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GOE 409 AIRFOIL (goe409-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 409 AIRFOIL (goe409-il)
Reynolds number: 100,000
Max Cl/Cd: 38.57 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe409-il-100000.txt
Download as CSV file: xf-goe409-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 409 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7858   0.07787   0.07225  -0.0482   1.0000   0.1022
 -11.750  -0.8050   0.07247   0.06678  -0.0488   1.0000   0.1015
 -11.500  -0.8306   0.06773   0.06194  -0.0481   1.0000   0.1008
 -11.250  -0.8544   0.06362   0.05770  -0.0460   1.0000   0.0997
 -11.000  -0.8823   0.06020   0.05412  -0.0420   1.0000   0.0991
 -10.750  -0.9039   0.05672   0.05042  -0.0379   1.0000   0.0985
 -10.500  -0.9213   0.05339   0.04683  -0.0337   1.0000   0.0986
 -10.250  -0.9338   0.05028   0.04341  -0.0295   1.0000   0.0991
 -10.000  -0.9429   0.04746   0.04025  -0.0252   1.0000   0.0999
  -9.750  -0.9488   0.04493   0.03733  -0.0209   1.0000   0.1010
  -9.500  -0.9513   0.04268   0.03467  -0.0167   1.0000   0.1021
  -9.250  -0.9485   0.04021   0.03187  -0.0133   1.0000   0.1035
  -9.000  -0.9351   0.03802   0.02962  -0.0115   1.0000   0.1055
  -8.750  -0.9216   0.03631   0.02777  -0.0093   1.0000   0.1073
  -8.500  -0.9083   0.03479   0.02608  -0.0071   1.0000   0.1094
  -8.250  -0.8949   0.03320   0.02425  -0.0047   1.0000   0.1111
  -8.000  -0.8793   0.03160   0.02238  -0.0027   1.0000   0.1122
  -7.750  -0.8622   0.03016   0.02071  -0.0008   1.0000   0.1135
  -7.500  -0.8450   0.02901   0.01930   0.0012   1.0000   0.1154
  -7.250  -0.8232   0.02755   0.01780   0.0021   1.0000   0.1174
  -7.000  -0.8016   0.02639   0.01666   0.0032   1.0000   0.1195
  -6.750  -0.7807   0.02540   0.01564   0.0045   1.0000   0.1216
  -6.500  -0.7605   0.02450   0.01471   0.0059   1.0000   0.1242
  -6.250  -0.7409   0.02371   0.01385   0.0074   1.0000   0.1271
  -6.000  -0.7224   0.02292   0.01306   0.0091   1.0000   0.1309
  -5.750  -0.7058   0.02219   0.01242   0.0110   1.0000   0.1354
  -5.500  -0.6892   0.02156   0.01179   0.0130   1.0000   0.1407
  -5.250  -0.6742   0.02087   0.01116   0.0153   1.0000   0.1468
  -5.000  -0.6599   0.02024   0.01059   0.0176   1.0000   0.1557
  -4.750  -0.6469   0.01951   0.00998   0.0202   1.0000   0.1703
  -4.500  -0.6361   0.01856   0.00932   0.0230   1.0000   0.2051
  -4.250  -0.6304   0.01715   0.00869   0.0264   1.0000   0.3054
  -4.000  -0.6246   0.01621   0.00856   0.0302   1.0000   0.4506
  -3.750  -0.6118   0.01587   0.00847   0.0331   1.0000   0.5257
  -3.500  -0.5974   0.01563   0.00848   0.0359   1.0000   0.5815
  -3.250  -0.5810   0.01551   0.00851   0.0382   1.0000   0.6243
  -3.000  -0.5644   0.01547   0.00862   0.0406   1.0000   0.6668
  -2.750  -0.5470   0.01550   0.00874   0.0428   1.0000   0.7038
  -2.500  -0.5286   0.01563   0.00898   0.0450   1.0000   0.7402
  -2.250  -0.5099   0.01588   0.00933   0.0472   1.0000   0.7769
  -2.000  -0.4898   0.01624   0.00974   0.0491   1.0000   0.8109
  -1.750  -0.4670   0.01669   0.01021   0.0504   1.0000   0.8394
  -1.500  -0.4372   0.01728   0.01077   0.0502   0.9982   0.8660
  -1.250  -0.3816   0.01848   0.01190   0.0455   0.9902   0.8940
  -1.000  -0.3056   0.02009   0.01344   0.0379   0.9861   0.9171
  -0.750  -0.2156   0.02144   0.01470   0.0271   0.9842   0.9339
