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GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL (goe320-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL (goe320-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.13 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe320-il-1000000.txt
Download as CSV file: xf-goe320-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1411   0.09110   0.08847  -0.0438   0.7329   0.0231
  -8.000  -0.1399   0.08716   0.08454  -0.0483   0.7275   0.0232
  -7.750  -0.1351   0.08355   0.08091  -0.0517   0.7217   0.0232
  -7.500  -0.1286   0.08021   0.07755  -0.0528   0.7164   0.0233
  -7.250  -0.1155   0.07768   0.07502  -0.0537   0.7116   0.0234
  -7.000  -0.1020   0.07511   0.07244  -0.0556   0.7060   0.0235
  -6.750  -0.0874   0.07250   0.06979  -0.0581   0.7004   0.0237
  -6.500  -0.0715   0.06977   0.06705  -0.0611   0.6957   0.0238
  -6.250  -0.0542   0.06693   0.06419  -0.0645   0.6911   0.0241
  -6.000  -0.0354   0.06400   0.06123  -0.0681   0.6865   0.0244
  -5.750  -0.0153   0.06097   0.05814  -0.0718   0.6818   0.0248
  -5.500   0.0066   0.05776   0.05489  -0.0757   0.6775   0.0253
  -5.250   0.0433   0.05079   0.04774  -0.0864   0.6736   0.0265
  -5.000   0.0648   0.04643   0.04328  -0.0896   0.6690   0.0267
  -4.750   0.0864   0.04439   0.04116  -0.0907   0.6631   0.0269
  -4.500   0.1097   0.04252   0.03926  -0.0918   0.6572   0.0271
  -4.250   0.1342   0.04063   0.03730  -0.0931   0.6507   0.0273
  -4.000   0.1598   0.03867   0.03525  -0.0945   0.6451   0.0277
  -3.750   0.1869   0.03650   0.03300  -0.0960   0.6407   0.0283
  -3.500   0.2238   0.02990   0.02598  -0.0992   0.6368   0.0304
  -3.250   0.2488   0.02842   0.02443  -0.0998   0.6314   0.0306
  -3.000   0.2750   0.02723   0.02316  -0.1003   0.6256   0.0308
  -2.750   0.3021   0.02601   0.02187  -0.1008   0.6197   0.0311
  -2.500   0.3297   0.02474   0.02049  -0.1012   0.6124   0.0316
  -2.250   0.3581   0.02328   0.01890  -0.1016   0.6057   0.0326
  -2.000   0.3903   0.01380   0.00817  -0.1016   0.6019   0.0304
  -1.750   0.4191   0.01304   0.00721  -0.1016   0.5934   0.0303
  -1.500   0.4478   0.01197   0.00594  -0.1017   0.5841   0.0304
  -1.250   0.4761   0.01122   0.00506  -0.1017   0.5719   0.0309
  -1.000   0.5048   0.01102   0.00480  -0.1018   0.5568   0.0314
  -0.750   0.5332   0.01081   0.00450  -0.1018   0.5354   0.0319
  -0.500   0.5599   0.01078   0.00419  -0.1015   0.4802   0.0324
  -0.250   0.5844   0.01109   0.00411  -0.1010   0.4068   0.0329
   0.000   0.6110   0.01116   0.00398  -0.1008   0.3739   0.0334
   0.250   0.6386   0.01115   0.00386  -0.1007   0.3568   0.0339
   0.500   0.6664   0.01115   0.00377  -0.1006   0.3454   0.0343
   0.750   0.6941   0.01094   0.00353  -0.1005   0.3362   0.0352
   1.000   0.7221   0.01094   0.00350  -0.1005   0.3285   0.0361
   1.250   0.7503   0.01094   0.00348  -0.1005   0.3225   0.0372
   1.500   0.7781   0.01101   0.00350  -0.1004   0.3162   0.0384
   1.750   0.8062   0.01095   0.00343  -0.1004   0.3114   0.0399
   2.000   0.8345   0.01095   0.00344  -0.1005   0.3075   0.0416
   2.250   0.8625   0.01100   0.00347  -0.1004   0.3029   0.0434
   2.500   0.8901   0.01105   0.00351  -0.1004   0.2975   0.0465
   2.750   0.9181   0.01109   0.00355  -0.1004   0.2935   0.0508
   3.000   0.9462   0.01111   0.00359  -0.1004   0.2895   0.0581
   3.250   0.9738   0.01117   0.00367  -0.1004   0.2847   0.0727
   3.500   1.0010   0.01123   0.00383  -0.1003   0.2792   0.1282
   3.750   1.0249   0.00968   0.00413  -0.1000   0.2757   1.0000
   4.000   1.0524   0.00982   0.00422  -0.0999   0.2709   1.0000
   4.250   1.0792   0.01002   0.00434  -0.0998   0.2645   1.0000
   4.500   1.1062   0.01019   0.00447  -0.0997   0.2587   1.0000
