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GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.64 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe316-il-1000000-n5.txt
Download as CSV file: xf-goe316-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4532   0.09155   0.08929  -0.0018   0.7528   0.0085
  -8.500  -0.4503   0.08758   0.08529  -0.0045   0.7439   0.0089
  -8.250  -0.4605   0.07875   0.07646  -0.0132   0.7374   0.0100
  -8.000  -0.4468   0.07542   0.07309  -0.0173   0.7290   0.0101
  -7.750  -0.4313   0.07214   0.06976  -0.0213   0.7200   0.0103
  -7.500  -0.4148   0.06855   0.06611  -0.0256   0.7120   0.0106
  -7.250  -0.3972   0.06447   0.06197  -0.0302   0.7043   0.0109
  -7.000  -0.3827   0.05257   0.04984  -0.0415   0.7002   0.0128
  -6.750  -0.3600   0.05035   0.04755  -0.0433   0.6925   0.0130
  -6.500  -0.3369   0.04819   0.04529  -0.0450   0.6842   0.0132
  -6.250  -0.3134   0.04563   0.04262  -0.0468   0.6743   0.0136
  -6.000  -0.2911   0.03492   0.03141  -0.0517   0.6688   0.0161
  -5.750  -0.2657   0.03375   0.03012  -0.0521   0.6564   0.0163
  -5.500  -0.2401   0.03254   0.02881  -0.0526   0.6439   0.0166
  -5.250  -0.2143   0.03092   0.02703  -0.0531   0.6300   0.0170
  -5.000  -0.1882   0.02878   0.02468  -0.0536   0.6135   0.0176
  -4.750  -0.1634   0.02000   0.01508  -0.0541   0.6019   0.0203
  -4.500  -0.1362   0.01931   0.01421  -0.0543   0.5805   0.0206
  -4.250  -0.1088   0.01881   0.01357  -0.0544   0.5627   0.0208
  -4.000  -0.0812   0.01820   0.01281  -0.0545   0.5462   0.0212
  -3.750  -0.0537   0.01675   0.01111  -0.0546   0.5317   0.0217
  -3.500  -0.0260   0.01486   0.00889  -0.0546   0.5181   0.0224
  -3.250   0.0018   0.01337   0.00710  -0.0546   0.5040   0.0233
  -3.000   0.0299   0.01264   0.00618  -0.0546   0.4890   0.0239
  -2.750   0.0581   0.01215   0.00553  -0.0547   0.4724   0.0243
  -2.500   0.0864   0.01181   0.00505  -0.0547   0.4540   0.0245
  -2.250   0.1146   0.01155   0.00465  -0.0548   0.4320   0.0246
  -2.000   0.1426   0.01112   0.00404  -0.0549   0.4042   0.0249
  -1.750   0.1704   0.01071   0.00347  -0.0550   0.3776   0.0253
  -1.500   0.1986   0.01049   0.00315  -0.0550   0.3598   0.0257
  -1.250   0.2269   0.01034   0.00292  -0.0551   0.3475   0.0260
  -1.000   0.2553   0.01020   0.00273  -0.0552   0.3392   0.0263
  -0.750   0.2838   0.01011   0.00260  -0.0553   0.3322   0.0267
  -0.500   0.3124   0.01003   0.00250  -0.0554   0.3275   0.0273
  -0.250   0.3409   0.00993   0.00237  -0.0555   0.3229   0.0279
   0.250   0.3980   0.00976   0.00214  -0.0557   0.3155   0.0290
   0.500   0.4267   0.00969   0.00206  -0.0558   0.3129   0.0296
   0.750   0.4553   0.00965   0.00200  -0.0560   0.3100   0.0301
   1.000   0.4839   0.00962   0.00195  -0.0561   0.3071   0.0305
   1.250   0.5124   0.00962   0.00193  -0.0562   0.3041   0.0308
   1.500   0.5410   0.00959   0.00188  -0.0563   0.3012   0.0315
   1.750   0.5696   0.00954   0.00185  -0.0565   0.3000   0.0328
   2.000   0.5982   0.00954   0.00187  -0.0566   0.2985   0.0345
   2.250   0.6267   0.00955   0.00190  -0.0567   0.2969   0.0365
   2.500   0.6553   0.00957   0.00193  -0.0568   0.2952   0.0383
   2.750   0.6837   0.00959   0.00197  -0.0570   0.2935   0.0423
   3.000   0.7121   0.00963   0.00203  -0.0571   0.2918   0.0476
   3.250   0.7405   0.00968   0.00210  -0.0572   0.2897   0.0578
   3.500   0.7638   0.00783   0.00235  -0.0569   0.2859   1.0000
