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GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il)
Reynolds number: 100,000
Max Cl/Cd: 55.76 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe315-il-100000-n5.txt
Download as CSV file: xf-goe315-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 315 (HANSA-BRANDENBURG III.5) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3449   0.09287   0.08797  -0.0215   1.0000   0.0471
  -7.750  -0.3492   0.09086   0.08605  -0.0236   1.0000   0.0483
  -7.500  -0.3497   0.08856   0.08381  -0.0287   1.0000   0.0489
  -7.250  -0.3446   0.08581   0.08105  -0.0336   1.0000   0.0492
  -7.000  -0.3371   0.08290   0.07810  -0.0371   1.0000   0.0494
  -6.750  -0.3330   0.07781   0.07318  -0.0333   1.0000   0.0504
  -6.500  -0.3267   0.07482   0.07027  -0.0306   1.0000   0.0518
  -6.250  -0.3199   0.07211   0.06760  -0.0304   1.0000   0.0538
  -6.000  -0.3129   0.06938   0.06490  -0.0313   1.0000   0.0559
  -5.750  -0.2995   0.06638   0.06187  -0.0343   0.9970   0.0587
  -5.500  -0.2510   0.06223   0.05721  -0.0471   0.9760   0.0616
  -5.250  -0.2306   0.05705   0.05216  -0.0484   0.9624   0.0632
  -5.000  -0.2037   0.05368   0.04878  -0.0509   0.9465   0.0668
  -4.750  -0.1570   0.05167   0.04609  -0.0584   0.9260   0.0752
  -4.500  -0.1330   0.04665   0.04120  -0.0604   0.9105   0.0771
  -4.250  -0.1032   0.04356   0.03801  -0.0627   0.8935   0.0803
  -4.000  -0.0628   0.04253   0.03626  -0.0661   0.8751   0.0898
  -3.750  -0.0399   0.03835   0.03221  -0.0672   0.8588   0.0928
  -3.500  -0.0098   0.03691   0.03034  -0.0684   0.8421   0.1053
  -3.000   0.0520   0.03055   0.02311  -0.0683   0.8127   0.0591
  -2.750   0.0780   0.02855   0.02085  -0.0681   0.7986   0.0565
  -2.500   0.1053   0.02698   0.01895  -0.0679   0.7853   0.0564
  -2.250   0.1327   0.02562   0.01725  -0.0675   0.7727   0.0568
  -2.000   0.1599   0.02424   0.01555  -0.0670   0.7601   0.0554
  -1.750   0.1871   0.02300   0.01400  -0.0665   0.7476   0.0540
  -1.500   0.2144   0.02192   0.01262  -0.0659   0.7360   0.0531
  -1.250   0.2418   0.02099   0.01141  -0.0653   0.7252   0.0526
  -1.000   0.2687   0.02018   0.01040  -0.0648   0.7133   0.0526
  -0.750   0.2953   0.01957   0.00967  -0.0643   0.7021   0.0540
  -0.500   0.3220   0.01904   0.00901  -0.0638   0.6916   0.0560
  -0.250   0.3486   0.01848   0.00835  -0.0632   0.6808   0.0569
   0.000   0.3750   0.01796   0.00776  -0.0626   0.6697   0.0572
   0.250   0.4008   0.01749   0.00723  -0.0619   0.6582   0.0578
   0.500   0.4258   0.01706   0.00675  -0.0610   0.6446   0.0586
   0.750   0.4504   0.01671   0.00633  -0.0600   0.6300   0.0597
   1.000   0.4755   0.01645   0.00597  -0.0591   0.6161   0.0611
   1.250   0.5012   0.01619   0.00568  -0.0586   0.6033   0.0654
   1.500   0.5275   0.01609   0.00552  -0.0581   0.5921   0.0704
   1.750   0.5541   0.01603   0.00534  -0.0576   0.5820   0.0746
   2.000   0.5806   0.01596   0.00522  -0.0571   0.5719   0.0831
   2.250   0.6072   0.01582   0.00520  -0.0567   0.5613   0.1297
   2.750   0.6773   0.01427   0.00525  -0.0595   0.5400   1.0000
   3.000   0.7023   0.01447   0.00539  -0.0588   0.5286   1.0000
   3.250   0.7272   0.01469   0.00553  -0.0581   0.5176   1.0000
   3.500   0.7521   0.01493   0.00566  -0.0574   0.5068   1.0000
   3.750   0.7768   0.01515   0.00589  -0.0568   0.4947   1.0000
   4.000   0.8016   0.01539   0.00612  -0.0561   0.4828   1.0000
