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GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il)
Reynolds number: 100,000
Max Cl/Cd: 54.35 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe315-il-100000.txt
Download as CSV file: xf-goe315-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3690   0.10113   0.09613  -0.0189   1.0000   0.0621
  -8.250  -0.3774   0.10018   0.09530  -0.0224   1.0000   0.0628
  -8.000  -0.3810   0.09870   0.09387  -0.0284   1.0000   0.0632
  -7.750  -0.3779   0.09605   0.09123  -0.0329   1.0000   0.0635
  -7.500  -0.3605   0.08843   0.08370  -0.0226   1.0000   0.0657
  -7.250  -0.3528   0.08530   0.08060  -0.0219   1.0000   0.0682
  -7.000  -0.3478   0.08242   0.07777  -0.0231   1.0000   0.0706
  -6.750  -0.3427   0.07957   0.07497  -0.0255   1.0000   0.0733
  -6.500  -0.3347   0.07778   0.07311  -0.0330   1.0000   0.0763
  -6.250  -0.3263   0.07573   0.07090  -0.0378   1.0000   0.0774
  -6.000  -0.3211   0.07023   0.06563  -0.0340   1.0000   0.0787
  -5.750  -0.3148   0.06714   0.06262  -0.0318   1.0000   0.0806
  -5.500  -0.3087   0.06460   0.06014  -0.0310   1.0000   0.0832
  -5.250  -0.3055   0.06247   0.05803  -0.0304   1.0000   0.0864
  -5.000  -0.3030   0.06397   0.05911  -0.0325   1.0000   0.0914
  -4.750  -0.3076   0.06048   0.05574  -0.0302   1.0000   0.0923
  -4.500  -0.2806   0.05544   0.05088  -0.0325   0.9929   0.0968
  -4.250  -0.2287   0.05177   0.04680  -0.0417   0.9821   0.1077
  -4.000  -0.1925   0.04781   0.04286  -0.0456   0.9724   0.1151
  -3.750  -0.1508   0.04431   0.03915  -0.0511   0.9608   0.1261
  -3.500  -0.1100   0.04119   0.03586  -0.0557   0.9496   0.1417
  -3.250  -0.0649   0.03840   0.03281  -0.0611   0.9406   0.1691
  -3.000  -0.0268   0.03576   0.03004  -0.0646   0.9292   0.1993
  -2.750   0.0054   0.03285   0.02718  -0.0666   0.9166   0.2334
  -2.500   0.0372   0.03097   0.02521  -0.0682   0.9035   0.2899
  -2.250   0.0653   0.02820   0.02258  -0.0685   0.8905   0.3335
  -2.000   0.0930   0.02614   0.02054  -0.0683   0.8768   0.3788
  -1.750   0.1243   0.02445   0.01867  -0.0688   0.8628   0.4045
  -1.500   0.1641   0.02313   0.01690  -0.0708   0.8489   0.3835
  -1.250   0.2308   0.02353   0.01560  -0.0733   0.8348   0.1686
  -1.000   0.2633   0.02250   0.01417  -0.0722   0.8207   0.1303
  -0.750   0.2924   0.02171   0.01305  -0.0712   0.8071   0.1159
  -0.500   0.3197   0.02097   0.01212  -0.0703   0.7941   0.1133
  -0.250   0.3477   0.02046   0.01133  -0.0693   0.7821   0.1083
   0.000   0.3752   0.02010   0.01078  -0.0682   0.7699   0.1056
   0.250   0.4005   0.01946   0.01009  -0.0671   0.7553   0.1047
   0.500   0.4256   0.01896   0.00954  -0.0658   0.7407   0.1047
   0.750   0.4502   0.01856   0.00911  -0.0645   0.7267   0.1057
   1.000   0.4738   0.01807   0.00871  -0.0633   0.7139   0.1108
   1.250   0.4991   0.01787   0.00846  -0.0623   0.7028   0.1177
   1.500   0.5257   0.01766   0.00815  -0.0616   0.6924   0.1248
   1.750   0.5514   0.01754   0.00803  -0.0608   0.6801   0.1412
   2.000   0.6023   0.01544   0.00774  -0.0649   0.6674   1.0000
   2.250   0.6271   0.01564   0.00772  -0.0638   0.6562   1.0000
   2.500   0.6522   0.01578   0.00769  -0.0628   0.6451   1.0000
   2.750   0.6763   0.01598   0.00783  -0.0619   0.6320   1.0000
