Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il)
Reynolds number: 100,000
Max Cl/Cd: 54.27 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe321-il-100000.txt
Download as CSV file: xf-goe321-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 321 (HANSA-BRANDENBURG III.1) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2793   0.10159   0.09717  -0.0261   1.0000   0.0772
  -8.250  -0.2872   0.10056   0.09629  -0.0317   1.0000   0.0789
  -8.000  -0.3128   0.10110   0.09704  -0.0293   1.0000   0.0790
  -7.750  -0.2920   0.09566   0.09158  -0.0419   0.9852   0.0802
  -7.500  -0.2624   0.09032   0.08625  -0.0379   0.9829   0.0825
  -7.250  -0.2327   0.08579   0.08169  -0.0437   0.9708   0.0856
  -7.000  -0.2057   0.08146   0.07729  -0.0528   0.9551   0.0898
  -6.750  -0.1822   0.07816   0.07369  -0.0712   0.9313   0.0935
  -6.500  -0.1659   0.07322   0.06886  -0.0679   0.9199   0.0949
  -6.250  -0.1498   0.07013   0.06576  -0.0670   0.9067   0.0974
  -6.000  -0.1340   0.06740   0.06296  -0.0683   0.8930   0.1017
  -5.750  -0.1125   0.06469   0.05987  -0.0774   0.8778   0.1087
  -5.500  -0.1006   0.06127   0.05655  -0.0749   0.8657   0.1108
  -5.250  -0.0850   0.05881   0.05405  -0.0743   0.8546   0.1146
  -5.000  -0.0593   0.05677   0.05155  -0.0798   0.8439   0.1243
  -4.750  -0.0451   0.05349   0.04838  -0.0784   0.8331   0.1269
  -4.500  -0.0265   0.05134   0.04614  -0.0781   0.8250   0.1329
  -4.250  -0.0030   0.04893   0.04351  -0.0805   0.8152   0.1428
  -4.000   0.0176   0.04706   0.04155  -0.0803   0.8079   0.1516
  -3.750   0.0389   0.04484   0.03923  -0.0811   0.7988   0.1628
  -3.500   0.0605   0.04297   0.03720  -0.0812   0.7925   0.1790
  -3.250   0.0830   0.04129   0.03548  -0.0819   0.7838   0.1969
  -3.000   0.1061   0.03992   0.03390  -0.0823   0.7778   0.2258
  -2.750   0.1264   0.03810   0.03214  -0.0819   0.7712   0.2473
  -2.500   0.1463   0.03662   0.03069  -0.0813   0.7644   0.2835
  -2.250   0.1542   0.01917   0.01384  -0.0752   0.7461   0.3313
  -2.000   0.1853   0.03383   0.02791  -0.0795   0.7526   0.3771
  -1.750   0.2040   0.03191   0.02611  -0.0778   0.7469   0.4157
  -1.500   0.2271   0.03032   0.02448  -0.0767   0.7424   0.4506
  -1.250   0.3214   0.02930   0.02098  -0.0861   0.7353   0.1353
  -1.000   0.3517   0.02815   0.01941  -0.0854   0.7290   0.1195
  -0.750   0.3797   0.02718   0.01819  -0.0848   0.7220   0.1131
  -0.500   0.4076   0.02654   0.01732  -0.0842   0.7143   0.1112
  -0.250   0.4351   0.02586   0.01649  -0.0834   0.7092   0.1134
   0.000   0.4617   0.02561   0.01622  -0.0834   0.7012   0.1138
   0.250   0.4893   0.02510   0.01563  -0.0828   0.6955   0.1149
   0.500   0.5159   0.02483   0.01534  -0.0823   0.6897   0.1177
   0.750   0.5418   0.02476   0.01528  -0.0819   0.6823   0.1236
   1.000   0.5678   0.02407   0.01466  -0.0807   0.6769   0.1329
   1.250   0.5921   0.02405   0.01469  -0.0802   0.6677   0.1434
   1.500   0.6198   0.02347   0.01410  -0.0793   0.6610   0.1751
   1.750   0.6506   0.02147   0.01395  -0.0791   0.6514   1.0000
   2.000   0.6781   0.02129   0.01346  -0.0779   0.6442   1.0000
   2.250   0.7027   0.02151   0.01358  -0.0773   0.6337   1.0000
   2.500   0.7308   0.02120   0.01303  -0.0762   0.6268   1.0000
   2.750   0.7553   0.02140   0.01320  -0.0756   0.6156   1.0000
   3.000   0.7825   0.02126   0.01291  -0.0748   0.6078   1.0000
   3.250   0.8084   0.02131   0.01290  -0.0741   0.5981   1.0000
   3.500   0.8346   0.02134   0.01286  -0.0735   0.5892   1.0000
   3.750   0.8620   0.02118   0.01261  -0.0728   0.5805   1.0000
   4.000   0.8873   0.02130   0.01271  -0.0722   0.5697   1.0000
