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GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 401 AIRFOIL (goe401-il)
Reynolds number: 100,000
Max Cl/Cd: 53.88 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe401-il-100000.txt
Download as CSV file: xf-goe401-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 401 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3104   0.09386   0.08902  -0.0215   1.0000   0.0694
  -7.250  -0.3132   0.09207   0.08732  -0.0214   1.0000   0.0711
  -7.000  -0.3148   0.09084   0.08618  -0.0239   1.0000   0.0729
  -6.750  -0.3137   0.09152   0.08688  -0.0318   1.0000   0.0741
  -6.500  -0.3099   0.08787   0.08329  -0.0327   1.0000   0.0748
  -6.250  -0.3067   0.08254   0.07807  -0.0264   1.0000   0.0762
  -6.000  -0.3036   0.07970   0.07530  -0.0241   1.0000   0.0778
  -5.750  -0.3024   0.07750   0.07316  -0.0229   1.0000   0.0793
  -5.500  -0.3031   0.07556   0.07128  -0.0218   1.0000   0.0811
  -5.250  -0.3038   0.07377   0.06952  -0.0212   1.0000   0.0831
  -5.000  -0.3008   0.07221   0.06796  -0.0220   1.0000   0.0859
  -4.750  -0.2780   0.07318   0.06859  -0.0309   1.0000   0.0888
  -4.500  -0.2808   0.06843   0.06399  -0.0275   1.0000   0.0896
  -4.250  -0.2693   0.06451   0.06016  -0.0267   0.9973   0.0913
  -4.000  -0.2326   0.06076   0.05636  -0.0316   0.9896   0.0972
  -3.750  -0.1749   0.05725   0.05252  -0.0430   0.9806   0.1051
  -3.500  -0.1422   0.05321   0.04849  -0.0461   0.9728   0.1091
  -3.000  -0.0565   0.04679   0.04174  -0.0573   0.9536   0.1232
  -2.750  -0.0041   0.04429   0.03890  -0.0640   0.9453   0.1354
  -2.500   0.0313   0.04160   0.03617  -0.0667   0.9344   0.1466
  -2.250   0.0710   0.03845   0.03293  -0.0704   0.9250   0.1557
  -2.000   0.1186   0.03575   0.03004  -0.0750   0.9171   0.1705
  -1.750   0.1634   0.03401   0.02800  -0.0787   0.9062   0.1935
  -1.500   0.2051   0.03095   0.02494  -0.0820   0.8975   0.2124
  -1.250   0.2441   0.02888   0.02272  -0.0844   0.8857   0.2531
  -1.000   0.2773   0.02705   0.02081  -0.0853   0.8710   0.2963
  -0.750   0.3098   0.02507   0.01875  -0.0859   0.8552   0.3294
  -0.500   0.3780   0.02343   0.01565  -0.0879   0.8400   0.1161
  -0.250   0.4135   0.02197   0.01361  -0.0874   0.8221   0.1034
   0.000   0.4403   0.02068   0.01217  -0.0864   0.7996   0.1019
   0.250   0.4693   0.01967   0.01092  -0.0855   0.7779   0.1014
   0.500   0.4964   0.01892   0.00994  -0.0844   0.7549   0.1049
   0.750   0.5226   0.01834   0.00929  -0.0834   0.7316   0.1104
   1.000   0.5493   0.01781   0.00858  -0.0823   0.7095   0.1153
   1.250   0.5748   0.01731   0.00803  -0.0811   0.6875   0.1233
   1.500   0.6015   0.01692   0.00756  -0.0802   0.6680   0.1435
   1.750   0.6282   0.01616   0.00690  -0.0795   0.6504   0.2401
   2.000   0.6828   0.01460   0.00662  -0.0848   0.6288   1.0000
   2.250   0.7074   0.01488   0.00667  -0.0838   0.6127   1.0000
   2.500   0.7321   0.01518   0.00676  -0.0829   0.5978   1.0000
   2.750   0.7569   0.01549   0.00689  -0.0820   0.5839   1.0000
   3.000   0.7819   0.01582   0.00705  -0.0812   0.5711   1.0000
   3.250   0.8067   0.01616   0.00727  -0.0804   0.5585   1.0000
   3.500   0.8309   0.01653   0.00757  -0.0795   0.5459   1.0000
   3.750   0.8552   0.01693   0.00790  -0.0787   0.5341   1.0000
