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GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il)
Reynolds number: 50,000
Max Cl/Cd: 20.9 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe321-il-50000.txt
Download as CSV file: xf-goe321-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3513   0.14110   0.13417  -0.0090   1.0000   0.1208
 -11.000  -0.3577   0.14109   0.13424  -0.0122   1.0000   0.1227
 -10.750  -0.3692   0.14189   0.13514  -0.0162   1.0000   0.1234
 -10.500  -0.3292   0.13079   0.12400  -0.0124   1.0000   0.1292
 -10.250  -0.3224   0.12790   0.12116  -0.0136   1.0000   0.1342
 -10.000  -0.3264   0.12698   0.12033  -0.0165   1.0000   0.1382
  -9.750  -0.3403   0.12777   0.12125  -0.0209   1.0000   0.1394
  -9.500  -0.3060   0.11878   0.11223  -0.0179   1.0000   0.1444
  -9.250  -0.2976   0.11569   0.10919  -0.0187   1.0000   0.1497
  -9.000  -0.3017   0.11446   0.10807  -0.0215   1.0000   0.1544
  -8.750  -0.3195   0.11516   0.10895  -0.0260   1.0000   0.1560
  -8.500  -0.2821   0.10690   0.10065  -0.0227   1.0000   0.1624
  -8.250  -0.2801   0.10472   0.09858  -0.0241   1.0000   0.1692
  -8.000  -0.3004   0.10514   0.09923  -0.0271   1.0000   0.1722
  -7.750  -0.2738   0.09921   0.09332  -0.0252   1.0000   0.1795
  -7.500  -0.2853   0.09834   0.09263  -0.0237   1.0000   0.1845
  -7.250  -0.3166   0.09927   0.09377  -0.0185   1.0000   0.1845
  -7.000  -0.3458   0.09990   0.09455  -0.0143   1.0000   0.1851
  -6.750  -0.3717   0.10016   0.09493  -0.0120   1.0000   0.1868
  -6.500  -0.3980   0.10057   0.09544  -0.0123   1.0000   0.1886
  -6.250  -0.4095   0.09869   0.09365  -0.0116   1.0000   0.1910
  -6.000  -0.3887   0.09481   0.08977  -0.0113   0.9951   0.2023
  -5.750  -0.3641   0.09058   0.08552  -0.0165   0.9858   0.2139
  -5.500  -0.3431   0.08695   0.08186  -0.0224   0.9762   0.2281
  -5.250  -0.3202   0.08344   0.07831  -0.0269   0.9676   0.2450
  -5.000  -0.2990   0.08020   0.07504  -0.0298   0.9588   0.2638
  -4.750  -0.2822   0.07757   0.07238  -0.0323   0.9497   0.2871
  -4.500  -0.2612   0.07437   0.06920  -0.0335   0.9425   0.3157
  -4.250  -0.2540   0.07223   0.06708  -0.0325   0.9346   0.3472
  -4.000   0.0554   0.05639   0.05112  -0.0254   0.9629   0.9403
  -3.750  -0.0136   0.05904   0.05389  -0.0160   0.9449   0.8422
  -3.500  -0.0786   0.06086   0.05584  -0.0098   0.9293   0.7606
  -3.250  -0.1257   0.06154   0.05663  -0.0033   0.9175   0.7365
  -3.000   0.1547   0.04809   0.04275  -0.0445   0.9261   0.9385
  -2.750   0.1053   0.04953   0.04430  -0.0350   0.9125   0.8957
  -2.500   0.0513   0.05095   0.04584  -0.0249   0.9010   0.8663
  -2.000  -0.0690   0.05285   0.04801  -0.0027   0.8835   0.8239
  -1.750  -0.1271   0.05285   0.04814   0.0053   0.8773   0.7921
  -1.500  -0.1634   0.05213   0.04747   0.0065   0.8714   0.7567
