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GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 394 AIRFOIL (goe394-il)
Reynolds number: 200,000
Max Cl/Cd: 90.51 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe394-il-200000.txt
Download as CSV file: xf-goe394-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 394 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2999   0.09837   0.09511  -0.0217   1.0000   0.0378
  -7.750  -0.2910   0.09569   0.09248  -0.0235   1.0000   0.0396
  -7.500  -0.2864   0.09361   0.09048  -0.0255   1.0000   0.0417
  -7.250  -0.2547   0.09178   0.08865  -0.0445   0.9807   0.0434
  -7.000  -0.2366   0.08575   0.08261  -0.0467   0.9731   0.0440
  -6.750  -0.2195   0.08154   0.07839  -0.0454   0.9673   0.0452
  -6.500  -0.1970   0.07818   0.07499  -0.0489   0.9578   0.0470
  -6.250  -0.1744   0.07497   0.07174  -0.0537   0.9467   0.0497
  -6.000  -0.1261   0.07118   0.06781  -0.0735   0.9329   0.0539
  -5.750  -0.1209   0.06758   0.06423  -0.0689   0.9272   0.0548
  -5.500  -0.1057   0.06492   0.06154  -0.0687   0.9202   0.0563
  -5.250  -0.0839   0.06224   0.05881  -0.0714   0.9139   0.0589
  -4.750  -0.0176   0.05505   0.05142  -0.0861   0.9006   0.0657
  -4.500  -0.0016   0.05283   0.04916  -0.0852   0.8946   0.0677
  -4.250   0.0251   0.05028   0.04653  -0.0881   0.8869   0.0711
  -4.000   0.0816   0.04583   0.04172  -0.1008   0.8808   0.0765
  -3.750   0.0974   0.04339   0.03932  -0.0997   0.8739   0.0776
  -3.500   0.1181   0.04151   0.03740  -0.0995   0.8682   0.0803
  -3.250   0.1786   0.03935   0.03460  -0.1091   0.8628   0.0881
  -3.000   0.1997   0.03527   0.03056  -0.1100   0.8568   0.0891
  -2.750   0.2227   0.03302   0.02828  -0.1101   0.8520   0.0902
  -2.500   0.2494   0.03116   0.02636  -0.1109   0.8475   0.0920
  -2.250   0.2961   0.02533   0.01976  -0.1158   0.8428   0.0748
  -2.000   0.3243   0.02284   0.01708  -0.1165   0.8382   0.0708
  -1.750   0.3593   0.01811   0.01142  -0.1179   0.8345   0.0666
  -1.500   0.3879   0.01714   0.01026  -0.1181   0.8287   0.0683
  -1.250   0.4157   0.01652   0.00945  -0.1178   0.8235   0.0725
  -1.000   0.4440   0.01547   0.00804  -0.1174   0.8189   0.0764
  -0.750   0.4715   0.01522   0.00781  -0.1172   0.8125   0.0811
  -0.500   0.4990   0.01476   0.00719  -0.1167   0.8070   0.0910
  -0.250   0.5262   0.01456   0.00697  -0.1163   0.8009   0.1092
   0.000   0.5530   0.01449   0.00683  -0.1159   0.7940   0.1268
   0.250   0.5796   0.01424   0.00657  -0.1154   0.7880   0.1376
   0.500   0.6065   0.01404   0.00635  -0.1151   0.7801   0.1456
   0.750   0.6330   0.01406   0.00631  -0.1144   0.7735   0.1569
   1.000   0.6596   0.01381   0.00616  -0.1141   0.7647   0.1650
   1.250   0.6863   0.01365   0.00595  -0.1134   0.7571   0.1679
   1.500   0.7130   0.01350   0.00580  -0.1128   0.7476   0.1701
   1.750   0.7396   0.01339   0.00568  -0.1122   0.7383   0.1722
   2.000   0.7661   0.01318   0.00550  -0.1115   0.7292   0.1756
   2.250   0.7925   0.01305   0.00546  -0.1110   0.7176   0.1810
   2.500   0.8190   0.01295   0.00539  -0.1103   0.7059   0.1864
   2.750   0.8455   0.01279   0.00531  -0.1097   0.6936   0.1924
   3.000   0.8722   0.01266   0.00521  -0.1091   0.6799   0.2019
   3.250   0.8985   0.01245   0.00511  -0.1085   0.6631   0.2214
   3.500   0.9255   0.01103   0.00503  -0.1080   0.6436   1.0000