  -0.500  -0.1412   0.02200   0.01520   0.0179   0.9785   0.9458
  -0.250  -0.0714   0.02231   0.01547   0.0092   0.9717   0.9568
   0.000   0.0001   0.02233   0.01548   0.0000   0.9636   0.9636
   0.250   0.0713   0.02231   0.01547  -0.0092   0.9568   0.9717
   0.500   0.1414   0.02199   0.01519  -0.0179   0.9458   0.9784
   0.750   0.2153   0.02144   0.01471  -0.0271   0.9340   0.9842
   1.000   0.3053   0.02010   0.01345  -0.0379   0.9173   0.9862
   1.250   0.3815   0.01848   0.01189  -0.0455   0.8939   0.9903
   1.500   0.4372   0.01727   0.01076  -0.0502   0.8661   0.9983
   1.750   0.4669   0.01669   0.01020  -0.0504   0.8396   1.0000
   2.000   0.4897   0.01624   0.00974  -0.0491   0.8108   1.0000
   2.250   0.5097   0.01588   0.00932  -0.0472   0.7768   1.0000
   2.500   0.5285   0.01563   0.00899  -0.0450   0.7406   1.0000
   2.750   0.5468   0.01550   0.00874  -0.0428   0.7040   1.0000
   3.000   0.5643   0.01547   0.00862  -0.0406   0.6674   1.0000
   3.250   0.5808   0.01551   0.00850  -0.0382   0.6242   1.0000
   3.500   0.5972   0.01562   0.00848  -0.0358   0.5821   1.0000
   3.750   0.6117   0.01586   0.00846  -0.0331   0.5263   1.0000
   4.000   0.6245   0.01620   0.00856  -0.0302   0.4514   1.0000
   4.250   0.6304   0.01713   0.00868  -0.0264   0.3074   1.0000
   4.500   0.6360   0.01855   0.00931  -0.0229   0.2054   1.0000
   4.750   0.6468   0.01951   0.00997  -0.0201   0.1704   1.0000
   5.000   0.6597   0.02024   0.01058  -0.0176   0.1556   1.0000
   5.250   0.6740   0.02087   0.01115  -0.0152   0.1467   1.0000
   5.500   0.6891   0.02156   0.01179  -0.0130   0.1408   1.0000
   5.750   0.7056   0.02218   0.01241  -0.0110   0.1355   1.0000
   6.000   0.7222   0.02291   0.01304  -0.0091   0.1309   1.0000
   6.250   0.7408   0.02371   0.01385  -0.0074   0.1272   1.0000
   6.500   0.7603   0.02450   0.01471  -0.0058   0.1241   1.0000
   6.750   0.7806   0.02539   0.01564  -0.0044   0.1216   1.0000
   7.000   0.8014   0.02638   0.01665  -0.0032   0.1195   1.0000
   7.250   0.8230   0.02753   0.01779  -0.0021   0.1175   1.0000
   7.500   0.8449   0.02901   0.01929  -0.0012   0.1154   1.0000
   7.750   0.8620   0.03015   0.02069   0.0008   0.1136   1.0000
   8.000   0.8792   0.03159   0.02237   0.0027   0.1122   1.0000
   8.250   0.8948   0.03319   0.02424   0.0048   0.1111   1.0000
   8.500   0.9082   0.03476   0.02605   0.0071   0.1094   1.0000
   8.750   0.9215   0.03632   0.02778   0.0094   0.1073   1.0000
   9.000   0.9350   0.03802   0.02962   0.0115   0.1056   1.0000
   9.250   0.9484   0.04021   0.03187   0.0133   0.1035   1.0000
   9.500   0.9509   0.04265   0.03465   0.0168   0.1020   1.0000
   9.750   0.9487   0.04492   0.03733   0.0209   0.1010   1.0000
  10.000   0.9430   0.04748   0.04027   0.0252   0.1000   1.0000
  10.250   0.9338   0.05030   0.04343   0.0295   0.0991   1.0000
  10.500   0.9212   0.05336   0.04680   0.0338   0.0985   1.0000
  10.750   0.9042   0.05675   0.05046   0.0379   0.0986   1.0000
  11.000   0.8824   0.06022   0.05415   0.0419   0.0991   1.0000
  11.250   0.8548   0.06373   0.05781   0.0459   0.0998   1.0000
  11.500   0.8275   0.06782   0.06204   0.0481   0.1006   1.0000
  11.750   0.8021   0.07261   0.06694   0.0487   0.1013   1.0000
  12.000   0.7880   0.07791   0.07229   0.0481   0.1022   1.0000
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