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GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il)
Reynolds number: 200,000
Max Cl/Cd: 71.21 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe316-il-200000.txt
Download as CSV file: xf-goe316-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.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  -0.4090   0.10783   0.10445   0.0009   1.0000   0.0336
  -8.750  -0.4034   0.10452   0.10117  -0.0012   1.0000   0.0346
  -8.500  -0.3994   0.10152   0.09821  -0.0049   1.0000   0.0356
  -8.250  -0.3005   0.08559   0.08254  -0.0169   1.0000   0.0373
  -8.000  -0.2926   0.08206   0.07903  -0.0167   1.0000   0.0382
  -7.750  -0.2884   0.07860   0.07560  -0.0176   1.0000   0.0390
  -7.500  -0.3797   0.08621   0.08305  -0.0188   1.0000   0.0371
  -7.250  -0.3697   0.08296   0.07982  -0.0180   1.0000   0.0379
  -7.000  -0.3588   0.07955   0.07644  -0.0201   1.0000   0.0388
  -6.750  -0.3465   0.07594   0.07284  -0.0235   1.0000   0.0399
  -6.500  -0.3326   0.07221   0.06911  -0.0274   1.0000   0.0412
  -6.250  -0.3154   0.06840   0.06527  -0.0326   1.0000   0.0431
  -6.000  -0.2862   0.06548   0.06197  -0.0428   0.9963   0.0447
  -5.750  -0.2636   0.05857   0.05516  -0.0462   0.9856   0.0456
  -5.500  -0.2362   0.05487   0.05148  -0.0490   0.9720   0.0471
  -5.250  -0.2038   0.05124   0.04773  -0.0533   0.9551   0.0493
  -5.000  -0.1601   0.04901   0.04496  -0.0586   0.9330   0.0546
  -4.750  -0.1375   0.04445   0.04011  -0.0602   0.9126   0.0557
  -4.500  -0.1218   0.04119   0.03689  -0.0598   0.8921   0.0571
  -4.250  -0.1033   0.03906   0.03467  -0.0591   0.8724   0.0593
  -4.000  -0.0802   0.03707   0.03245  -0.0589   0.8551   0.0630
  -3.750  -0.0505   0.03513   0.02990  -0.0592   0.8405   0.0684
  -3.500  -0.0301   0.03247   0.02724  -0.0591   0.8266   0.0704
  -3.250  -0.0065   0.03076   0.02537  -0.0589   0.8132   0.0739
  -3.000   0.0220   0.02947   0.02357  -0.0587   0.8006   0.0829
  -2.750   0.0450   0.02750   0.02161  -0.0586   0.7875   0.0870
  -2.500   0.0732   0.02646   0.02015  -0.0584   0.7741   0.0977
  -2.250   0.0980   0.02474   0.01841  -0.0584   0.7606   0.1032
  -2.000   0.1247   0.02346   0.01689  -0.0583   0.7473   0.1153
  -1.750   0.1510   0.02227   0.01553  -0.0582   0.7339   0.1304
  -1.500   0.1779   0.02182   0.01486  -0.0580   0.7203   0.1534
  -1.250   0.2027   0.02034   0.01328  -0.0581   0.7068   0.1871
  -1.000   0.2283   0.01885   0.01180  -0.0581   0.6928   0.2115
  -0.750   0.2564   0.01793   0.01071  -0.0578   0.6778   0.2295
  -0.500   0.3002   0.01745   0.00910  -0.0550   0.6635   0.0817
  -0.250   0.3281   0.01617   0.00775  -0.0546   0.6467   0.0772
   0.000   0.3561   0.01553   0.00700  -0.0542   0.6270   0.0774
   0.250   0.3837   0.01490   0.00624  -0.0538   0.6056   0.0764
   0.500   0.4111   0.01439   0.00559  -0.0533   0.5820   0.0753
   0.750   0.4380   0.01403   0.00508  -0.0528   0.5566   0.0755
   1.000   0.4649   0.01378   0.00471  -0.0525   0.5301   0.0766
   1.250   0.4918   0.01368   0.00446  -0.0522   0.5065   0.0790
   1.500   0.5189   0.01353   0.00423  -0.0520   0.4859   0.0838
   1.750   0.5464   0.01351   0.00410  -0.0519   0.4694   0.0890
   2.000   0.5741   0.01355   0.00402  -0.0518   0.4562   0.0968
   2.250   0.6017   0.01347   0.00399  -0.0518   0.4461   0.1430
   2.750   0.6553   0.01197   0.00412  -0.0511   0.4300   1.0000
   3.000   0.6829   0.01222   0.00427  -0.0511   0.4230   1.0000
   3.250   0.7103   0.01253   0.00445  -0.0510   0.4174   1.0000
   3.500   0.7380   0.01278   0.00467  -0.0510   0.4119   1.0000
   3.750   0.7656   0.01306   0.00491  -0.0510   0.4074   1.0000
   4.000   0.7930   0.01343   0.00516  -0.0510   0.4037   1.0000
   4.250   0.8207   0.01371   0.00548  -0.0510   0.3999   1.0000
