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GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 379 AIRFOIL (goe379-il)
Reynolds number: 50,000
Max Cl/Cd: 41.01 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe379-il-50000-n5.txt
Download as CSV file: xf-goe379-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 379 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2865   0.10227   0.09605  -0.0276   1.0000   0.0603
  -7.250  -0.2925   0.10127   0.09520  -0.0275   1.0000   0.0611
  -7.000  -0.2953   0.10010   0.09416  -0.0283   1.0000   0.0616
  -6.750  -0.2974   0.09896   0.09312  -0.0293   1.0000   0.0619
  -6.500  -0.2982   0.09768   0.09192  -0.0302   1.0000   0.0621
  -6.250  -0.2980   0.09641   0.09072  -0.0314   1.0000   0.0623
  -6.000  -0.2984   0.09071   0.08515  -0.0261   1.0000   0.0636
  -5.750  -0.2992   0.08768   0.08219  -0.0234   1.0000   0.0658
  -5.500  -0.3000   0.08555   0.08012  -0.0223   1.0000   0.0678
  -5.250  -0.2996   0.08357   0.07820  -0.0220   1.0000   0.0704
  -5.000  -0.2959   0.08182   0.07646  -0.0232   1.0000   0.0732
  -4.500  -0.2362   0.07359   0.06810  -0.0356   0.9843   0.0782
  -4.250  -0.2062   0.06946   0.06386  -0.0402   0.9758   0.0821
  -4.000  -0.1525   0.06700   0.06101  -0.0519   0.9655   0.0892
  -3.750  -0.1271   0.06208   0.05609  -0.0545   0.9568   0.0907
  -3.500  -0.0998   0.05815   0.05209  -0.0571   0.9478   0.0933
  -3.000  -0.0042   0.04965   0.04265  -0.0686   0.9308   0.0491
  -2.500   0.0683   0.04264   0.03502  -0.0746   0.9144   0.0489
  -2.250   0.0998   0.03959   0.03169  -0.0762   0.9046   0.0481
  -2.000   0.1408   0.03642   0.02803  -0.0788   0.8978   0.0481
  -1.750   0.1728   0.03427   0.02561  -0.0801   0.8878   0.0537
  -1.500   0.2081   0.03207   0.02288  -0.0811   0.8783   0.0583
  -1.250   0.2502   0.02954   0.01954  -0.0826   0.8714   0.0619
  -1.000   0.2823   0.02817   0.01786  -0.0833   0.8601   0.0774
  -0.750   0.3168   0.02660   0.01576  -0.0837   0.8495   0.0889
  -0.500   0.3582   0.02536   0.01418  -0.0857   0.8398   0.1119
  -0.250   0.3999   0.02429   0.01268  -0.0874   0.8300   0.1313
   0.000   0.4328   0.02355   0.01174  -0.0878   0.8172   0.1460
   0.250   0.4633   0.02296   0.01107  -0.0878   0.8040   0.1640
   0.500   0.4930   0.02247   0.01048  -0.0877   0.7908   0.1900
   0.750   0.5221   0.02182   0.01002  -0.0877   0.7776   0.2459
   1.000   0.5750   0.02010   0.00941  -0.0923   0.7653   1.0000
   1.250   0.6019   0.02021   0.00920  -0.0917   0.7514   1.0000
   1.500   0.6283   0.02034   0.00909  -0.0910   0.7373   1.0000
   1.750   0.6543   0.02049   0.00904  -0.0902   0.7233   1.0000
   2.000   0.6799   0.02065   0.00905  -0.0895   0.7092   1.0000
   2.250   0.7053   0.02083   0.00910  -0.0887   0.6952   1.0000
   2.500   0.7305   0.02103   0.00919  -0.0879   0.6809   1.0000
   2.750   0.7554   0.02124   0.00934  -0.0871   0.6668   1.0000
   3.000   0.7802   0.02148   0.00951  -0.0863   0.6528   1.0000
   3.250   0.8049   0.02173   0.00972  -0.0855   0.6389   1.0000