   4.250   0.9164   0.02100   0.01225  -0.0715   0.5621   1.0000
   4.500   0.9409   0.02117   0.01245  -0.0709   0.5497   1.0000
   4.750   0.9667   0.02124   0.01249  -0.0702   0.5381   1.0000
   5.000   0.9944   0.02111   0.01223  -0.0696   0.5277   1.0000
   5.250   1.0202   0.02112   0.01222  -0.0689   0.5145   1.0000
   5.500   1.0449   0.02122   0.01231  -0.0682   0.4998   1.0000
   5.750   1.0697   0.02127   0.01234  -0.0674   0.4842   1.0000
   6.000   1.0944   0.02129   0.01234  -0.0666   0.4675   1.0000
   6.250   1.1188   0.02128   0.01227  -0.0658   0.4495   1.0000
   6.500   1.1416   0.02138   0.01234  -0.0648   0.4290   1.0000
   6.750   1.1638   0.02157   0.01249  -0.0638   0.4071   1.0000
   7.000   1.1863   0.02186   0.01261  -0.0628   0.3876   1.0000
   7.250   1.2082   0.02241   0.01299  -0.0619   0.3693   1.0000
   7.500   1.2301   0.02314   0.01357  -0.0611   0.3537   1.0000
   7.750   1.2530   0.02395   0.01424  -0.0605   0.3410   1.0000
   8.000   1.2749   0.02486   0.01516  -0.0598   0.3300   1.0000
   8.250   1.2993   0.02578   0.01599  -0.0595   0.3219   1.0000
   8.500   1.3220   0.02671   0.01699  -0.0591   0.3143   1.0000
   8.750   1.3487   0.02767   0.01780  -0.0591   0.3083   1.0000
   9.000   1.3685   0.02869   0.01904  -0.0583   0.3022   1.0000
   9.250   1.3925   0.02966   0.02004  -0.0581   0.2972   1.0000
   9.500   1.4208   0.03074   0.02103  -0.0585   0.2933   1.0000
   9.750   1.4390   0.03197   0.02254  -0.0576   0.2898   1.0000
  10.000   1.4582   0.03322   0.02401  -0.0569   0.2863   1.0000
  10.250   1.4792   0.03445   0.02542  -0.0564   0.2832   1.0000
  10.500   1.5025   0.03566   0.02671  -0.0562   0.2803   1.0000
  10.750   1.5297   0.03702   0.02805  -0.0566   0.2773   1.0000
  11.000   1.5395   0.03867   0.03010  -0.0549   0.2746   1.0000
  11.250   1.5509   0.04043   0.03218  -0.0536   0.2719   1.0000
  11.500   1.5652   0.04182   0.03377  -0.0524   0.2679   1.0000
  11.750   1.5974   0.04226   0.03403  -0.0531   0.2614   1.0000
  12.000   1.5930   0.04402   0.03620  -0.0500   0.2566   1.0000
  12.250   1.6166   0.04398   0.03611  -0.0495   0.2486   1.0000
  12.500   1.6219   0.04530   0.03762  -0.0475   0.2430   1.0000
  12.750   1.6252   0.04633   0.03884  -0.0451   0.2370   1.0000
  13.000   1.6452   0.04635   0.03877  -0.0443   0.2290   1.0000
  13.250   1.6324   0.04796   0.04066  -0.0405   0.2243   1.0000
  13.500   1.6579   0.04734   0.03985  -0.0400   0.2153   1.0000
  13.750   1.6369   0.04969   0.04253  -0.0361   0.2122   1.0000
  14.000   1.6272   0.05164   0.04469  -0.0338   0.2078   1.0000
  14.250   1.6478   0.05146   0.04440  -0.0331   0.2003   1.0000
  14.500   1.6242   0.05488   0.04816  -0.0311   0.1973   1.0000
  14.750   1.6118   0.05757   0.05104  -0.0300   0.1926   1.0000
  15.000   1.6191   0.05827   0.05171  -0.0292   0.1848   1.0000
  15.250   1.5940   0.06279   0.05654  -0.0289   0.1813   1.0000
  15.500   1.5991   0.06348   0.05714  -0.0284   0.1715   1.0000
  15.750   1.5696   0.06915   0.06315  -0.0291   0.1682   1.0000
  16.000   1.5640   0.07133   0.06528  -0.0293   0.1578   1.0000
  16.250   1.5314   0.07830   0.07261  -0.0311   0.1546   1.0000
  16.500   1.5064   0.08452   0.07902  -0.0333   0.1478   1.0000
  16.750   1.4805   0.09140   0.08607  -0.0359   0.1409   1.0000
  17.000   1.4460   0.10035   0.09528  -0.0395   0.1370   1.0000
  17.250   1.3704   0.11784   0.11302  -0.0462   0.1474   1.0000
  17.500   1.3191   0.13178   0.12700  -0.0527   0.1449   1.0000
<< Back to GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il)

Polar data table (+)

Polar graphs


<< Back to GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il)