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GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)
Reynolds number: 200,000
Max Cl/Cd: 72.78 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe346-il-200000-n5.txt
Download as CSV file: xf-goe346-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3314   0.10673   0.10325  -0.0213   1.0000   0.0221
  -9.500  -0.3313   0.10370   0.10024  -0.0228   1.0000   0.0221
  -9.250  -0.3310   0.10052   0.09709  -0.0244   1.0000   0.0222
  -9.000  -0.3292   0.09707   0.09366  -0.0256   1.0000   0.0222
  -8.750  -0.3154   0.09093   0.08752  -0.0230   1.0000   0.0228
  -8.500  -0.3102   0.08744   0.08405  -0.0229   1.0000   0.0232
  -8.250  -0.3068   0.08419   0.08081  -0.0233   1.0000   0.0236
  -8.000  -0.3042   0.08103   0.07767  -0.0237   1.0000   0.0241
  -7.750  -0.3026   0.07797   0.07465  -0.0241   1.0000   0.0248
  -7.500  -0.3028   0.07511   0.07184  -0.0242   1.0000   0.0256
  -7.250  -0.3069   0.07275   0.06953  -0.0237   1.0000   0.0269
  -7.000  -0.3163   0.07122   0.06809  -0.0231   1.0000   0.0282
  -6.750  -0.3177   0.06916   0.06605  -0.0270   0.9983   0.0289
  -6.500  -0.2950   0.06418   0.06099  -0.0358   0.9929   0.0292
  -6.250  -0.2724   0.05909   0.05581  -0.0420   0.9881   0.0293
  -6.000  -0.2485   0.05404   0.05066  -0.0475   0.9839   0.0294
  -5.750  -0.2231   0.04936   0.04585  -0.0524   0.9792   0.0295
  -5.500  -0.2104   0.04237   0.03887  -0.0547   0.9762   0.0303
  -5.250  -0.1921   0.03854   0.03502  -0.0561   0.9713   0.0312
  -5.000  -0.1679   0.03486   0.03127  -0.0590   0.9667   0.0323
  -4.750  -0.1393   0.03119   0.02749  -0.0628   0.9630   0.0340
  -4.500  -0.0986   0.02908   0.02503  -0.0677   0.9563   0.0397
  -4.250  -0.0633   0.02597   0.02161  -0.0711   0.9513   0.0401
  -4.000  -0.0352   0.02305   0.01846  -0.0728   0.9437   0.0402
  -3.750  -0.0055   0.02020   0.01538  -0.0745   0.9374   0.0403
  -3.500   0.0141   0.01582   0.01101  -0.0764   0.9314   0.0417
  -3.250   0.0380   0.01399   0.00916  -0.0773   0.9245   0.0438
  -3.000   0.0661   0.01233   0.00733  -0.0783   0.9187   0.0465
  -2.750   0.0997   0.01193   0.00645  -0.0783   0.9107   0.0517
  -2.500   0.1285   0.01063   0.00487  -0.0786   0.9045   0.0520
  -2.000   0.1825   0.02222   0.01598  -0.0838   0.9121   0.0472
  -1.750   0.2045   0.00640   0.00030  -0.0798   0.8832   0.0554
  -1.250   0.2734   0.01859   0.01147  -0.0834   0.8909   0.0399
  -1.000   0.3005   0.01724   0.00998  -0.0832   0.8817   0.0391
  -0.750   0.3285   0.01627   0.00887  -0.0830   0.8739   0.0388
  -0.500   0.3558   0.01548   0.00793  -0.0826   0.8639   0.0387
  -0.250   0.3827   0.01479   0.00712  -0.0821   0.8512   0.0389
   0.000   0.4091   0.01421   0.00641  -0.0813   0.8359   0.0392
   0.250   0.4354   0.01374   0.00583  -0.0806   0.8193   0.0396
   0.500   0.4613   0.01315   0.00516  -0.0799   0.8000   0.0416
   0.750   0.4872   0.01268   0.00466  -0.0792   0.7786   0.0429
   1.000   0.5133   0.01233   0.00423  -0.0785   0.7584   0.0429
   1.250   0.5399   0.01203   0.00390  -0.0780   0.7415   0.0430
   1.500   0.5665   0.01179   0.00365  -0.0776   0.7242   0.0433
   1.750   0.5930   0.01161   0.00344  -0.0772   0.7051   0.0439
   2.000   0.6195   0.01150   0.00328  -0.0767   0.6846   0.0449
   2.250   0.6461   0.01143   0.00318  -0.0764   0.6624   0.0463
   2.500   0.6725   0.01143   0.00311  -0.0759   0.6382   0.0484
