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GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 389 AIRFOIL (goe389-il)
Reynolds number: 100,000
Max Cl/Cd: 55.03 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe389-il-100000.txt
Download as CSV file: xf-goe389-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 389 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3421   0.10174   0.09684  -0.0312   1.0000   0.0963
  -8.500  -0.3588   0.10037   0.09561  -0.0348   1.0000   0.0989
  -8.250  -0.3825   0.09931   0.09473  -0.0375   1.0000   0.0994
  -8.000  -0.3433   0.09297   0.08828  -0.0322   1.0000   0.1043
  -7.750  -0.3449   0.09072   0.08611  -0.0313   1.0000   0.1083
  -7.500  -0.3606   0.08916   0.08469  -0.0305   1.0000   0.1112
  -7.250  -0.3859   0.08781   0.08349  -0.0342   1.0000   0.1132
  -7.000  -0.4054   0.08519   0.08093  -0.0382   1.0000   0.1143
  -6.750  -0.3900   0.08201   0.07782  -0.0288   1.0000   0.1171
  -6.500  -0.3925   0.08011   0.07598  -0.0260   1.0000   0.1200
  -6.250  -0.4001   0.07811   0.07403  -0.0256   1.0000   0.1239
  -6.000  -0.4127   0.07454   0.07038  -0.0334   1.0000   0.1293
  -5.750  -0.4102   0.07228   0.06822  -0.0282   1.0000   0.1312
  -5.500  -0.4042   0.07007   0.06569  -0.0359   1.0000   0.1431
  -5.250  -0.4009   0.06632   0.06213  -0.0319   1.0000   0.1449
  -4.500  -0.3015   0.05516   0.05063  -0.0467   0.9838   0.1907
  -4.250  -0.2702   0.05204   0.04745  -0.0496   0.9764   0.2069
  -4.000  -0.2305   0.04915   0.04441  -0.0546   0.9706   0.2361
  -3.750  -0.1580   0.03492   0.02835  -0.0694   0.9660   0.1184
  -3.500  -0.1076   0.03043   0.02257  -0.0732   0.9609   0.0991
  -3.250  -0.0648   0.02848   0.02014  -0.0762   0.9546   0.0996
  -3.000  -0.0237   0.02650   0.01781  -0.0788   0.9476   0.1000
  -2.750   0.0218   0.02470   0.01573  -0.0820   0.9419   0.1007
  -2.500   0.0605   0.02334   0.01430  -0.0840   0.9335   0.1031
  -2.250   0.1057   0.02227   0.01316  -0.0870   0.9271   0.1088
  -2.000   0.1459   0.02129   0.01220  -0.0891   0.9184   0.1175
  -1.750   0.1902   0.02029   0.01126  -0.0918   0.9113   0.1299
  -1.500   0.2308   0.01917   0.01039  -0.0938   0.9027   0.1649
  -1.250   0.2608   0.01657   0.01000  -0.0938   0.8948   0.6587
  -1.000   0.3147   0.01567   0.00938  -0.0970   0.8869   1.0000
  -0.750   0.3483   0.01556   0.00901  -0.0975   0.8741   1.0000
  -0.500   0.3812   0.01542   0.00867  -0.0978   0.8608   1.0000
  -0.250   0.4127   0.01527   0.00834  -0.0978   0.8468   1.0000
   0.000   0.4428   0.01512   0.00802  -0.0974   0.8317   1.0000
   0.250   0.4718   0.01496   0.00771  -0.0968   0.8157   1.0000
   0.500   0.5005   0.01481   0.00740  -0.0961   0.7990   1.0000
   0.750   0.5290   0.01468   0.00711  -0.0953   0.7820   1.0000
   1.000   0.5560   0.01465   0.00693  -0.0944   0.7629   1.0000
   1.250   0.5822   0.01472   0.00685  -0.0935   0.7427   1.0000
   1.500   0.6092   0.01483   0.00679  -0.0927   0.7238   1.0000
   1.750   0.6362   0.01500   0.00679  -0.0921   0.7058   1.0000
   2.000   0.6612   0.01526   0.00694  -0.0913   0.6864   1.0000
   2.250   0.6867   0.01552   0.00710  -0.0906   0.6689   1.0000
   2.500   0.7125   0.01577   0.00726  -0.0900   0.6529   1.0000
   2.750   0.7384   0.01602   0.00742  -0.0894   0.6383   1.0000
   3.000   0.7644   0.01627   0.00762  -0.0889   0.6248   1.0000
   3.250   0.7908   0.01653   0.00780  -0.0885   0.6126   1.0000
   3.500   0.8174   0.01679   0.00798  -0.0881   0.6011   1.0000
   3.750   0.8429   0.01713   0.00831  -0.0876   0.5891   1.0000
   4.000   0.8686   0.01746   0.00864  -0.0871   0.5775   1.0000