   3.000   0.7006   0.01617   0.00795  -0.0609   0.6192   1.0000
   3.250   0.7252   0.01634   0.00806  -0.0599   0.6063   1.0000
   3.500   0.7498   0.01650   0.00815  -0.0590   0.5929   1.0000
   3.750   0.7744   0.01666   0.00825  -0.0580   0.5786   1.0000
   4.000   0.7989   0.01685   0.00838  -0.0570   0.5635   1.0000
   4.250   0.8233   0.01709   0.00857  -0.0560   0.5475   1.0000
   4.500   0.8473   0.01735   0.00880  -0.0549   0.5301   1.0000
   4.750   0.8709   0.01756   0.00893  -0.0537   0.5107   1.0000
   5.000   0.8946   0.01772   0.00896  -0.0525   0.4908   1.0000
   5.250   0.9170   0.01794   0.00917  -0.0513   0.4696   1.0000
   5.500   0.9399   0.01818   0.00943  -0.0502   0.4505   1.0000
   5.750   0.9631   0.01842   0.00966  -0.0492   0.4328   1.0000
   6.000   0.9860   0.01863   0.00985  -0.0481   0.4154   1.0000
   6.250   1.0089   0.01888   0.01008  -0.0471   0.3990   1.0000
   6.500   1.0312   0.01914   0.01035  -0.0460   0.3823   1.0000
   6.750   1.0531   0.01944   0.01070  -0.0449   0.3650   1.0000
   7.000   1.0748   0.01979   0.01109  -0.0438   0.3488   1.0000
   7.250   1.0963   0.02017   0.01155  -0.0428   0.3332   1.0000
   7.500   1.1172   0.02058   0.01202  -0.0416   0.3170   1.0000
   7.750   1.1361   0.02096   0.01243  -0.0402   0.2957   1.0000
   8.000   1.1534   0.02140   0.01295  -0.0386   0.2685   1.0000
   8.250   1.1676   0.02206   0.01359  -0.0367   0.2276   1.0000
   8.500   1.1747   0.02359   0.01469  -0.0341   0.1368   1.0000
   8.750   1.1785   0.02567   0.01632  -0.0313   0.1039   1.0000
   9.000   1.1849   0.02742   0.01799  -0.0287   0.0942   1.0000
   9.250   1.1914   0.02903   0.01963  -0.0262   0.0880   1.0000
   9.500   1.1958   0.03077   0.02134  -0.0235   0.0835   1.0000
   9.750   1.2039   0.03218   0.02286  -0.0210   0.0803   1.0000
  10.000   1.2128   0.03371   0.02445  -0.0188   0.0776   1.0000
  10.250   1.2250   0.03546   0.02613  -0.0170   0.0745   1.0000
  10.500   1.2465   0.03753   0.02816  -0.0164   0.0713   1.0000
  10.750   1.2646   0.03920   0.03001  -0.0153   0.0689   1.0000
  11.000   1.2879   0.04127   0.03226  -0.0148   0.0669   1.0000
  11.250   1.3079   0.04343   0.03454  -0.0142   0.0647   1.0000
  11.500   1.3383   0.04661   0.03766  -0.0152   0.0617   1.0000
  11.750   1.3562   0.05013   0.04142  -0.0147   0.0607   1.0000
  12.000   1.3610   0.05289   0.04453  -0.0127   0.0603   1.0000
  12.250   1.3594   0.05565   0.04763  -0.0103   0.0600   1.0000
  12.500   1.3517   0.05842   0.05073  -0.0076   0.0596   1.0000
  12.750   1.3403   0.06140   0.05401  -0.0053   0.0593   1.0000
  13.000   1.3261   0.06474   0.05764  -0.0037   0.0591   1.0000
  13.250   1.3088   0.06848   0.06165  -0.0029   0.0589   1.0000
  13.500   1.2908   0.07286   0.06629  -0.0030   0.0590   1.0000
  13.750   1.2708   0.07772   0.07139  -0.0040   0.0591   1.0000
  14.000   1.2499   0.08322   0.07711  -0.0057   0.0595   1.0000
  14.250   1.2262   0.08939   0.08349  -0.0083   0.0597   1.0000
  14.500   1.2028   0.09624   0.09050  -0.0115   0.0602   1.0000
  14.750   1.1811   0.10361   0.09801  -0.0151   0.0607   1.0000
  15.000   1.1595   0.11159   0.10611  -0.0191   0.0611   1.0000
  15.250   1.0087   0.15279   0.14758  -0.0496   0.0734   1.0000
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