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GOE 370 AIRFOIL (goe370-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 370 AIRFOIL (goe370-il)
Reynolds number: 200,000
Max Cl/Cd: 92.01 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe370-il-200000.txt
Download as CSV file: xf-goe370-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 370 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3180   0.09177   0.08862  -0.0228   1.0000   0.0258
  -6.750  -0.3306   0.09088   0.08783  -0.0197   1.0000   0.0262
  -6.500  -0.3474   0.09053   0.08757  -0.0159   1.0000   0.0263
  -6.250  -0.3178   0.08652   0.08354  -0.0246   0.9949   0.0284
  -6.000  -0.2608   0.08338   0.08030  -0.0434   0.9861   0.0299
  -5.750  -0.2201   0.07883   0.07567  -0.0532   0.9806   0.0301
  -5.500  -0.2048   0.07141   0.06828  -0.0563   0.9746   0.0311
  -5.250  -0.1810   0.06690   0.06375  -0.0585   0.9709   0.0325
  -5.000  -0.1520   0.06310   0.05988  -0.0633   0.9640   0.0341
  -4.750  -0.1147   0.05898   0.05569  -0.0703   0.9590   0.0364
  -4.500   0.0067   0.03348   0.03009  -0.0915   0.9429   0.0433
  -4.250   0.0157   0.03009   0.02676  -0.0895   0.9352   0.0459
  -4.000   0.0733   0.02749   0.02379  -0.1000   0.9312   0.0554
  -3.750   0.0871   0.02267   0.01903  -0.1003   0.9255   0.0576
  -3.500   0.1121   0.02023   0.01651  -0.1016   0.9193   0.0624
  -3.250   0.1534   0.01666   0.01264  -0.1072   0.9156   0.0706
  -3.000   0.1642   0.03292   0.02856  -0.1106   0.9245   0.0721
  -2.750   0.2012   0.03028   0.02566  -0.1136   0.9189   0.0845
  -2.500   0.2412   0.02789   0.02290  -0.1166   0.9151   0.0968
  -2.250   0.2726   0.02223   0.01658  -0.1170   0.9069   0.0701
  -2.000   0.3063   0.01941   0.01338  -0.1180   0.9023   0.0658
  -1.750   0.3338   0.01701   0.01049  -0.1177   0.8945   0.0638
  -1.500   0.3655   0.01534   0.00835  -0.1180   0.8892   0.0645
  -1.250   0.3929   0.01476   0.00749  -0.1176   0.8815   0.0681
  -1.000   0.4228   0.01368   0.00619  -0.1176   0.8753   0.0694
  -0.750   0.4488   0.01297   0.00545  -0.1171   0.8672   0.0725
  -0.500   0.4778   0.01250   0.00493  -0.1170   0.8608   0.0788
  -0.250   0.5028   0.01214   0.00459  -0.1162   0.8522   0.0884
   0.000   0.5311   0.01191   0.00440  -0.1160   0.8456   0.1198
   0.250   0.5562   0.01182   0.00437  -0.1153   0.8364   0.1655
   0.500   0.5823   0.01169   0.00427  -0.1149   0.8284   0.1915
   0.750   0.6087   0.01156   0.00421  -0.1144   0.8204   0.2168
   1.000   0.6336   0.01146   0.00422  -0.1138   0.8111   0.2432
   1.250   0.6591   0.01125   0.00423  -0.1132   0.8024   0.3171
   1.500   0.7080   0.00992   0.00402  -0.1175   0.7920   1.0000
   1.750   0.7325   0.00998   0.00397  -0.1164   0.7790   1.0000
   2.000   0.7570   0.01006   0.00399  -0.1154   0.7665   1.0000
   2.250   0.7818   0.01016   0.00404  -0.1146   0.7551   1.0000
   2.500   0.8070   0.01028   0.00411  -0.1138   0.7445   1.0000
   2.750   0.8327   0.01039   0.00418  -0.1132   0.7345   1.0000
   3.000   0.8575   0.01051   0.00430  -0.1124   0.7233   1.0000
   3.250   0.8822   0.01064   0.00450  -0.1116   0.7118   1.0000
   3.500   0.9071   0.01077   0.00466  -0.1109   0.7007   1.0000
   3.750   0.9321   0.01090   0.00483  -0.1101   0.6895   1.0000
   4.000   0.9553   0.01090   0.00484  -0.1088   0.6703   1.0000
   4.250   0.9763   0.01079   0.00470  -0.1068   0.6382   1.0000
   4.500   0.9965   0.01083   0.00465  -0.1047   0.5976   1.0000
   4.750   1.0145   0.01114   0.00474  -0.1023   0.5418   1.0000
   5.000   1.0200   0.01233   0.00508  -0.0977   0.3751   1.0000
   5.250   1.0071   0.01598   0.00675  -0.0916   0.0638   1.0000
   5.500   1.0230   0.01720   0.00790  -0.0894   0.0408   1.0000
   5.750   1.0405   0.01817   0.00904  -0.0874   0.0359   1.0000
   6.000   1.0529   0.01956   0.01056  -0.0847   0.0332   1.0000
   6.250   1.0634   0.02122   0.01233  -0.0817   0.0318   1.0000
   6.500   1.0814   0.02215   0.01334  -0.0799   0.0291   1.0000
   6.750   1.0976   0.02362   0.01487  -0.0778   0.0279   1.0000
   7.000   1.1176   0.02539   0.01669  -0.0762   0.0273   1.0000
   7.250   1.1433   0.02754   0.01894  -0.0754   0.0275   1.0000
   7.500   1.1740   0.03044   0.02199  -0.0752   0.0291   1.0000
   7.750   1.2114   0.03592   0.02762  -0.0762   0.0325   1.0000
   8.000   1.2337   0.03731   0.02925  -0.0745   0.0332   1.0000
  13.500   1.0382   0.14993   0.14668  -0.0744   0.0421   1.0000
  13.750   1.0324   0.15803   0.15476  -0.0797   0.0409   1.0000
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