   4.500   0.8483   0.01401   0.00579  -0.0510   0.3963   1.0000
   4.750   0.8758   0.01434   0.00612  -0.0511   0.3930   1.0000
   5.000   0.9033   0.01472   0.00646  -0.0511   0.3898   1.0000
   5.250   0.9306   0.01510   0.00686  -0.0511   0.3864   1.0000
   5.500   0.9578   0.01539   0.00724  -0.0511   0.3816   1.0000
   5.750   0.9847   0.01569   0.00750  -0.0510   0.3759   1.0000
   6.000   1.0112   0.01602   0.00788  -0.0509   0.3698   1.0000
   6.250   1.0377   0.01627   0.00818  -0.0508   0.3630   1.0000
   6.500   1.0644   0.01671   0.00856  -0.0508   0.3578   1.0000
   6.750   1.0907   0.01698   0.00900  -0.0507   0.3527   1.0000
   7.000   1.1173   0.01732   0.00941  -0.0506   0.3482   1.0000
   7.250   1.1439   0.01779   0.00984  -0.0506   0.3434   1.0000
   7.500   1.1695   0.01807   0.01033  -0.0504   0.3380   1.0000
   7.750   1.1954   0.01836   0.01069  -0.0502   0.3319   1.0000
   8.000   1.2209   0.01873   0.01113  -0.0500   0.3254   1.0000
   8.250   1.2457   0.01889   0.01144  -0.0496   0.3171   1.0000
   8.500   1.2699   0.01908   0.01172  -0.0492   0.3076   1.0000
   8.750   1.2935   0.01914   0.01181  -0.0487   0.2957   1.0000
   9.000   1.3165   0.01912   0.01193  -0.0481   0.2824   1.0000
   9.250   1.3395   0.01912   0.01211  -0.0475   0.2676   1.0000
   9.500   1.3630   0.01914   0.01237  -0.0470   0.2463   1.0000
   9.750   1.3828   0.01950   0.01263  -0.0462   0.1920   1.0000
  10.000   1.3879   0.02168   0.01429  -0.0442   0.1257   1.0000
  10.250   1.3911   0.02401   0.01629  -0.0420   0.0807   1.0000
  10.500   1.3921   0.02626   0.01843  -0.0395   0.0628   1.0000
  10.750   1.3876   0.02856   0.02080  -0.0363   0.0540   1.0000
  11.000   1.3784   0.03105   0.02334  -0.0332   0.0493   1.0000
  11.250   1.3722   0.03377   0.02619  -0.0314   0.0458   1.0000
  11.500   1.3712   0.03638   0.02892  -0.0306   0.0424   1.0000
  11.750   1.3669   0.03952   0.03213  -0.0303   0.0401   1.0000
  12.000   1.3560   0.04344   0.03606  -0.0299   0.0384   1.0000
  12.250   1.3587   0.04610   0.03890  -0.0298   0.0367   1.0000
  12.500   1.3582   0.04910   0.04202  -0.0297   0.0351   1.0000
  12.750   1.3573   0.05214   0.04515  -0.0296   0.0338   1.0000
  13.000   1.3564   0.05520   0.04827  -0.0296   0.0327   1.0000
  13.250   1.3552   0.05819   0.05127  -0.0292   0.0317   1.0000
  13.500   1.3564   0.06069   0.05378  -0.0277   0.0305   1.0000
  13.750   1.3583   0.06356   0.05681  -0.0277   0.0297   1.0000
  14.000   1.3596   0.06648   0.05987  -0.0277   0.0287   1.0000
  14.250   1.3603   0.06952   0.06303  -0.0278   0.0278   1.0000
  14.500   1.3612   0.07251   0.06614  -0.0278   0.0270   1.0000
  14.750   1.3625   0.07546   0.06920  -0.0278   0.0264   1.0000
  15.000   1.3637   0.07847   0.07229  -0.0278   0.0258   1.0000
  15.250   1.3660   0.08134   0.07523  -0.0274   0.0253   1.0000
  15.500   1.3696   0.08410   0.07808  -0.0263   0.0247   1.0000
  15.750   1.3669   0.08809   0.08223  -0.0259   0.0244   1.0000
  16.000   1.3583   0.09292   0.08729  -0.0275   0.0243   1.0000
  16.250   1.3481   0.09818   0.09277  -0.0296   0.0242   1.0000
  16.500   1.3364   0.10384   0.09864  -0.0320   0.0241   1.0000
  16.750   1.3231   0.10997   0.10499  -0.0350   0.0240   1.0000
  17.000   1.3089   0.11650   0.11173  -0.0384   0.0240   1.0000
  17.250   1.2935   0.12352   0.11896  -0.0423   0.0240   1.0000
  17.500   1.2770   0.13100   0.12663  -0.0467   0.0240   1.0000
  17.750   1.2597   0.13897   0.13479  -0.0516   0.0241   1.0000
  18.000   1.2422   0.14733   0.14333  -0.0568   0.0242   1.0000
  18.250   1.2239   0.15626   0.15241  -0.0626   0.0243   1.0000
  18.500   1.2063   0.16549   0.16180  -0.0687   0.0245   1.0000
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