.00852  -0.0753   0.3459   1.0000
   7.000   1.1798   0.01664   0.00878  -0.0747   0.3345   1.0000
   7.250   1.2037   0.01682   0.00913  -0.0741   0.3232   1.0000
   7.500   1.2279   0.01709   0.00950  -0.0736   0.3132   1.0000
   7.750   1.2509   0.01728   0.00977  -0.0729   0.2992   1.0000
   8.000   1.2739   0.01747   0.01007  -0.0721   0.2840   1.0000
   8.250   1.2963   0.01766   0.01037  -0.0713   0.2639   1.0000
   8.500   1.3179   0.01793   0.01066  -0.0704   0.2281   1.0000
   8.750   1.3276   0.01951   0.01160  -0.0683   0.1340   1.0000
   9.000   1.3335   0.02173   0.01336  -0.0656   0.0725   1.0000
   9.250   1.3420   0.02352   0.01489  -0.0631   0.0412   1.0000
   9.500   1.3526   0.02495   0.01638  -0.0608   0.0354   1.0000
   9.750   1.3620   0.02634   0.01791  -0.0584   0.0324   1.0000
  10.000   1.3697   0.02769   0.01939  -0.0558   0.0302   1.0000
  10.250   1.3720   0.02919   0.02102  -0.0526   0.0289   1.0000
  10.500   1.3712   0.03101   0.02296  -0.0494   0.0279   1.0000
  10.750   1.3673   0.03323   0.02528  -0.0464   0.0272   1.0000
  11.000   1.3615   0.03583   0.02799  -0.0437   0.0265   1.0000
  11.250   1.3605   0.03823   0.03050  -0.0418   0.0262   1.0000
  11.500   1.3623   0.04054   0.03293  -0.0402   0.0258   1.0000
  11.750   1.3644   0.04293   0.03547  -0.0389   0.0254   1.0000
  12.000   1.3672   0.04536   0.03802  -0.0377   0.0248   1.0000
  12.250   1.3701   0.04784   0.04062  -0.0367   0.0241   1.0000
  12.500   1.3732   0.05037   0.04326  -0.0358   0.0233   1.0000
  12.750   1.3765   0.05294   0.04594  -0.0348   0.0228   1.0000
  13.000   1.3811   0.05548   0.04859  -0.0337   0.0225   1.0000
  13.250   1.3854   0.05814   0.05138  -0.0327   0.0222   1.0000
  13.500   1.3889   0.06099   0.05438  -0.0317   0.0220   1.0000
  13.750   1.3906   0.06412   0.05770  -0.0310   0.0218   1.0000
  14.000   1.3903   0.06758   0.06136  -0.0305   0.0218   1.0000
  14.250   1.3868   0.07144   0.06545  -0.0304   0.0218   1.0000
  14.500   1.3803   0.07579   0.07004  -0.0307   0.0220   1.0000
  14.750   1.3695   0.08077   0.07529  -0.0316   0.0222   1.0000
  15.000   1.3546   0.08644   0.08124  -0.0332   0.0224   1.0000
  15.250   1.3374   0.09274   0.08781  -0.0356   0.0227   1.0000
  15.500   1.3184   0.09961   0.09494  -0.0387   0.0230   1.0000
  15.750   1.2985   0.10700   0.10257  -0.0425   0.0232   1.0000
  16.000   1.2778   0.11497   0.11077  -0.0469   0.0235   1.0000
  16.250   1.2566   0.12350   0.11951  -0.0521   0.0238   1.0000
  16.500   1.2346   0.13268   0.12889  -0.0579   0.0242   1.0000
  16.750   1.2119   0.14265   0.13903  -0.0645   0.0245   1.0000
  17.000   1.1881   0.15360   0.15012  -0.0718   0.0248   1.0000
  17.250   1.1624   0.16602   0.16266  -0.0802   0.0253   1.0000
  17.500   1.1398   0.17827   0.17497  -0.0878   0.0261   1.0000
  17.750   0.8938   0.15530   0.15218  -0.0553   0.0260   1.0000
  18.000   0.8079   0.18330   0.18020  -0.0681   0.0334   1.0000
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