   4.250   0.8947   0.01778   0.00892  -0.0867   0.5665   1.0000
   4.500   0.9216   0.01810   0.00914  -0.0863   0.5560   1.0000
   4.750   0.9466   0.01849   0.00958  -0.0858   0.5443   1.0000
   5.000   0.9716   0.01894   0.01006  -0.0853   0.5337   1.0000
   5.250   0.9980   0.01939   0.01048  -0.0850   0.5243   1.0000
   5.500   1.0234   0.01984   0.01096  -0.0846   0.5141   1.0000
   5.750   1.0479   0.02038   0.01161  -0.0841   0.5043   1.0000
   6.000   1.0752   0.02089   0.01209  -0.0839   0.4965   1.0000
   6.250   1.0983   0.02144   0.01280  -0.0832   0.4861   1.0000
   6.500   1.1227   0.02198   0.01345  -0.0826   0.4764   1.0000
   6.750   1.1494   0.02242   0.01385  -0.0823   0.4665   1.0000
   7.000   1.1718   0.02276   0.01428  -0.0812   0.4528   1.0000
   7.250   1.1947   0.02292   0.01442  -0.0801   0.4366   1.0000
   7.500   1.2153   0.02308   0.01468  -0.0787   0.4200   1.0000
   7.750   1.2355   0.02323   0.01494  -0.0773   0.4036   1.0000
   8.000   1.2550   0.02337   0.01520  -0.0757   0.3870   1.0000
   8.250   1.2738   0.02351   0.01548  -0.0741   0.3703   1.0000
   8.500   1.2921   0.02368   0.01579  -0.0724   0.3533   1.0000
   8.750   1.3084   0.02378   0.01601  -0.0704   0.3332   1.0000
   9.000   1.3229   0.02404   0.01644  -0.0682   0.3091   1.0000
   9.250   1.3360   0.02444   0.01692  -0.0659   0.2808   1.0000
   9.500   1.3439   0.02520   0.01757  -0.0630   0.2376   1.0000
   9.750   1.3461   0.02659   0.01868  -0.0597   0.1857   1.0000
  10.000   1.3381   0.02874   0.02044  -0.0553   0.1388   1.0000
  10.250   1.3255   0.03137   0.02283  -0.0508   0.1059   1.0000
  10.500   1.3156   0.03407   0.02539  -0.0472   0.0750   1.0000
  10.750   1.3073   0.03679   0.02803  -0.0443   0.0647   1.0000
  11.000   1.2979   0.03978   0.03100  -0.0420   0.0596   1.0000
  11.250   1.2926   0.04263   0.03400  -0.0403   0.0556   1.0000
  11.500   1.2858   0.04580   0.03724  -0.0390   0.0525   1.0000
  11.750   1.2764   0.04934   0.04080  -0.0379   0.0502   1.0000
  12.000   1.2759   0.05213   0.04372  -0.0369   0.0480   1.0000
  12.250   1.2766   0.05481   0.04653  -0.0358   0.0460   1.0000
  12.500   1.2791   0.05732   0.04911  -0.0346   0.0444   1.0000
  12.750   1.2842   0.05959   0.05142  -0.0333   0.0430   1.0000
  13.000   1.2931   0.06153   0.05335  -0.0316   0.0416   1.0000
  13.250   1.3173   0.06277   0.05451  -0.0285   0.0401   1.0000
  13.500   1.3282   0.06518   0.05714  -0.0272   0.0396   1.0000
  13.750   1.3337   0.06808   0.06029  -0.0264   0.0390   1.0000
  14.000   1.3344   0.07140   0.06388  -0.0258   0.0384   1.0000
  14.250   1.3313   0.07513   0.06787  -0.0256   0.0379   1.0000
  14.500   1.3253   0.07923   0.07223  -0.0257   0.0374   1.0000
  14.750   1.3163   0.08375   0.07700  -0.0262   0.0372   1.0000
  15.000   1.3045   0.08874   0.08226  -0.0272   0.0370   1.0000
  15.250   1.2900   0.09427   0.08805  -0.0289   0.0371   1.0000
  15.500   1.2730   0.10039   0.09443  -0.0312   0.0372   1.0000
  15.750   1.2540   0.10718   0.10147  -0.0343   0.0374   1.0000
  16.000   1.2332   0.11466   0.10918  -0.0383   0.0377   1.0000
  16.250   1.2112   0.12282   0.11755  -0.0430   0.0381   1.0000
  16.500   1.1882   0.13174   0.12667  -0.0486   0.0386   1.0000
  16.750   1.1650   0.14134   0.13642  -0.0547   0.0391   1.0000
  17.000   1.1441   0.15111   0.14630  -0.0608   0.0397   1.0000
  17.250   1.0301   0.20257   0.19769  -0.0934   0.0566   1.0000
  17.500   1.0391   0.20713   0.20232  -0.0944   0.0618   1.0000
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