   4.000   0.8802   0.01734   0.00821  -0.0780   0.5232   1.0000
   4.250   0.9052   0.01775   0.00855  -0.0773   0.5125   1.0000
   4.500   0.9288   0.01821   0.00903  -0.0765   0.5012   1.0000
   4.750   0.9532   0.01871   0.00950  -0.0757   0.4909   1.0000
   5.000   0.9787   0.01920   0.00991  -0.0752   0.4813   1.0000
   5.250   1.0015   0.01973   0.01053  -0.0742   0.4703   1.0000
   5.500   1.0257   0.02032   0.01113  -0.0735   0.4609   1.0000
   5.750   1.0504   0.02088   0.01167  -0.0729   0.4515   1.0000
   6.000   1.0727   0.02153   0.01247  -0.0719   0.4414   1.0000
   6.250   1.0975   0.02214   0.01304  -0.0713   0.4324   1.0000
   6.500   1.1199   0.02268   0.01368  -0.0703   0.4216   1.0000
   6.750   1.1415   0.02326   0.01435  -0.0692   0.4104   1.0000
   7.000   1.1649   0.02373   0.01485  -0.0683   0.3997   1.0000
   7.250   1.1877   0.02420   0.01539  -0.0673   0.3896   1.0000
   7.500   1.2084   0.02483   0.01620  -0.0661   0.3797   1.0000
   7.750   1.2323   0.02520   0.01658  -0.0653   0.3700   1.0000
   8.000   1.2530   0.02554   0.01709  -0.0640   0.3591   1.0000
   8.250   1.2729   0.02599   0.01773  -0.0626   0.3487   1.0000
   8.500   1.2932   0.02599   0.01782  -0.0611   0.3357   1.0000
   8.750   1.3105   0.02559   0.01751  -0.0590   0.3184   1.0000
   9.000   1.3257   0.02511   0.01710  -0.0566   0.2988   1.0000
   9.250   1.3388   0.02499   0.01715  -0.0540   0.2782   1.0000
   9.500   1.3485   0.02503   0.01732  -0.0509   0.2487   1.0000
   9.750   1.3490   0.02583   0.01796  -0.0468   0.1878   1.0000
  10.000   1.3371   0.02832   0.01982  -0.0419   0.1199   1.0000
  10.250   1.3254   0.03073   0.02196  -0.0370   0.0988   1.0000
  10.500   1.3139   0.03306   0.02417  -0.0326   0.0891   1.0000
  10.750   1.3074   0.03529   0.02648  -0.0291   0.0812   1.0000
  11.000   1.2977   0.03796   0.02909  -0.0262   0.0761   1.0000
  11.250   1.2962   0.04028   0.03154  -0.0241   0.0710   1.0000
  11.500   1.2954   0.04284   0.03399  -0.0221   0.0667   1.0000
  11.750   1.3077   0.04495   0.03611  -0.0203   0.0630   1.0000
  12.000   1.3201   0.04702   0.03829  -0.0188   0.0596   1.0000
  12.250   1.3604   0.05002   0.04101  -0.0187   0.0539   1.0000
  12.500   1.3653   0.05231   0.04360  -0.0171   0.0527   1.0000
  12.750   1.3733   0.05503   0.04663  -0.0157   0.0517   1.0000
  13.000   1.3779   0.05805   0.04993  -0.0145   0.0508   1.0000
  13.250   1.3775   0.06132   0.05348  -0.0133   0.0503   1.0000
  13.500   1.3716   0.06482   0.05726  -0.0123   0.0497   1.0000
  13.750   1.3622   0.06861   0.06132  -0.0117   0.0493   1.0000
  14.000   1.3502   0.07272   0.06570  -0.0117   0.0491   1.0000
  14.250   1.3345   0.07737   0.07060  -0.0122   0.0490   1.0000
  14.500   1.3166   0.08244   0.07592  -0.0135   0.0487   1.0000
  14.750   1.2956   0.08823   0.08197  -0.0156   0.0490   1.0000
  15.000   1.2716   0.09491   0.08890  -0.0187   0.0496   1.0000
  15.250   1.2454   0.10239   0.09662  -0.0227   0.0502   1.0000
  15.500   1.2185   0.11063   0.10507  -0.0275   0.0509   1.0000
  15.750   1.1917   0.11967   0.11428  -0.0330   0.0519   1.0000
  16.000   1.1637   0.12968   0.12442  -0.0394   0.0526   1.0000
  16.250   1.1427   0.13911   0.13391  -0.0447   0.0536   1.0000
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