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GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il)
Reynolds number: 50,000
Max Cl/Cd: 45.2 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe417a-il-50000-n5.txt
Download as CSV file: xf-goe417a-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 417A (GEW. PLATTE) AIRFOIL                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3519   0.12208   0.11464  -0.0225   1.0000   0.0455
  -8.750  -0.3565   0.12179   0.11444  -0.0220   1.0000   0.0457
  -8.500  -0.3623   0.12158   0.11433  -0.0214   1.0000   0.0458
  -8.250  -0.3597   0.11857   0.11139  -0.0209   1.0000   0.0460
  -8.000  -0.3491   0.11219   0.10501  -0.0193   1.0000   0.0468
  -7.750  -0.3469   0.10922   0.10206  -0.0182   1.0000   0.0475
  -7.500  -0.3452   0.10669   0.09958  -0.0173   1.0000   0.0482
  -7.250  -0.3432   0.10439   0.09733  -0.0167   1.0000   0.0490
  -7.000  -0.3408   0.10218   0.09517  -0.0162   1.0000   0.0498
  -6.750  -0.3379   0.10000   0.09304  -0.0160   1.0000   0.0506
  -6.500  -0.3341   0.09788   0.09096  -0.0159   1.0000   0.0516
  -6.250  -0.3293   0.09581   0.08894  -0.0162   1.0000   0.0528
  -6.000  -0.3224   0.09405   0.08720  -0.0172   1.0000   0.0543
  -5.750  -0.3112   0.09306   0.08622  -0.0199   1.0000   0.0555
  -5.500  -0.2946   0.09258   0.08569  -0.0240   1.0000   0.0560
  -5.250  -0.2811   0.09049   0.08361  -0.0260   1.0000   0.0563
  -5.000  -0.2802   0.08571   0.07888  -0.0229   1.0000   0.0569
  -4.750  -0.2748   0.08223   0.07545  -0.0216   1.0000   0.0579
  -4.500  -0.2657   0.07942   0.07265  -0.0214   1.0000   0.0592
  -4.250  -0.2538   0.07693   0.07017  -0.0220   1.0000   0.0606
  -4.000  -0.2397   0.07460   0.06783  -0.0230   1.0000   0.0622
  -3.750  -0.2224   0.07247   0.06567  -0.0248   1.0000   0.0643
  -3.500  -0.1929   0.07172   0.06475  -0.0293   1.0000   0.0668
  -3.250  -0.1677   0.07021   0.06316  -0.0325   1.0000   0.0679
  -3.000  -0.1642   0.06616   0.05920  -0.0303   1.0000   0.0691
  -2.750  -0.1525   0.06346   0.05652  -0.0299   1.0000   0.0712
  -2.500  -0.1352   0.06135   0.05438  -0.0307   1.0000   0.0739
  -2.250  -0.0851   0.05985   0.05264  -0.0382   0.9930   0.0790
  -2.000  -0.0429   0.05758   0.05021  -0.0438   0.9860   0.0809
  -1.750  -0.0170   0.05418   0.04682  -0.0459   0.9790   0.0841
  -1.500   0.0223   0.05232   0.04481  -0.0503   0.9716   0.0902
  -1.250   0.0637   0.05044   0.04276  -0.0549   0.9644   0.0942
  -1.000   0.0950   0.04840   0.04065  -0.0573   0.9559   0.1022
  -0.750   0.1282   0.04634   0.03850  -0.0601   0.9477   0.1097
  -0.500   0.1663   0.04463   0.03667  -0.0634   0.9403   0.1207
  -0.250   0.1974   0.04309   0.03502  -0.0653   0.9305   0.1336
   0.000   0.2282   0.04138   0.03326  -0.0670   0.9216   0.1505
   0.250   0.2602   0.03966   0.03150  -0.0690   0.9133   0.1830
   0.500   0.2836   0.03830   0.03012  -0.0694   0.9024   0.2379
   0.750   0.3108   0.03640   0.02826  -0.0701   0.8935   0.2825
   1.000   0.3406   0.03481   0.02666  -0.0709   0.8837   0.3093
   1.250   0.3740   0.03412   0.02581  -0.0721   0.8724   0.3158
   1.500   0.4164   0.03288   0.02447  -0.0748   0.8652   0.3112
