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GOE 647 AIRFOIL (goe647-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 647 AIRFOIL (goe647-il)
Reynolds number: 200,000
Max Cl/Cd: 58.53 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe647-il-200000-n5.txt
Download as CSV file: xf-goe647-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 647 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5086   0.04903   0.04466  -0.0978   0.9761   0.0359
 -11.250  -0.5293   0.04157   0.03673  -0.1080   0.9576   0.0360
 -11.000  -0.5307   0.03731   0.03197  -0.1111   0.9439   0.0364
 -10.750  -0.5078   0.03547   0.03005  -0.1128   0.9368   0.0369
 -10.500  -0.4859   0.03394   0.02842  -0.1139   0.9278   0.0373
 -10.250  -0.4633   0.03225   0.02657  -0.1151   0.9197   0.0379
 -10.000  -0.4419   0.03061   0.02471  -0.1158   0.9101   0.0384
  -9.750  -0.4201   0.02901   0.02289  -0.1163   0.9007   0.0389
  -9.500  -0.3973   0.02751   0.02115  -0.1166   0.8912   0.0395
  -9.250  -0.3758   0.02620   0.01960  -0.1163   0.8808   0.0400
  -9.000  -0.3517   0.02497   0.01810  -0.1164   0.8713   0.0407
  -8.750  -0.3307   0.02400   0.01686  -0.1156   0.8602   0.0414
  -8.500  -0.3048   0.02306   0.01589  -0.1156   0.8510   0.0420
  -8.250  -0.2828   0.02236   0.01513  -0.1147   0.8395   0.0426
  -8.000  -0.2586   0.02163   0.01430  -0.1142   0.8296   0.0433
  -7.750  -0.2354   0.02095   0.01351  -0.1134   0.8184   0.0439
  -7.500  -0.2122   0.02030   0.01274  -0.1125   0.8077   0.0446
  -7.250  -0.1881   0.01968   0.01198  -0.1118   0.7970   0.0454
  -7.000  -0.1653   0.01913   0.01131  -0.1108   0.7854   0.0462
  -6.750  -0.1414   0.01859   0.01065  -0.1100   0.7743   0.0472
  -6.500  -0.1186   0.01810   0.01011  -0.1090   0.7606   0.0482
  -6.250  -0.0958   0.01767   0.00961  -0.1079   0.7455   0.0494
  -6.000  -0.0726   0.01727   0.00912  -0.1069   0.7304   0.0507
  -5.750  -0.0491   0.01689   0.00861  -0.1058   0.7168   0.0520
  -5.500  -0.0252   0.01654   0.00814  -0.1049   0.7048   0.0533
  -5.250  -0.0022   0.01616   0.00773  -0.1039   0.6929   0.0548
  -5.000   0.0219   0.01586   0.00736  -0.1030   0.6818   0.0568
  -4.750   0.0462   0.01561   0.00700  -0.1022   0.6705   0.0595
  -4.500   0.0701   0.01533   0.00668  -0.1013   0.6592   0.0628
  -4.250   0.0947   0.01512   0.00637  -0.1005   0.6488   0.0672
  -4.000   0.1190   0.01488   0.00611  -0.0996   0.6380   0.0729
  -3.750   0.1436   0.01467   0.00586  -0.0988   0.6279   0.0809
  -3.500   0.1680   0.01448   0.00562  -0.0980   0.6171   0.0924
  -3.250   0.1925   0.01427   0.00540  -0.0972   0.6068   0.1070
  -3.000   0.2167   0.01406   0.00518  -0.0964   0.5968   0.1257
  -2.750   0.2405   0.01380   0.00509  -0.0956   0.5867   0.1633
  -2.500   0.2651   0.01373   0.00502  -0.0948   0.5766   0.2010
  -2.250   0.2899   0.01366   0.00497  -0.0940   0.5653   0.2246
  -2.000   0.3144   0.01363   0.00493  -0.0932   0.5547   0.2459
  -1.750   0.3388   0.01360   0.00490  -0.0924   0.5437   0.2683
  -1.500   0.3632   0.01357   0.00489  -0.0916   0.5328   0.2905
  -1.250   0.3871   0.01358   0.00487  -0.0906   0.5213   0.3096
  -1.000   0.4112   0.01357   0.00485  -0.0898   0.5091   0.3259
  -0.750   0.4350   0.01359   0.00484  -0.0888   0.4969   0.3419
  -0.500   0.4584   0.01363   0.00484  -0.0878   0.4851   0.3594
  -0.250   0.4818   0.01366   0.00486  -0.0868   0.4729   0.3781
   0.000   0.5050   0.01370   0.00490  -0.0858   0.4608   0.4001
   0.250   0.5273   0.01377   0.00495  -0.0846   0.4489   0.4264
   0.500   0.5497   0.01384   0.00501  -0.0834   0.4368   0.4535
   0.750   0.5720   0.01389   0.00507  -0.0823   0.4256   0.4797
   1.250   0.6154   0.01400   0.00523  -0.0797   0.4059   0.5362
   1.500   0.6357   0.01402   0.00534  -0.0782   0.3972   0.5780
   1.750   0.6553   0.01391   0.00548  -0.0764   0.3885   0.6637
   2.000   0.7536   0.01391   0.00592  -0.0909   0.3739   0.9990
   2.250   0.7747   0.01417   0.00605  -0.0896   0.3669   1.0000
   2.500   0.7954   0.01440   0.00619  -0.0882   0.3610   1.0000
   2.750   0.8162   0.01463   0.00635  -0.0868   0.3551   1.0000
   3.000   0.8361   0.01490   0.00652  -0.0853   0.3498   1.0000
