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GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 673 AIRFOIL (goe673-il)
Reynolds number: 50,000
Max Cl/Cd: 38.13 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe673-il-50000.txt
Download as CSV file: xf-goe673-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 673 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.4209   0.08613   0.07998  -0.0158   1.0000   0.3323
  -6.750  -0.4421   0.08473   0.07876  -0.0127   1.0000   0.3434
  -6.500  -0.4392   0.08146   0.07555  -0.0110   1.0000   0.3478
  -6.250  -0.5031   0.06124   0.05484  -0.0436   1.0000   0.1412
  -6.000  -0.4962   0.05486   0.04808  -0.0454   1.0000   0.1249
  -5.750  -0.4846   0.04886   0.04141  -0.0470   1.0000   0.1134
  -5.500  -0.4683   0.04404   0.03601  -0.0474   1.0000   0.1070
  -5.250  -0.4469   0.03999   0.03104  -0.0475   1.0000   0.1021
  -5.000  -0.4246   0.03683   0.02744  -0.0471   1.0000   0.1012
  -4.750  -0.4004   0.03424   0.02424  -0.0467   1.0000   0.1035
  -4.500  -0.3772   0.03206   0.02201  -0.0463   1.0000   0.1089
  -4.250  -0.3511   0.03007   0.01960  -0.0456   1.0000   0.1127
  -4.000  -0.3244   0.02828   0.01757  -0.0449   1.0000   0.1187
  -3.750  -0.2990   0.02691   0.01618  -0.0442   1.0000   0.1335
  -3.500  -0.2731   0.02552   0.01485  -0.0436   1.0000   0.1608
  -3.250  -0.2435   0.02197   0.01347  -0.0436   1.0000   0.4732
  -3.000  -0.2335   0.02170   0.01389  -0.0384   1.0000   0.6400
  -2.750  -0.2333   0.02172   0.01432  -0.0301   1.0000   0.7596
  -2.500  -0.2331   0.02140   0.01424  -0.0218   1.0000   0.8611
  -2.250  -0.1768   0.02093   0.01331  -0.0284   1.0000   1.0000
  -2.000  -0.1551   0.02080   0.01265  -0.0306   1.0000   1.0000
  -1.750  -0.1313   0.02100   0.01239  -0.0319   1.0000   1.0000
  -1.500  -0.1083   0.02130   0.01227  -0.0326   1.0000   1.0000
  -1.250  -0.0859   0.02167   0.01232  -0.0331   1.0000   1.0000
  -1.000  -0.0640   0.02211   0.01247  -0.0335   1.0000   1.0000
  -0.750  -0.0425   0.02260   0.01271  -0.0339   1.0000   1.0000
  -0.500  -0.0213   0.02315   0.01301  -0.0342   1.0000   1.0000
  -0.250  -0.0005   0.02375   0.01341  -0.0345   1.0000   1.0000
   0.000   0.0200   0.02440   0.01389  -0.0348   1.0000   1.0000
   0.250   0.0401   0.02510   0.01445  -0.0351   1.0000   1.0000
   0.500   0.0599   0.02586   0.01506  -0.0354   1.0000   1.0000
   0.750   0.0794   0.02667   0.01576  -0.0357   1.0000   1.0000
   1.000   0.1222   0.02783   0.01679  -0.0404   0.9898   1.0000
   1.250   0.1699   0.02903   0.01790  -0.0459   0.9759   1.0000
   1.500   0.2147   0.03016   0.01895  -0.0507   0.9617   1.0000
   1.750   0.2571   0.03121   0.01996  -0.0550   0.9472   1.0000
   2.000   0.2978   0.03220   0.02094  -0.0587   0.9326   1.0000
   2.250   0.3374   0.03315   0.02191  -0.0621   0.9178   1.0000
   2.500   0.3757   0.03405   0.02284  -0.0651   0.9030   1.0000
   2.750   0.4134   0.03490   0.02375  -0.0679   0.8881   1.0000
   3.000   0.4510   0.03570   0.02466  -0.0705   0.8732   1.0000
   3.250   0.4885   0.03645   0.02551  -0.0729   0.8583   1.0000
   3.500   0.5168   0.03725   0.02641  -0.0738   0.8422   1.0000
   3.750   0.5451   0.03804   0.02736  -0.0746   0.8258   1.0000
   4.000   0.5757   0.03878   0.02824  -0.0756   0.8098   1.0000
   4.250   0.6077   0.03944   0.02907  -0.0767   0.7939   1.0000
   4.500   0.6411   0.04001   0.02983  -0.0777   0.7783   1.0000
   4.750   0.6760   0.04046   0.03054  -0.0787   0.7628   1.0000
   5.000   0.7117   0.04079   0.03113  -0.0797   0.7476   1.0000
   5.250   0.7483   0.04100   0.03162  -0.0804   0.7327   1.0000
   5.500   0.7648   0.04217   0.03300  -0.0792   0.7151   1.0000
   5.750   0.7890   0.04298   0.03413  -0.0787   0.6987   1.0000
   6.000   0.8166   0.04365   0.03511  -0.0784   0.6832   1.0000
   6.250   0.8451   0.04423   0.03605  -0.0780   0.6680   1.0000
   6.500   0.9543   0.02503   0.01701  -0.0603   0.4898   1.0000
   6.750   0.9409   0.02624   0.01700  -0.0517   0.2897   1.0000
   7.000   0.9288   0.02967   0.01897  -0.0466   0.1538   1.0000
   7.250   0.9299   0.03226   0.02114  -0.0432   0.1250   1.0000
   7.500   0.9349   0.03436   0.02318  -0.0400   0.1131   1.0000
   7.750   0.9468   0.03641   0.02522  -0.0374   0.1052   1.0000
   8.000   0.9839   0.03879   0.02747  -0.0375   0.0947   1.0000
   8.250   1.0365   0.04141   0.03028  -0.0393   0.0869   1.0000
   8.500   1.0896   0.04523   0.03424  -0.0415   0.0848   1.0000
   8.750   1.1226   0.04893   0.03830  -0.0414   0.0846   1.0000
   9.000   1.1477   0.05322   0.04290  -0.0409   0.0835   1.0000
   9.250   1.1655   0.05782   0.04787  -0.0397   0.0830   1.0000
   9.500   1.1729   0.06046   0.05111  -0.0367   0.0840   1.0000
   9.750   1.1631   0.06343   0.05495  -0.0322   0.0870   1.0000
  10.000   1.1577   0.06771   0.05975  -0.0291   0.0901   1.0000
  10.250   1.1535   0.07232   0.06470  -0.0266   0.0929   1.0000
  10.500   1.1598   0.07750   0.07011  -0.0254   0.0966   1.0000
  10.750   1.1236   0.08032   0.07338  -0.0209   0.0981   1.0000
  11.000   1.0900   0.08422   0.07754  -0.0184   0.0993   1.0000
  11.250   1.0560   0.08909   0.08263  -0.0179   0.1001   1.0000
  11.500   1.0215   0.09511   0.08879  -0.0196   0.1009   1.0000
  11.750   0.9845   0.10296   0.09675  -0.0238   0.1025   1.0000
  12.000   0.9614   0.11132   0.10513  -0.0283   0.1059   1.0000
  12.250   0.9130   0.12776   0.12153  -0.0411   0.1179   1.0000
  12.500   0.8955   0.13932   0.13299  -0.0482   0.1321   1.0000
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