   4.250   0.8260   0.01563   0.00635  -0.0554   0.4695   1.0000
   4.500   0.8499   0.01586   0.00656  -0.0545   0.4529   1.0000
   4.750   0.8734   0.01608   0.00676  -0.0537   0.4337   1.0000
   5.000   0.8966   0.01632   0.00697  -0.0528   0.4134   1.0000
   5.250   0.9199   0.01660   0.00723  -0.0519   0.3933   1.0000
   5.500   0.9427   0.01692   0.00749  -0.0510   0.3724   1.0000
   5.750   0.9647   0.01730   0.00780  -0.0500   0.3503   1.0000
   6.000   0.9867   0.01773   0.00816  -0.0491   0.3297   1.0000
   6.250   1.0087   0.01819   0.00858  -0.0482   0.3129   1.0000
   6.500   1.0306   0.01867   0.00905  -0.0473   0.2984   1.0000
   6.750   1.0525   0.01916   0.00958  -0.0464   0.2858   1.0000
   7.000   1.0739   0.01967   0.01011  -0.0454   0.2733   1.0000
   7.250   1.0945   0.02023   0.01067  -0.0444   0.2572   1.0000
   7.500   1.1149   0.02080   0.01127  -0.0434   0.2426   1.0000
   7.750   1.1350   0.02139   0.01193  -0.0424   0.2277   1.0000
   8.000   1.1545   0.02201   0.01261  -0.0413   0.2095   1.0000
   8.250   1.1725   0.02274   0.01334  -0.0400   0.1848   1.0000
   8.500   1.1883   0.02365   0.01417  -0.0386   0.1364   1.0000
   8.750   1.1923   0.02565   0.01564  -0.0362   0.0858   1.0000
   9.000   1.2026   0.02707   0.01705  -0.0342   0.0718   1.0000
   9.250   1.2136   0.02834   0.01839  -0.0323   0.0634   1.0000
   9.750   1.2307   0.03092   0.02115  -0.0281   0.0556   1.0000
  10.000   1.2356   0.03225   0.02260  -0.0256   0.0534   1.0000
  10.250   1.2384   0.03377   0.02425  -0.0232   0.0515   1.0000
  10.500   1.2382   0.03560   0.02616  -0.0212   0.0499   1.0000
  10.750   1.2376   0.03762   0.02829  -0.0195   0.0484   1.0000
  11.000   1.2375   0.03979   0.03060  -0.0183   0.0472   1.0000
  11.250   1.2369   0.04217   0.03312  -0.0175   0.0461   1.0000
  11.500   1.2358   0.04477   0.03584  -0.0170   0.0451   1.0000
  11.750   1.2345   0.04749   0.03867  -0.0166   0.0441   1.0000
  12.000   1.2330   0.05034   0.04160  -0.0164   0.0431   1.0000
  12.250   1.2314   0.05324   0.04456  -0.0162   0.0420   1.0000
  12.500   1.2335   0.05579   0.04717  -0.0157   0.0409   1.0000
  12.750   1.2374   0.05825   0.04978  -0.0154   0.0399   1.0000
  13.000   1.2426   0.06060   0.05226  -0.0149   0.0389   1.0000
  13.250   1.2479   0.06301   0.05479  -0.0145   0.0377   1.0000
  13.500   1.2526   0.06553   0.05738  -0.0142   0.0364   1.0000
  13.750   1.2604   0.06771   0.05955  -0.0136   0.0351   1.0000
  14.000   1.2731   0.06973   0.06162  -0.0124   0.0339   1.0000
  14.250   1.2715   0.07329   0.06544  -0.0129   0.0333   1.0000
  14.500   1.2682   0.07713   0.06953  -0.0137   0.0326   1.0000
  14.750   1.2634   0.08126   0.07390  -0.0149   0.0319   1.0000
  15.000   1.2575   0.08564   0.07849  -0.0163   0.0312   1.0000
  15.250   1.2507   0.09021   0.08326  -0.0179   0.0305   1.0000
  15.500   1.2435   0.09502   0.08825  -0.0198   0.0300   1.0000
  15.750   1.2347   0.10021   0.09362  -0.0222   0.0294   1.0000
  16.000   1.2247   0.10579   0.09938  -0.0248   0.0291   1.0000
  16.250   1.2131   0.11187   0.10565  -0.0280   0.0288   1.0000
  16.500   1.1994   0.11866   0.11264  -0.0319   0.0287   1.0000
  16.750   1.1827   0.12639   0.12057  -0.0366   0.0286   1.0000
  17.000   1.1597   0.13608   0.13049  -0.0430   0.0288   1.0000
  17.250   1.1192   0.15154   0.14625  -0.0537   0.0295   1.0000
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