   1.750   0.4518   0.03260   0.02395  -0.0758   0.8526   0.2829
   2.000   0.4926   0.03239   0.02345  -0.0772   0.8415   0.2197
   2.250   0.5396   0.03193   0.02267  -0.0790   0.8337   0.1530
   2.500   0.5730   0.03177   0.02224  -0.0786   0.8209   0.1151
   2.750   0.6114   0.03094   0.02126  -0.0796   0.8088   0.0964
   3.000   0.6564   0.02993   0.02007  -0.0816   0.7958   0.0857
   3.250   0.7043   0.02882   0.01881  -0.0840   0.7803   0.0836
   3.500   0.7541   0.02766   0.01748  -0.0866   0.7624   0.0833
   3.750   0.8002   0.02682   0.01644  -0.0884   0.7436   0.0802
   4.000   0.8508   0.02567   0.01521  -0.0912   0.7220   0.0794
   4.250   0.8901   0.02508   0.01459  -0.0924   0.6986   0.0795
   4.500   0.9285   0.02452   0.01410  -0.0937   0.6772   0.0835
   4.750   0.9587   0.02431   0.01394  -0.0934   0.6533   0.0892
   5.000   0.9866   0.02423   0.01385  -0.0926   0.6280   0.0919
   5.250   1.0115   0.02421   0.01389  -0.0914   0.6010   0.0956
   5.500   1.0362   0.02428   0.01395  -0.0900   0.5733   0.1030
   5.750   1.0595   0.02442   0.01413  -0.0884   0.5438   0.1185
   6.000   1.0779   0.02466   0.01443  -0.0860   0.5060   0.1433
   6.250   1.1250   0.02489   0.01504  -0.0902   0.4181   1.0000
   6.500   1.1360   0.02572   0.01545  -0.0868   0.3561   1.0000
   6.750   1.1473   0.02674   0.01609  -0.0839   0.3069   1.0000
   7.000   1.1595   0.02786   0.01693  -0.0812   0.2686   1.0000
   7.250   1.1689   0.02924   0.01797  -0.0783   0.2268   1.0000
   7.500   1.1783   0.03067   0.01917  -0.0756   0.1810   1.0000
   7.750   1.1894   0.03203   0.02044  -0.0729   0.1297   1.0000
   8.000   1.1976   0.03372   0.02175  -0.0701   0.0924   1.0000
   8.250   1.2050   0.03547   0.02329  -0.0672   0.0804   1.0000
   8.500   1.2129   0.03712   0.02497  -0.0641   0.0741   1.0000
   8.750   1.2196   0.03885   0.02671  -0.0611   0.0688   1.0000
   9.000   1.2269   0.04067   0.02859  -0.0582   0.0642   1.0000
   9.250   1.2370   0.04239   0.03046  -0.0556   0.0602   1.0000
   9.500   1.2483   0.04427   0.03249  -0.0533   0.0576   1.0000
   9.750   1.2633   0.04646   0.03470  -0.0515   0.0552   1.0000
  10.000   1.2828   0.04876   0.03719  -0.0503   0.0525   1.0000
  10.250   1.2976   0.05097   0.03972  -0.0486   0.0497   1.0000
  10.500   1.3104   0.05342   0.04242  -0.0468   0.0475   1.0000
  10.750   1.3225   0.05617   0.04547  -0.0450   0.0462   1.0000
  11.000   1.3304   0.05910   0.04866  -0.0429   0.0453   1.0000
  11.250   1.3341   0.06217   0.05199  -0.0406   0.0445   1.0000
  11.500   1.3341   0.06539   0.05544  -0.0382   0.0438   1.0000
  11.750   1.3324   0.06912   0.05935  -0.0361   0.0429   1.0000
  12.000   1.3226   0.07278   0.06325  -0.0335   0.0424   1.0000
  12.250   1.3071   0.07628   0.06706  -0.0311   0.0422   1.0000
  12.500   1.2884   0.08023   0.07133  -0.0293   0.0420   1.0000
  12.750   1.2705   0.08466   0.07602  -0.0286   0.0419   1.0000
  13.000   1.2508   0.08957   0.08119  -0.0288   0.0419   1.0000
  13.250   1.2310   0.09513   0.08697  -0.0299   0.0420   1.0000
  13.500   1.2101   0.10130   0.09333  -0.0321   0.0421   1.0000
  13.750   1.1908   0.10794   0.10013  -0.0350   0.0424   1.0000
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