  -1.250   0.1400   0.04743   0.03891  -0.0848   0.8565   0.2191
  -1.000   0.1700   0.04670   0.03777  -0.0858   0.8492   0.2002
  -0.750   0.2189   0.04594   0.03641  -0.0889   0.8420   0.1882
  -0.500   0.2358   0.04570   0.03605  -0.0880   0.8337   0.1851
  -0.250   0.2871   0.04477   0.03472  -0.0912   0.8257   0.1779
   0.000   0.2995   0.04520   0.03492  -0.0895   0.8169   0.1752
   0.250   0.3463   0.04464   0.03413  -0.0919   0.8086   0.1761
   0.500   0.3579   0.04519   0.03463  -0.0902   0.7992   0.1797
   0.750   0.3988   0.04513   0.03436  -0.0916   0.7905   0.1861
   1.000   0.4184   0.04571   0.03481  -0.0907   0.7804   0.1898
   1.250   0.4454   0.04594   0.03511  -0.0907   0.7709   0.2003
   1.500   0.4814   0.04594   0.03513  -0.0916   0.7607   0.2219
   1.750   0.4949   0.04678   0.03609  -0.0904   0.7494   0.2429
   2.000   0.5321   0.04493   0.03610  -0.0904   0.7397   1.0000
   2.250   0.5581   0.04597   0.03658  -0.0897   0.7276   1.0000
   2.500   0.5688   0.04750   0.03790  -0.0880   0.7145   1.0000
   2.750   0.5888   0.04875   0.03895  -0.0872   0.7010   1.0000
   3.000   0.6146   0.04971   0.03975  -0.0868   0.6869   1.0000
   3.250   0.6423   0.05034   0.04024  -0.0860   0.6707   1.0000
   3.500   0.6703   0.05073   0.04051  -0.0850   0.6533   1.0000
   3.750   0.7002   0.05085   0.04054  -0.0839   0.6359   1.0000
   4.000   0.7309   0.05083   0.04044  -0.0828   0.6195   1.0000
   4.250   0.7598   0.05084   0.04039  -0.0814   0.6044   1.0000
   4.500   0.8109   0.04896   0.03844  -0.0804   0.5946   1.0000
   4.750   0.8312   0.04951   0.03896  -0.0788   0.5793   1.0000
   5.000   0.8515   0.05005   0.03949  -0.0772   0.5640   1.0000
   5.250   0.8713   0.05064   0.04010  -0.0756   0.5487   1.0000
   5.500   0.8910   0.05122   0.04068  -0.0739   0.5334   1.0000
   5.750   0.9116   0.05165   0.04112  -0.0722   0.5182   1.0000
   6.000   0.9331   0.05194   0.04141  -0.0704   0.5033   1.0000
   6.250   0.9776   0.04978   0.03923  -0.0687   0.4934   1.0000
   6.500   1.0138   0.04853   0.03797  -0.0672   0.4815   1.0000
   6.750   1.0238   0.05021   0.03971  -0.0657   0.4663   1.0000
   7.250   1.0083   0.05785   0.04744  -0.0630   0.4371   1.0000
   7.500   1.0889   0.05209   0.04164  -0.0619   0.4330   1.0000
   7.750   1.0360   0.06096   0.05060  -0.0607   0.4185   1.0000
   8.000   0.9500   0.07647   0.06612  -0.0643   0.4043   1.0000
   8.250   0.9254   0.08392   0.07356  -0.0657   0.3982   1.0000
   8.500   0.8901   0.09295   0.08260  -0.0681   0.3957   1.0000
   8.750   0.8731   0.09974   0.08942  -0.0699   0.3962   1.0000
   9.000   0.8663   0.10547   0.09518  -0.0714   0.3984   1.0000
   9.250   0.8699   0.11014   0.09989  -0.0725   0.4004   1.0000
   9.500   0.7525   0.12966   0.11960  -0.0842   0.5032   1.0000
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