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

GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il)
Reynolds number: 200,000
Max Cl/Cd: 73.59 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe315-il-200000.txt
Download as CSV file: xf-goe315-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3729   0.10275   0.09911  -0.0172   1.0000   0.0334
  -8.750  -0.3765   0.10077   0.09718  -0.0208   1.0000   0.0336
  -8.500  -0.3813   0.09860   0.09508  -0.0240   1.0000   0.0338
  -8.250  -0.3719   0.09335   0.08985  -0.0224   1.0000   0.0343
  -8.000  -0.3605   0.08967   0.08618  -0.0207   1.0000   0.0349
  -7.750  -0.3568   0.08689   0.08344  -0.0207   1.0000   0.0354
  -7.500  -0.3559   0.08427   0.08088  -0.0210   1.0000   0.0359
  -7.250  -0.3527   0.08143   0.07808  -0.0220   1.0000   0.0366
  -7.000  -0.3481   0.07845   0.07514  -0.0237   1.0000   0.0374
  -6.750  -0.3424   0.07538   0.07209  -0.0257   1.0000   0.0384
  -6.500  -0.3343   0.07221   0.06893  -0.0287   1.0000   0.0398
  -6.250  -0.3163   0.06957   0.06609  -0.0371   1.0000   0.0413
  -6.000  -0.3091   0.06574   0.06220  -0.0382   1.0000   0.0417
  -5.750  -0.3092   0.06204   0.05866  -0.0355   1.0000   0.0423
  -5.500  -0.2991   0.05923   0.05592  -0.0351   0.9972   0.0431
  -5.250  -0.2636   0.05528   0.05190  -0.0404   0.9882   0.0451
  -5.000  -0.2229   0.05124   0.04770  -0.0469   0.9771   0.0481
  -4.750  -0.1710   0.04713   0.04302  -0.0551   0.9636   0.0519
  -4.500  -0.1423   0.04289   0.03888  -0.0583   0.9517   0.0536
  -4.250  -0.1075   0.04002   0.03593  -0.0617   0.9373   0.0567
  -4.000  -0.0563   0.04062   0.03574  -0.0650   0.9199   0.0634
  -3.750  -0.0322   0.03426   0.02952  -0.0678   0.9027   0.0656
  -3.500  -0.0036   0.03200   0.02717  -0.0691   0.8831   0.0686
  -3.250   0.0324   0.03382   0.02824  -0.0685   0.8622   0.0771
  -3.000   0.0495   0.02859   0.02313  -0.0690   0.8438   0.0800
  -2.750   0.0724   0.02716   0.02159  -0.0685   0.8257   0.0853
  -2.500   0.0977   0.02595   0.01998  -0.0678   0.8089   0.0941
  -2.250   0.1207   0.02453   0.01847  -0.0672   0.7928   0.0994
  -2.000   0.1453   0.02338   0.01704  -0.0665   0.7776   0.1101
  -1.750   0.1697   0.02245   0.01587  -0.0659   0.7630   0.1238
  -1.500   0.1936   0.02137   0.01464  -0.0653   0.7491   0.1392
  -1.250   0.2172   0.02025   0.01344  -0.0648   0.7361   0.1580
  -0.250   0.3339   0.01652   0.00831  -0.0600   0.6820   0.0753
   0.000   0.3604   0.01550   0.00719  -0.0593   0.6695   0.0715
   0.250   0.3872   0.01490   0.00645  -0.0586   0.6594   0.0702
   0.500   0.4137   0.01444   0.00595  -0.0580   0.6485   0.0714
   0.750   0.4399   0.01396   0.00544  -0.0573   0.6385   0.0706
   1.000   0.4659   0.01358   0.00500  -0.0566   0.6293   0.0706
   1.250   0.4916   0.01324   0.00470  -0.0559   0.6186   0.0716
   1.500   0.5173   0.01300   0.00444  -0.0553   0.6093   0.0735
   1.750   0.5432   0.01285   0.00424  -0.0547   0.6001   0.0767
   2.000   0.5689   0.01268   0.00408  -0.0541   0.5901   0.0851
   2.250   0.5951   0.01260   0.00395  -0.0535   0.5806   0.0983
   2.500   0.6482   0.01062   0.00386  -0.0588   0.5684   1.0000
   2.750   0.6734   0.01076   0.00393  -0.0581   0.5572   1.0000
   3.000   0.6985   0.01094   0.00402  -0.0574   0.5466   1.0000
   3.250   0.7234   0.01112   0.00409  -0.0567   0.5342   1.0000
   3.500   0.7475   0.01127   0.00415  -0.0558   0.5177   1.0000
   3.750   0.7716   0.01140   0.00423  -0.0549   0.4999   1.0000
