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GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il)
Reynolds number: 200,000
Max Cl/Cd: 80 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe602m-il-200000.txt
Download as CSV file: xf-goe602m-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 MOD. 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2913   0.09346   0.09027  -0.0349   1.0000   0.0463
  -9.000  -0.2927   0.09108   0.08792  -0.0337   1.0000   0.0479
  -8.750  -0.3806   0.09437   0.09103  -0.0382   1.0000   0.0442
  -8.500  -0.3747   0.09239   0.08906  -0.0356   1.0000   0.0455
  -8.250  -0.3768   0.09039   0.08711  -0.0339   1.0000   0.0467
  -8.000  -0.3824   0.08859   0.08536  -0.0321   1.0000   0.0484
  -7.750  -0.3939   0.08673   0.08357  -0.0301   1.0000   0.0492
  -7.500  -0.4098   0.08509   0.08200  -0.0275   1.0000   0.0495
  -7.250  -0.4282   0.08346   0.08045  -0.0253   1.0000   0.0513
  -7.000  -0.4397   0.08069   0.07775  -0.0256   1.0000   0.0523
  -6.250  -0.4264   0.06472   0.06174  -0.0425   0.9951   0.0578
  -6.000  -0.4000   0.06127   0.05822  -0.0465   0.9905   0.0613
  -5.750  -0.3618   0.05007   0.04650  -0.0632   0.9843   0.0699
  -5.500  -0.3363   0.04823   0.04472  -0.0641   0.9794   0.0735
  -5.250  -0.3023   0.04216   0.03816  -0.0715   0.9738   0.0840
  -5.000  -0.2629   0.03064   0.02527  -0.0771   0.9710   0.0575
  -4.750  -0.2334   0.02642   0.02052  -0.0777   0.9657   0.0501
  -4.500  -0.1984   0.02345   0.01698  -0.0793   0.9615   0.0499
  -4.250  -0.1586   0.02190   0.01500  -0.0815   0.9583   0.0535
  -4.000  -0.1252   0.02056   0.01331  -0.0824   0.9530   0.0547
  -3.750  -0.0914   0.01880   0.01142  -0.0837   0.9481   0.0585
  -3.500  -0.0509   0.01782   0.01037  -0.0861   0.9448   0.0622
  -3.250  -0.0175   0.01704   0.00949  -0.0871   0.9389   0.0653
  -3.000   0.0183   0.01620   0.00863  -0.0885   0.9335   0.0706
  -2.750   0.0596   0.01550   0.00795  -0.0911   0.9303   0.0771
  -2.500   0.0911   0.01494   0.00739  -0.0917   0.9234   0.0855
  -2.250   0.1292   0.01412   0.00673  -0.0937   0.9187   0.1268
  -2.000   0.1697   0.01296   0.00639  -0.0966   0.9161   0.3464
  -1.750   0.2003   0.01262   0.00622  -0.0970   0.9086   0.4055
  -1.500   0.2375   0.01219   0.00601  -0.0987   0.9038   0.4789
  -1.250   0.2771   0.01171   0.00575  -0.1007   0.9006   0.5657
  -1.000   0.3014   0.01130   0.00561  -0.0996   0.8906   0.6371
  -0.750   0.3354   0.01042   0.00537  -0.0997   0.8866   0.8284
  -0.500   0.3999   0.01006   0.00505  -0.1071   0.8813   1.0000
  -0.250   0.4341   0.00988   0.00475  -0.1080   0.8732   1.0000
   0.000   0.4617   0.00981   0.00458  -0.1076   0.8619   1.0000
   0.250   0.4908   0.00973   0.00439  -0.1075   0.8508   1.0000
   0.500   0.5205   0.00963   0.00421  -0.1075   0.8396   1.0000
   0.750   0.5494   0.00956   0.00404  -0.1074   0.8275   1.0000
   1.000   0.5771   0.00952   0.00392  -0.1069   0.8139   1.0000
   1.250   0.6037   0.00951   0.00383  -0.1063   0.7987   1.0000
   1.500   0.6299   0.00952   0.00378  -0.1057   0.7824   1.0000
   1.750   0.6562   0.00956   0.00373  -0.1050   0.7650   1.0000