   3.750   0.7922   0.00791   0.00241  -0.0570   0.2834   1.0000
   4.000   0.8206   0.00800   0.00248  -0.0571   0.2802   1.0000
   4.250   0.8487   0.00811   0.00257  -0.0572   0.2762   1.0000
   4.500   0.8768   0.00825   0.00267  -0.0573   0.2722   1.0000
   4.750   0.9049   0.00836   0.00279  -0.0574   0.2699   1.0000
   5.000   0.9330   0.00846   0.00289  -0.0576   0.2682   1.0000
   5.250   0.9611   0.00857   0.00301  -0.0577   0.2657   1.0000
   5.500   0.9891   0.00868   0.00313  -0.0578   0.2621   1.0000
   5.750   1.0168   0.00884   0.00326  -0.0579   0.2573   1.0000
   6.000   1.0446   0.00896   0.00340  -0.0580   0.2539   1.0000
   6.250   1.0724   0.00910   0.00354  -0.0581   0.2476   1.0000
   6.500   1.0998   0.00927   0.00369  -0.0581   0.2397   1.0000
   6.750   1.1263   0.00959   0.00389  -0.0581   0.2151   1.0000
   7.000   1.1483   0.01060   0.00452  -0.0578   0.1516   1.0000
   7.250   1.1727   0.01122   0.00500  -0.0575   0.1251   1.0000
   7.500   1.1967   0.01185   0.00549  -0.0573   0.0986   1.0000
   8.000   1.2439   0.01317   0.00656  -0.0566   0.0535   1.0000
   8.250   1.2689   0.01357   0.00696  -0.0564   0.0488   1.0000
   8.500   1.2942   0.01390   0.00731  -0.0563   0.0457   1.0000
   8.750   1.3191   0.01427   0.00770  -0.0561   0.0417   1.0000
   9.000   1.3429   0.01476   0.00817  -0.0558   0.0356   1.0000
   9.250   1.3648   0.01546   0.00876  -0.0553   0.0223   1.0000
   9.500   1.3864   0.01615   0.00942  -0.0547   0.0150   1.0000
   9.750   1.4091   0.01668   0.00998  -0.0542   0.0127   1.0000
  10.000   1.4309   0.01726   0.01058  -0.0537   0.0111   1.0000
  10.250   1.4527   0.01781   0.01117  -0.0531   0.0101   1.0000
  10.500   1.4742   0.01834   0.01175  -0.0525   0.0094   1.0000
  10.750   1.4946   0.01895   0.01241  -0.0518   0.0087   1.0000
  11.000   1.5138   0.01964   0.01314  -0.0509   0.0080   1.0000
  11.250   1.5319   0.02037   0.01392  -0.0500   0.0075   1.0000
  11.500   1.5500   0.02102   0.01463  -0.0490   0.0072   1.0000
  11.750   1.5668   0.02174   0.01541  -0.0479   0.0068   1.0000
  12.000   1.5814   0.02253   0.01626  -0.0465   0.0064   1.0000
  12.250   1.5914   0.02341   0.01719  -0.0445   0.0061   1.0000
  12.500   1.5985   0.02449   0.01834  -0.0423   0.0058   1.0000
  12.750   1.6038   0.02586   0.01979  -0.0405   0.0056   1.0000
  13.000   1.6095   0.02739   0.02140  -0.0391   0.0054   1.0000
  13.250   1.6159   0.02904   0.02315  -0.0382   0.0053   1.0000
  13.500   1.6213   0.03098   0.02518  -0.0377   0.0052   1.0000
  13.750   1.6252   0.03321   0.02750  -0.0375   0.0050   1.0000
  14.000   1.6278   0.03571   0.03010  -0.0374   0.0049   1.0000
  14.250   1.6286   0.03850   0.03300  -0.0375   0.0048   1.0000
  14.500   1.6274   0.04159   0.03618  -0.0378   0.0047   1.0000
  14.750   1.6245   0.04498   0.03968  -0.0382   0.0046   1.0000
  15.000   1.6191   0.04876   0.04357  -0.0389   0.0045   1.0000
  15.250   1.6119   0.05290   0.04782  -0.0397   0.0044   1.0000
  15.500   1.6027   0.05739   0.05242  -0.0407   0.0044   1.0000
  15.750   1.5915   0.06221   0.05736  -0.0418   0.0043   1.0000
  16.000   1.5792   0.06727   0.06252  -0.0431   0.0043   1.0000
  16.250   1.5661   0.07258   0.06794  -0.0445   0.0042   1.0000
  16.500   1.5526   0.07809   0.07357  -0.0462   0.0042   1.0000
  16.750   1.5389   0.08371   0.07929  -0.0479   0.0041   1.0000
  17.000   1.5253   0.08939   0.08507  -0.0496   0.0041   1.0000
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