   4.000   0.7957   0.01154   0.00432  -0.0540   0.4823   1.0000
   4.250   0.8201   0.01168   0.00444  -0.0532   0.4658   1.0000
   4.500   0.8445   0.01184   0.00458  -0.0524   0.4484   1.0000
   4.750   0.8685   0.01201   0.00470  -0.0516   0.4294   1.0000
   5.000   0.8924   0.01218   0.00485  -0.0508   0.4059   1.0000
   5.250   0.9154   0.01244   0.00500  -0.0499   0.3788   1.0000
   5.500   0.9381   0.01277   0.00523  -0.0489   0.3540   1.0000
   5.750   0.9610   0.01313   0.00552  -0.0481   0.3324   1.0000
   6.000   0.9837   0.01353   0.00585  -0.0472   0.3134   1.0000
   6.250   1.0065   0.01394   0.00622  -0.0464   0.2970   1.0000
   6.500   1.0288   0.01437   0.00660  -0.0455   0.2799   1.0000
   6.750   1.0511   0.01481   0.00700  -0.0447   0.2632   1.0000
   7.000   1.0734   0.01523   0.00742  -0.0438   0.2436   1.0000
   7.250   1.0951   0.01572   0.00789  -0.0429   0.2223   1.0000
   7.500   1.1158   0.01630   0.00839  -0.0418   0.1915   1.0000
   7.750   1.1250   0.01804   0.00944  -0.0396   0.0898   1.0000
   8.000   1.1395   0.01932   0.01062  -0.0378   0.0696   1.0000
   8.250   1.1561   0.02029   0.01160  -0.0363   0.0617   1.0000
   8.500   1.1735   0.02112   0.01254  -0.0348   0.0580   1.0000
   8.750   1.1896   0.02200   0.01351  -0.0332   0.0553   1.0000
   9.000   1.2025   0.02306   0.01462  -0.0312   0.0529   1.0000
   9.250   1.2113   0.02437   0.01596  -0.0289   0.0509   1.0000
   9.500   1.2227   0.02542   0.01712  -0.0268   0.0494   1.0000
   9.750   1.2309   0.02657   0.01837  -0.0242   0.0483   1.0000
  10.000   1.2374   0.02780   0.01967  -0.0215   0.0473   1.0000
  10.250   1.2438   0.02913   0.02105  -0.0191   0.0460   1.0000
  10.500   1.2503   0.03058   0.02252  -0.0170   0.0448   1.0000
  10.750   1.2576   0.03232   0.02427  -0.0151   0.0435   1.0000
  11.000   1.2723   0.03452   0.02648  -0.0138   0.0422   1.0000
  11.250   1.2861   0.03603   0.02812  -0.0124   0.0416   1.0000
  11.500   1.2993   0.03765   0.02990  -0.0112   0.0408   1.0000
  11.750   1.3121   0.03945   0.03185  -0.0100   0.0398   1.0000
  12.000   1.3230   0.04131   0.03384  -0.0088   0.0385   1.0000
  12.250   1.3364   0.04341   0.03609  -0.0078   0.0377   1.0000
  12.500   1.3476   0.04575   0.03860  -0.0067   0.0371   1.0000
  12.750   1.3565   0.04831   0.04131  -0.0057   0.0365   1.0000
  13.000   1.3658   0.05123   0.04436  -0.0049   0.0357   1.0000
  13.250   1.3751   0.05606   0.04940  -0.0046   0.0348   1.0000
  13.500   1.3683   0.06070   0.05432  -0.0036   0.0345   1.0000
  13.750   1.3586   0.06437   0.05823  -0.0027   0.0345   1.0000
  14.000   1.3460   0.06822   0.06232  -0.0023   0.0345   1.0000
  14.250   1.3329   0.07200   0.06630  -0.0024   0.0345   1.0000
  14.500   1.3186   0.07594   0.07046  -0.0030   0.0346   1.0000
  14.750   1.3034   0.08008   0.07479  -0.0042   0.0348   1.0000
  15.000   1.2855   0.08479   0.07971  -0.0061   0.0349   1.0000
  15.250   1.2653   0.09018   0.08532  -0.0089   0.0352   1.0000
  15.500   1.2358   0.09725   0.09269  -0.0134   0.0359   1.0000
  15.750   1.1738   0.11130   0.10717  -0.0237   0.0372   1.0000
  16.000   1.1183   0.12775   0.12391  -0.0353   0.0386   1.0000
  16.250   1.0710   0.14492   0.14121  -0.0463   0.0410   1.0000
  16.500   1.0576   0.15366   0.14995  -0.0503   0.0422   1.0000
<< Back to GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il)

Polar data table (+)

Polar graphs


<< Back to GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il)