   2.000   0.6826   0.00962   0.00370  -0.1044   0.7473   1.0000
   2.250   0.7092   0.00972   0.00368  -0.1038   0.7292   1.0000
   2.500   0.7336   0.00985   0.00375  -0.1029   0.7084   1.0000
   2.750   0.7587   0.01001   0.00380  -0.1021   0.6882   1.0000
   3.000   0.7831   0.01019   0.00390  -0.1012   0.6677   1.0000
   3.250   0.8074   0.01038   0.00402  -0.1003   0.6476   1.0000
   3.500   0.8318   0.01061   0.00418  -0.0994   0.6287   1.0000
   3.750   0.8554   0.01083   0.00435  -0.0984   0.6082   1.0000
   4.000   0.8790   0.01107   0.00453  -0.0974   0.5882   1.0000
   4.250   0.9027   0.01133   0.00473  -0.0965   0.5698   1.0000
   4.500   0.9262   0.01159   0.00499  -0.0956   0.5513   1.0000
   4.750   0.9488   0.01186   0.00522  -0.0944   0.5301   1.0000
   5.000   0.9691   0.01215   0.00541  -0.0929   0.5011   1.0000
   5.250   0.9894   0.01247   0.00564  -0.0913   0.4721   1.0000
   5.500   1.0100   0.01281   0.00593  -0.0899   0.4451   1.0000
   5.750   1.0294   0.01320   0.00623  -0.0883   0.4137   1.0000
   6.000   1.0483   0.01362   0.00655  -0.0866   0.3790   1.0000
   6.250   1.0660   0.01413   0.00692  -0.0848   0.3386   1.0000
   6.500   1.0809   0.01484   0.00737  -0.0826   0.2828   1.0000
   6.750   1.0913   0.01599   0.00805  -0.0798   0.2024   1.0000
   7.000   1.0964   0.01773   0.00908  -0.0765   0.1017   1.0000
   7.250   1.1058   0.01917   0.01012  -0.0736   0.0444   1.0000
   7.500   1.1195   0.02022   0.01111  -0.0712   0.0358   1.0000
   7.750   1.1352   0.02105   0.01207  -0.0691   0.0334   1.0000
   8.000   1.1468   0.02203   0.01319  -0.0664   0.0307   1.0000
   8.250   1.1548   0.02316   0.01445  -0.0633   0.0288   1.0000
   8.500   1.1592   0.02451   0.01591  -0.0597   0.0277   1.0000
   8.750   1.1619   0.02606   0.01756  -0.0561   0.0270   1.0000
   9.000   1.1683   0.02751   0.01910  -0.0531   0.0266   1.0000
   9.250   1.1771   0.02894   0.02061  -0.0505   0.0262   1.0000
   9.500   1.1877   0.03047   0.02223  -0.0483   0.0260   1.0000
   9.750   1.2014   0.03215   0.02399  -0.0465   0.0258   1.0000
  10.000   1.2175   0.03380   0.02575  -0.0450   0.0253   1.0000
  10.250   1.2330   0.03540   0.02749  -0.0436   0.0242   1.0000
  10.500   1.2522   0.03740   0.02964  -0.0426   0.0238   1.0000
  10.750   1.2737   0.03980   0.03225  -0.0418   0.0239   1.0000
  11.000   1.2935   0.04269   0.03540  -0.0409   0.0245   1.0000
  11.250   1.3086   0.04627   0.03930  -0.0397   0.0253   1.0000
  11.500   1.3425   0.05165   0.04491  -0.0412   0.0273   1.0000
  11.750   1.3352   0.05206   0.04571  -0.0362   0.0291   1.0000
  12.000   1.3137   0.05785   0.05219  -0.0317   0.0334   1.0000
  14.000   1.0274   0.09693   0.09337  -0.0297   0.0344   1.0000
  14.250   0.9928   0.10371   0.10036  -0.0345   0.0338   1.0000
  14.500   0.9589   0.11187   0.10871  -0.0406   0.0333   1.0000
  14.750   0.9256   0.12106   0.11807  -0.0476   0.0328   1.0000
  15.000   0.8873   0.13270   0.12984  -0.0563   0.0324   1.0000
  15.250   0.8441   0.14777   0.14495  -0.0659   0.0340   1.0000
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