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GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 371 AIRFOIL (goe371-il)
Reynolds number: 50,000
Max Cl/Cd: 37.65 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe371-il-50000.txt
Download as CSV file: xf-goe371-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 371 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3437   0.11322   0.10619  -0.0241   1.0000   0.1249
  -8.750  -0.3438   0.11142   0.10446  -0.0248   1.0000   0.1300
  -8.500  -0.3543   0.11152   0.10472  -0.0264   1.0000   0.1321
  -8.250  -0.3369   0.10550   0.09867  -0.0249   1.0000   0.1379
  -8.000  -0.3390   0.10379   0.09706  -0.0249   1.0000   0.1447
  -7.750  -0.3522   0.10372   0.09716  -0.0253   1.0000   0.1466
  -7.500  -0.3365   0.09836   0.09181  -0.0237   1.0000   0.1535
  -7.250  -0.3433   0.09701   0.09060  -0.0230   1.0000   0.1593
  -7.000  -0.3576   0.09746   0.09122  -0.0265   1.0000   0.1619
  -6.500  -0.3501   0.09098   0.08489  -0.0238   1.0000   0.1757
  -6.000  -0.3487   0.08571   0.07979  -0.0221   1.0000   0.1899
  -5.500  -0.3501   0.08201   0.07620  -0.0242   1.0000   0.2059
  -5.250  -0.3463   0.07785   0.07215  -0.0182   1.0000   0.2139
  -4.750  -0.3434   0.07310   0.06748  -0.0175   1.0000   0.2392
  -4.500  -0.3403   0.07061   0.06503  -0.0159   1.0000   0.2556
  -4.000  -0.3321   0.06567   0.06017  -0.0135   1.0000   0.2988
  -3.750  -0.3267   0.06326   0.05778  -0.0124   1.0000   0.3264
  -3.500  -0.3228   0.06076   0.05534  -0.0095   1.0000   0.3566
  -2.250  -0.3447   0.04917   0.04428   0.0261   1.0000   0.6088
  -2.000  -0.3512   0.04698   0.04219   0.0335   1.0000   0.6619
  -1.750  -0.3544   0.04448   0.03978   0.0407   1.0000   0.7043
  -1.500  -0.3520   0.04192   0.03728   0.0450   1.0000   0.7373
  -1.250  -0.0131   0.03464   0.02616  -0.0517   1.0000   0.1986
  -1.000   0.0198   0.03309   0.02390  -0.0527   1.0000   0.1750
  -0.750   0.0461   0.03174   0.02216  -0.0529   1.0000   0.1649
  -0.500   0.0709   0.03090   0.02096  -0.0528   1.0000   0.1594
  -0.250   0.0932   0.03023   0.02004  -0.0526   1.0000   0.1577
   0.000   0.1140   0.02992   0.01947  -0.0522   1.0000   0.1601
   0.250   0.1418   0.02972   0.01902  -0.0532   0.9970   0.1629
   0.500   0.2018   0.02961   0.01861  -0.0593   0.9833   0.1674
   0.750   0.2564   0.02960   0.01840  -0.0646   0.9679   0.1782
   1.000   0.3072   0.02955   0.01841  -0.0694   0.9519   0.2068
   1.250   0.3619   0.02744   0.01810  -0.0742   0.9379   1.0000
   1.500   0.4057   0.02832   0.01844  -0.0776   0.9194   1.0000
   1.750   0.4487   0.02915   0.01900  -0.0811   0.9021   1.0000
   2.000   0.4913   0.02991   0.01959  -0.0843   0.8857   1.0000
   2.250   0.5321   0.03062   0.02019  -0.0871   0.8701   1.0000
   2.500   0.5708   0.03129   0.02079  -0.0894   0.8549   1.0000
   2.750   0.6025   0.03203   0.02149  -0.0906   0.8394   1.0000
   3.000   0.6349   0.03273   0.02218  -0.0917   0.8243   1.0000
   3.250   0.6674   0.03339   0.02287  -0.0927   0.8094   1.0000
   3.500   0.6989   0.03394   0.02345  -0.0933   0.7931   1.0000
   3.750   0.7379   0.03397   0.02354  -0.0942   0.7746   1.0000
   4.000   0.7856   0.03332   0.02303  -0.0954   0.7566   1.0000
   4.250   0.8304   0.03259   0.02241  -0.0958   0.7397   1.0000
   4.500   0.8620   0.03252   0.02245  -0.0951   0.7223   1.0000
   4.750   0.8872   0.03277   0.02282  -0.0938   0.7034   1.0000
   5.000   0.9200   0.03248   0.02271  -0.0928   0.6852   1.0000
   5.250   0.9576   0.03174   0.02212  -0.0919   0.6671   1.0000
   5.500   0.9819   0.03179   0.02232  -0.0900   0.6451   1.0000
   5.750   1.0194   0.03077   0.02148  -0.0887   0.6234   1.0000
   6.000   1.0467   0.03041   0.02126  -0.0866   0.5970   1.0000
   6.250   1.0773   0.02988   0.02079  -0.0846   0.5684   1.0000
   6.500   1.1094   0.02947   0.02033  -0.0827   0.5368   1.0000
   6.750   1.1308   0.03015   0.02109  -0.0804   0.5022   1.0000
   7.000   1.1541   0.03082   0.02172  -0.0784   0.4684   1.0000
   7.250   1.1769   0.03143   0.02226  -0.0763   0.4359   1.0000
   7.500   1.1975   0.03210   0.02288  -0.0742   0.4049   1.0000
   7.750   1.2162   0.03287   0.02374  -0.0720   0.3758   1.0000
   8.000   1.2344   0.03370   0.02463  -0.0698   0.3477   1.0000
   8.250   1.2511   0.03454   0.02550  -0.0674   0.3182   1.0000
   8.500   1.2632   0.03543   0.02644  -0.0644   0.2847   1.0000
   8.750   1.2705   0.03603   0.02671  -0.0610   0.2449   1.0000
   9.000   1.2739   0.03747   0.02779  -0.0576   0.2048   1.0000
   9.250   1.2764   0.03996   0.03017  -0.0542   0.1662   1.0000
   9.500   1.2825   0.04296   0.03298  -0.0512   0.1348   1.0000
   9.750   1.2925   0.04599   0.03623  -0.0487   0.1170   1.0000
  10.000   1.3040   0.04886   0.03921  -0.0468   0.1050   1.0000
  10.250   1.3222   0.05223   0.04256  -0.0457   0.0966   1.0000
  10.500   1.3251   0.05631   0.04728  -0.0431   0.0935   1.0000
  10.750   1.3251   0.06040   0.05183  -0.0407   0.0910   1.0000
  11.000   1.3238   0.06423   0.05596  -0.0384   0.0886   1.0000
  11.250   1.3356   0.06831   0.05997  -0.0376   0.0846   1.0000
  11.500   1.3189   0.07224   0.06430  -0.0347   0.0843   1.0000
  11.750   1.2996   0.07623   0.06857  -0.0320   0.0842   1.0000
  12.000   1.2792   0.08058   0.07318  -0.0303   0.0844   1.0000
  12.250   1.2580   0.08549   0.07830  -0.0297   0.0846   1.0000
  12.500   1.1721   0.09657   0.08992  -0.0354   0.0941   1.0000
  12.750   1.1460   0.10458   0.09801  -0.0394   0.0955   1.0000
  13.000   1.1253   0.11288   0.10635  -0.0435   0.0966   1.0000
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