   4.750   1.1329   0.01039   0.00460  -0.0995   0.2507   1.0000
   5.000   1.1590   0.01062   0.00476  -0.0993   0.2415   1.0000
   5.250   1.1842   0.01091   0.00495  -0.0989   0.2285   1.0000
   5.500   1.2085   0.01127   0.00519  -0.0985   0.2124   1.0000
   5.750   1.2320   0.01167   0.00547  -0.0979   0.1976   1.0000
   6.000   1.2554   0.01206   0.00577  -0.0972   0.1877   1.0000
   6.250   1.2797   0.01236   0.00603  -0.0968   0.1829   1.0000
   6.500   1.3036   0.01268   0.00631  -0.0962   0.1790   1.0000
   6.750   1.3267   0.01303   0.00662  -0.0956   0.1751   1.0000
   7.000   1.3501   0.01335   0.00693  -0.0950   0.1726   1.0000
   7.250   1.3741   0.01361   0.00719  -0.0945   0.1714   1.0000
   7.500   1.3974   0.01389   0.00748  -0.0939   0.1702   1.0000
   7.750   1.4202   0.01419   0.00779  -0.0932   0.1689   1.0000
   8.000   1.4421   0.01452   0.00811  -0.0924   0.1676   1.0000
   8.250   1.4631   0.01487   0.00846  -0.0914   0.1664   1.0000
   8.500   1.4826   0.01524   0.00884  -0.0902   0.1652   1.0000
   8.750   1.4997   0.01566   0.00927  -0.0886   0.1639   1.0000
   9.000   1.5162   0.01613   0.00976  -0.0870   0.1627   1.0000
   9.250   1.5321   0.01667   0.01032  -0.0854   0.1614   1.0000
   9.500   1.5471   0.01730   0.01097  -0.0837   0.1600   1.0000
   9.750   1.5640   0.01786   0.01156  -0.0825   0.1592   1.0000
  10.000   1.5824   0.01836   0.01210  -0.0815   0.1589   1.0000
  10.250   1.6001   0.01891   0.01268  -0.0804   0.1586   1.0000
  10.500   1.6178   0.01949   0.01330  -0.0795   0.1581   1.0000
  10.750   1.6357   0.02007   0.01392  -0.0786   0.1574   1.0000
  11.000   1.6533   0.02067   0.01456  -0.0777   0.1564   1.0000
  11.250   1.6706   0.02132   0.01524  -0.0769   0.1553   1.0000
  11.500   1.6872   0.02204   0.01600  -0.0760   0.1544   1.0000
  11.750   1.7032   0.02281   0.01680  -0.0752   0.1535   1.0000
  12.000   1.7184   0.02363   0.01766  -0.0743   0.1524   1.0000
  12.250   1.7327   0.02456   0.01861  -0.0733   0.1514   1.0000
  12.500   1.7458   0.02558   0.01966  -0.0724   0.1501   1.0000
  12.750   1.7574   0.02672   0.02084  -0.0713   0.1489   1.0000
  13.000   1.7671   0.02801   0.02217  -0.0701   0.1477   1.0000
  13.250   1.7755   0.02941   0.02362  -0.0688   0.1463   1.0000
  13.500   1.7925   0.03017   0.02444  -0.0684   0.1459   1.0000
  13.750   1.8099   0.03090   0.02522  -0.0680   0.1450   1.0000
  14.000   1.8250   0.03181   0.02619  -0.0674   0.1441   1.0000
  14.250   1.8391   0.03280   0.02723  -0.0668   0.1430   1.0000
  14.500   1.8523   0.03387   0.02836  -0.0661   0.1420   1.0000
  14.750   1.8652   0.03498   0.02951  -0.0655   0.1408   1.0000
  15.000   1.8770   0.03619   0.03076  -0.0648   0.1395   1.0000
  15.250   1.8870   0.03757   0.03218  -0.0641   0.1379   1.0000
  15.500   1.8933   0.03930   0.03394  -0.0633   0.1359   1.0000
  15.750   1.8992   0.04108   0.03577  -0.0625   0.1340   1.0000
  16.000   1.9151   0.04202   0.03678  -0.0622   0.1329   1.0000
  16.250   1.9296   0.04307   0.03789  -0.0620   0.1311   1.0000
  16.500   1.9422   0.04431   0.03918  -0.0616   0.1287   1.0000
  16.750   1.9504   0.04599   0.04088  -0.0612   0.1258   1.0000
  17.000   1.9554   0.04800   0.04291  -0.0606   0.1225   1.0000
  17.250   1.9669   0.04936   0.04433  -0.0604   0.1182   1.0000
  17.500   1.9689   0.05173   0.04667  -0.0599   0.1090   1.0000
  17.750   1.9508   0.05630   0.05111  -0.0591   0.0909   1.0000
  18.000   1.9228   0.06212   0.05688  -0.0583   0.0782   1.0000
  18.250   1.8949   0.06823   0.06302  -0.0580   0.0685   1.0000
  18.500   1.8631   0.07509   0.06991  -0.0582   0.0580   1.0000
  18.750   1.8277   0.08280   0.07767  -0.0590   0.0483   1.0000
  19.000   1.7928   0.09079   0.08573  -0.0603   0.0413   1.0000
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