   3.750   0.9519   0.01098   0.00489  -0.1073   0.6208   1.0000
   4.000   0.9780   0.01098   0.00477  -0.1066   0.5953   1.0000
   4.250   1.0038   0.01111   0.00474  -0.1059   0.5699   1.0000
   4.500   1.0291   0.01137   0.00483  -0.1052   0.5482   1.0000
   4.750   1.0542   0.01172   0.00505  -0.1046   0.5272   1.0000
   5.000   1.0793   0.01213   0.00533  -0.1040   0.5092   1.0000
   5.250   1.1043   0.01257   0.00566  -0.1034   0.4922   1.0000
   5.500   1.1294   0.01297   0.00604  -0.1029   0.4767   1.0000
   5.750   1.1546   0.01335   0.00642  -0.1024   0.4628   1.0000
   6.000   1.1798   0.01371   0.00681  -0.1019   0.4491   1.0000
   6.250   1.2047   0.01408   0.00721  -0.1014   0.4349   1.0000
   6.500   1.2291   0.01444   0.00761  -0.1007   0.4191   1.0000
   6.750   1.2521   0.01477   0.00795  -0.0999   0.3939   1.0000
   7.000   1.2743   0.01514   0.00827  -0.0990   0.3618   1.0000
   7.250   1.2965   0.01557   0.00868  -0.0982   0.3303   1.0000
   7.500   1.3173   0.01617   0.00919  -0.0972   0.2874   1.0000
   7.750   1.3338   0.01725   0.00992  -0.0958   0.2204   1.0000
   8.000   1.3470   0.01876   0.01101  -0.0941   0.1574   1.0000
   8.250   1.3605   0.02024   0.01225  -0.0925   0.1190   1.0000
   8.500   1.3701   0.02213   0.01379  -0.0903   0.0688   1.0000
   8.750   1.3784   0.02400   0.01546  -0.0878   0.0494   1.0000
   9.000   1.3904   0.02537   0.01693  -0.0856   0.0433   1.0000
   9.250   1.3943   0.02733   0.01889  -0.0827   0.0393   1.0000
   9.500   1.4038   0.02857   0.02027  -0.0803   0.0367   1.0000
   9.750   1.4104   0.03006   0.02184  -0.0778   0.0344   1.0000
  10.000   1.4149   0.03182   0.02366  -0.0753   0.0328   1.0000
  10.250   1.4172   0.03405   0.02592  -0.0726   0.0315   1.0000
  10.500   1.4238   0.03637   0.02831  -0.0702   0.0304   1.0000
  10.750   1.4349   0.03805   0.03015  -0.0684   0.0296   1.0000
  11.000   1.4455   0.03981   0.03206  -0.0667   0.0284   1.0000
  11.250   1.4552   0.04164   0.03400  -0.0650   0.0271   1.0000
  11.500   1.4647   0.04362   0.03611  -0.0634   0.0261   1.0000
  11.750   1.4747   0.04583   0.03844  -0.0617   0.0254   1.0000
  12.000   1.4850   0.04829   0.04102  -0.0602   0.0248   1.0000
  12.250   1.4953   0.05125   0.04415  -0.0586   0.0243   1.0000
  12.500   1.5017   0.05475   0.04791  -0.0570   0.0241   1.0000
  12.750   1.5020   0.05844   0.05186  -0.0553   0.0240   1.0000
  13.000   1.4971   0.06239   0.05609  -0.0536   0.0239   1.0000
  13.250   1.4879   0.06660   0.06057  -0.0523   0.0238   1.0000
  13.500   1.4750   0.07112   0.06535  -0.0513   0.0237   1.0000
  13.750   1.4595   0.07588   0.07038  -0.0508   0.0237   1.0000
  14.000   1.4426   0.08081   0.07554  -0.0508   0.0237   1.0000
  14.250   1.4253   0.08587   0.08083  -0.0513   0.0237   1.0000
  14.500   1.4073   0.09117   0.08635  -0.0525   0.0237   1.0000
  14.750   1.3890   0.09677   0.09216  -0.0542   0.0237   1.0000
  15.000   1.3703   0.10272   0.09831  -0.0567   0.0238   1.0000
  15.250   1.3523   0.10907   0.10486  -0.0601   0.0239   1.0000
  15.500   1.3332   0.11629   0.11229  -0.0645   0.0241   1.0000
  15.750   1.0612   0.12182   0.11844  -0.0533   0.0274   1.0000
  16.000   1.0228   0.13153   0.12834  -0.0594   0.0281   1.0000
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