   3.500   0.8294   0.02200   0.00996  -0.0846   0.6250   1.0000
   3.750   0.8540   0.02230   0.01029  -0.0838   0.6114   1.0000
   4.000   0.8785   0.02261   0.01060  -0.0830   0.5980   1.0000
   4.250   0.9031   0.02294   0.01095  -0.0823   0.5848   1.0000
   4.500   0.9278   0.02329   0.01139  -0.0815   0.5721   1.0000
   4.750   0.9512   0.02373   0.01191  -0.0807   0.5588   1.0000
   5.000   0.9744   0.02420   0.01248  -0.0798   0.5456   1.0000
   5.250   0.9975   0.02470   0.01311  -0.0789   0.5328   1.0000
   5.500   1.0203   0.02520   0.01379  -0.0780   0.5195   1.0000
   5.750   1.0427   0.02568   0.01442  -0.0769   0.5056   1.0000
   6.000   1.0646   0.02619   0.01509  -0.0758   0.4917   1.0000
   6.250   1.0864   0.02674   0.01584  -0.0747   0.4783   1.0000
   6.500   1.1083   0.02732   0.01666  -0.0736   0.4660   1.0000
   6.750   1.1310   0.02792   0.01758  -0.0726   0.4546   1.0000
   7.000   1.1474   0.02828   0.01817  -0.0704   0.4336   1.0000
   7.250   1.1566   0.02820   0.01805  -0.0666   0.3975   1.0000
   7.500   1.1636   0.02859   0.01848  -0.0630   0.3608   1.0000
   7.750   1.1682   0.02927   0.01911  -0.0593   0.3170   1.0000
   8.000   1.1693   0.03041   0.02009  -0.0555   0.2537   1.0000
   8.250   1.1617   0.03262   0.02155  -0.0514   0.1526   1.0000
   8.500   1.1429   0.03625   0.02422  -0.0471   0.0571   1.0000
   8.750   1.1383   0.03892   0.02682  -0.0442   0.0445   1.0000
   9.000   1.1350   0.04156   0.02954  -0.0417   0.0393   1.0000
   9.250   1.1315   0.04429   0.03245  -0.0398   0.0360   1.0000
   9.500   1.1254   0.04742   0.03573  -0.0383   0.0339   1.0000
   9.750   1.1208   0.05057   0.03923  -0.0372   0.0317   1.0000
  10.000   1.1157   0.05397   0.04285  -0.0366   0.0304   1.0000
  10.250   1.1097   0.05764   0.04672  -0.0363   0.0293   1.0000
  10.500   1.1042   0.06140   0.05068  -0.0362   0.0287   1.0000
  10.750   1.0982   0.06534   0.05480  -0.0363   0.0280   1.0000
  11.000   1.0936   0.06918   0.05878  -0.0363   0.0274   1.0000
  11.250   1.0906   0.07278   0.06253  -0.0363   0.0269   1.0000
  11.500   1.0885   0.07619   0.06603  -0.0358   0.0262   1.0000
  11.750   1.0926   0.07876   0.06873  -0.0345   0.0254   1.0000
  12.000   1.1007   0.08103   0.07127  -0.0331   0.0240   1.0000
  12.250   1.1118   0.08301   0.07350  -0.0315   0.0231   1.0000
  12.500   1.1254   0.08508   0.07587  -0.0295   0.0222   1.0000
  12.750   1.1373   0.08779   0.07891  -0.0280   0.0219   1.0000
  13.000   1.1406   0.09166   0.08308  -0.0277   0.0218   1.0000
  13.250   1.1381   0.09623   0.08795  -0.0285   0.0218   1.0000
  13.500   1.1317   0.10136   0.09335  -0.0300   0.0219   1.0000
  13.750   1.1225   0.10705   0.09929  -0.0322   0.0220   1.0000
  14.000   1.1119   0.11308   0.10555  -0.0350   0.0221   1.0000
  14.250   1.1002   0.11964   0.11231  -0.0384   0.0223   1.0000
  14.500   1.0886   0.12648   0.11933  -0.0422   0.0225   1.0000
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