   2.750   0.6986   0.01150   0.00306  -0.0755   0.6096   0.0508
   3.000   0.7237   0.01164   0.00304  -0.0748   0.5689   0.0578
   3.250   0.7478   0.01193   0.00311  -0.0740   0.5191   0.0677
   3.500   0.7686   0.01056   0.00331  -0.0726   0.4693   1.0000
   3.750   0.7928   0.01101   0.00348  -0.0719   0.4188   1.0000
   4.000   0.8167   0.01151   0.00371  -0.0713   0.3709   1.0000
   4.250   0.8405   0.01204   0.00401  -0.0707   0.3275   1.0000
   4.500   0.8645   0.01256   0.00433  -0.0702   0.2903   1.0000
   4.750   0.8887   0.01305   0.00467  -0.0697   0.2587   1.0000
   5.000   0.9129   0.01355   0.00503  -0.0693   0.2285   1.0000
   5.250   0.9373   0.01400   0.00539  -0.0688   0.2068   1.0000
   5.500   0.9622   0.01440   0.00576  -0.0684   0.1907   1.0000
   5.750   0.9868   0.01482   0.00616  -0.0680   0.1751   1.0000
   6.000   1.0113   0.01526   0.00660  -0.0675   0.1579   1.0000
   6.250   1.0347   0.01583   0.00706  -0.0669   0.1255   1.0000
   6.500   1.0552   0.01683   0.00773  -0.0661   0.0749   1.0000
   6.750   1.0765   0.01774   0.00850  -0.0652   0.0514   1.0000
   7.000   1.0987   0.01850   0.00928  -0.0644   0.0442   1.0000
   7.250   1.1203   0.01931   0.01012  -0.0636   0.0397   1.0000
   7.500   1.1415   0.02014   0.01106  -0.0627   0.0366   1.0000
   7.750   1.1628   0.02091   0.01197  -0.0617   0.0338   1.0000
   8.000   1.1825   0.02185   0.01304  -0.0607   0.0313   1.0000
   8.250   1.1984   0.02323   0.01449  -0.0591   0.0286   1.0000
   8.500   1.2172   0.02422   0.01561  -0.0579   0.0267   1.0000
   8.750   1.2355   0.02525   0.01678  -0.0566   0.0249   1.0000
   9.000   1.2528   0.02636   0.01801  -0.0552   0.0230   1.0000
   9.250   1.2689   0.02752   0.01923  -0.0539   0.0213   1.0000
   9.500   1.2813   0.02921   0.02100  -0.0520   0.0198   1.0000
   9.750   1.2976   0.03040   0.02238  -0.0505   0.0188   1.0000
  10.000   1.3119   0.03185   0.02401  -0.0488   0.0177   1.0000
  10.250   1.3252   0.03330   0.02562  -0.0471   0.0167   1.0000
  10.500   1.3375   0.03458   0.02703  -0.0454   0.0158   1.0000
  10.750   1.3467   0.03580   0.02834  -0.0433   0.0150   1.0000
  11.000   1.3516   0.03756   0.03022  -0.0409   0.0143   1.0000
  11.250   1.3570   0.03951   0.03239  -0.0385   0.0138   1.0000
  11.500   1.3604   0.04171   0.03485  -0.0362   0.0134   1.0000
  11.750   1.3614   0.04415   0.03754  -0.0339   0.0130   1.0000
  12.000   1.3598   0.04683   0.04048  -0.0318   0.0126   1.0000
  12.250   1.3559   0.04977   0.04368  -0.0301   0.0123   1.0000
  12.500   1.3498   0.05302   0.04718  -0.0287   0.0121   1.0000
  12.750   1.3418   0.05658   0.05098  -0.0278   0.0119   1.0000
  13.000   1.3323   0.06051   0.05514  -0.0276   0.0117   1.0000
  13.250   1.3215   0.06484   0.05970  -0.0281   0.0115   1.0000
  13.500   1.3086   0.06979   0.06487  -0.0294   0.0114   1.0000
  13.750   1.2949   0.07520   0.07048  -0.0314   0.0113   1.0000
  14.000   1.2776   0.08173   0.07723  -0.0344   0.0113   1.0000
  14.250   1.2577   0.08927   0.08499  -0.0384   0.0113   1.0000
  14.500   1.2342   0.09818   0.09413  -0.0436   0.0114   1.0000
  14.750   1.2067   0.10893   0.10511  -0.0503   0.0116   1.0000
  15.000   1.1740   0.12201   0.11840  -0.0585   0.0119   1.0000
  15.250   1.1358   0.13796   0.13453  -0.0684   0.0124   1.0000
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