   3.250   0.8566   0.01516   0.00670  -0.0840   0.3452   1.0000
   3.500   0.8777   0.01539   0.00689  -0.0827   0.3402   1.0000
   3.750   0.8978   0.01566   0.00709  -0.0813   0.3353   1.0000
   4.000   0.9171   0.01598   0.00730  -0.0797   0.3311   1.0000
   4.250   0.9380   0.01623   0.00753  -0.0785   0.3270   1.0000
   4.500   0.9585   0.01650   0.00777  -0.0772   0.3228   1.0000
   4.750   0.9783   0.01679   0.00801  -0.0758   0.3190   1.0000
   5.000   0.9968   0.01711   0.00828  -0.0741   0.3157   1.0000
   5.250   1.0152   0.01745   0.00855  -0.0725   0.3127   1.0000
   5.500   1.0351   0.01772   0.00884  -0.0712   0.3097   1.0000
   5.750   1.0545   0.01802   0.00914  -0.0697   0.3066   1.0000
   6.000   1.0734   0.01834   0.00945  -0.0683   0.3034   1.0000
   6.250   1.0919   0.01869   0.00977  -0.0668   0.3005   1.0000
   6.500   1.1101   0.01909   0.01011  -0.0653   0.2977   1.0000
   6.750   1.1293   0.01947   0.01047  -0.0640   0.2950   1.0000
   7.000   1.1484   0.01981   0.01085  -0.0627   0.2922   1.0000
   7.250   1.1674   0.02018   0.01125  -0.0614   0.2895   1.0000
   7.500   1.1861   0.02057   0.01166  -0.0602   0.2870   1.0000
   7.750   1.2045   0.02100   0.01208  -0.0589   0.2845   1.0000
   8.000   1.2228   0.02144   0.01251  -0.0576   0.2822   1.0000
   8.250   1.2418   0.02193   0.01296  -0.0566   0.2802   1.0000
   8.500   1.2609   0.02239   0.01345  -0.0555   0.2782   1.0000
   8.750   1.2788   0.02285   0.01398  -0.0543   0.2761   1.0000
   9.000   1.2965   0.02334   0.01453  -0.0531   0.2739   1.0000
   9.250   1.3136   0.02385   0.01509  -0.0519   0.2717   1.0000
   9.500   1.3303   0.02438   0.01566  -0.0506   0.2694   1.0000
   9.750   1.3466   0.02493   0.01623  -0.0494   0.2672   1.0000
  10.000   1.3640   0.02550   0.01681  -0.0484   0.2653   1.0000
  10.250   1.3825   0.02609   0.01738  -0.0475   0.2636   1.0000
  10.500   1.3996   0.02671   0.01806  -0.0465   0.2619   1.0000
  10.750   1.4147   0.02738   0.01884  -0.0453   0.2602   1.0000
  11.000   1.4296   0.02808   0.01963  -0.0441   0.2585   1.0000
  11.250   1.4441   0.02881   0.02045  -0.0430   0.2566   1.0000
  11.500   1.4583   0.02957   0.02128  -0.0418   0.2547   1.0000
  11.750   1.4717   0.03035   0.02213  -0.0407   0.2527   1.0000
  12.000   1.4856   0.03114   0.02297  -0.0396   0.2509   1.0000
  12.250   1.5007   0.03191   0.02377  -0.0387   0.2493   1.0000
  12.500   1.5177   0.03265   0.02452  -0.0380   0.2478   1.0000
  12.750   1.5326   0.03350   0.02544  -0.0371   0.2463   1.0000
  13.000   1.5404   0.03468   0.02676  -0.0358   0.2446   1.0000
  13.250   1.5484   0.03589   0.02811  -0.0346   0.2427   1.0000
  13.500   1.5569   0.03711   0.02946  -0.0335   0.2408   1.0000
  13.750   1.5645   0.03839   0.03084  -0.0324   0.2388   1.0000
  14.000   1.5726   0.03965   0.03219  -0.0315   0.2368   1.0000
  14.250   1.5806   0.04087   0.03345  -0.0306   0.2342   1.0000
  14.500   1.5942   0.04175   0.03429  -0.0299   0.2316   1.0000
  14.750   1.5905   0.04399   0.03673  -0.0288   0.2290   1.0000
  15.000   1.5865   0.04636   0.03927  -0.0280   0.2258   1.0000
  15.250   1.5862   0.04853   0.04156  -0.0273   0.2227   1.0000
  15.500   1.5881   0.05053   0.04362  -0.0269   0.2197   1.0000
  15.750   1.5973   0.05187   0.04492  -0.0265   0.2168   1.0000
  16.000   1.5907   0.05499   0.04824  -0.0263   0.2142   1.0000
  16.250   1.5826   0.05841   0.05185  -0.0262   0.2113   1.0000
  16.500   1.5765   0.06170   0.05528  -0.0264   0.2083   1.0000
  16.750   1.5745   0.06456   0.05822  -0.0266   0.2052   1.0000
  17.000   1.5808   0.06642   0.06007  -0.0266   0.2024   1.0000
  17.250   1.5634   0.07141   0.06528  -0.0274   0.1995   1.0000
  17.500   1.5412   0.07722   0.07129  -0.0286   0.1958   1.0000
  17.750   1.5259   0.08224   0.07645  -0.0297   0.1926   1.0000
  18.000   1.5281   0.08485   0.07906  -0.0302   0.1892   1.0000
  18.250   1.4998   0.09194   0.08635  -0.0322   0.1860   1.0000
  18.500   1.4214   0.10693   0.10165  -0.0372   0.1814   1.0000
  18.750   1.4067   0.11245   0.10724  -0.0392   0.1773   1.0000
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