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GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il)
Reynolds number: 100,000
Max Cl/Cd: 53.33 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe319-il-100000.txt
Download as CSV file: xf-goe319-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 319 (HANSA-BRANDENBURG II) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2401   0.10016   0.09566  -0.0278   1.0000   0.0715
  -7.750  -0.2643   0.10062   0.09627  -0.0229   1.0000   0.0717
  -7.500  -0.2930   0.10149   0.09728  -0.0176   1.0000   0.0717
  -7.250  -0.2879   0.09955   0.09537  -0.0226   0.9932   0.0734
  -7.000  -0.2519   0.09639   0.09209  -0.0459   0.9760   0.0751
  -6.750  -0.2313   0.09028   0.08605  -0.0414   0.9736   0.0763
  -6.500  -0.2023   0.08588   0.08163  -0.0442   0.9685   0.0784
  -6.250  -0.1742   0.08213   0.07786  -0.0500   0.9592   0.0817
  -6.000  -0.1279   0.07984   0.07525  -0.0712   0.9443   0.0870
  -5.750  -0.1045   0.07380   0.06936  -0.0697   0.9415   0.0885
  -5.500  -0.0800   0.07031   0.06587  -0.0714   0.9334   0.0909
  -5.250  -0.0464   0.06687   0.06236  -0.0770   0.9255   0.0954
  -5.000  -0.0088   0.06447   0.05964  -0.0875   0.9128   0.1008
  -4.750   0.0158   0.06016   0.05543  -0.0879   0.9072   0.1031
  -4.500   0.0355   0.05779   0.05303  -0.0886   0.8962   0.1067
  -4.250   0.0784   0.05554   0.05041  -0.0963   0.8885   0.1157
  -4.000   0.0903   0.05264   0.04763  -0.0945   0.8768   0.1182
  -3.750   0.1275   0.05186   0.04643  -0.0988   0.8683   0.1310
  -3.500   0.1405   0.04832   0.04308  -0.0974   0.8580   0.1337
  -3.250   0.1649   0.04636   0.04105  -0.0978   0.8500   0.1418
  -3.000   0.1885   0.04438   0.03893  -0.0986   0.8397   0.1509
  -2.750   0.2156   0.04321   0.03751  -0.0996   0.8309   0.1654
  -2.500   0.2353   0.04087   0.03525  -0.0988   0.8220   0.1725
  -2.250   0.2592   0.03925   0.03351  -0.0989   0.8135   0.1874
  -2.000   0.2828   0.03768   0.03185  -0.0987   0.8046   0.2050
  -1.750   0.3066   0.03637   0.03040  -0.0986   0.7962   0.2328
  -0.250   0.4928   0.02726   0.01920  -0.0955   0.7344   0.1329
   0.000   0.5232   0.02626   0.01776  -0.0944   0.7258   0.1133
   0.250   0.5506   0.02512   0.01649  -0.0937   0.7166   0.1104
   0.500   0.5778   0.02441   0.01560  -0.0929   0.7075   0.1099
   0.750   0.6058   0.02362   0.01465  -0.0920   0.6982   0.1085
   1.000   0.6323   0.02305   0.01397  -0.0911   0.6882   0.1077
   1.250   0.6605   0.02238   0.01318  -0.0901   0.6792   0.1086
   1.500   0.6857   0.02202   0.01280  -0.0891   0.6680   0.1113
   1.750   0.7138   0.02133   0.01207  -0.0882   0.6598   0.1184
   2.000   0.7378   0.02111   0.01189  -0.0871   0.6476   0.1274
   2.250   0.7648   0.02071   0.01145  -0.0862   0.6371   0.1427
   2.500   0.8060   0.01835   0.01068  -0.0877   0.6258   1.0000
   2.750   0.8305   0.01844   0.01056  -0.0866   0.6121   1.0000
   3.000   0.8557   0.01847   0.01042  -0.0855   0.5985   1.0000
   3.250   0.8815   0.01847   0.01025  -0.0846   0.5848   1.0000
   3.500   0.9074   0.01847   0.01008  -0.0836   0.5702   1.0000
   3.750   0.9326   0.01852   0.00997  -0.0826   0.5541   1.0000
   4.000   0.9569   0.01864   0.00996  -0.0815   0.5357   1.0000
   4.250   0.9805   0.01882   0.01000  -0.0803   0.5157   1.0000
   4.500   1.0041   0.01906   0.01009  -0.0792   0.4952   1.0000
   4.750   1.0278   0.01936   0.01022  -0.0782   0.4754   1.0000
   5.000   1.0513   0.01973   0.01042  -0.0772   0.4569   1.0000
   5.250   1.0746   0.02015   0.01071  -0.0763   0.4399   1.0000
   5.500   1.0977   0.02062   0.01106  -0.0754   0.4243   1.0000
   5.750   1.1208   0.02113   0.01149  -0.0746   0.4105   1.0000
   6.000   1.1443   0.02168   0.01194  -0.0738   0.3986   1.0000
   6.500   1.1913   0.02281   0.01292  -0.0724   0.3773   1.0000
   6.750   1.2150   0.02344   0.01348  -0.0718   0.3682   1.0000
   7.000   1.2385   0.02406   0.01406  -0.0712   0.3593   1.0000
   7.250   1.2617   0.02480   0.01479  -0.0706   0.3515   1.0000
   7.500   1.2851   0.02549   0.01547  -0.0700   0.3437   1.0000
   7.750   1.3092   0.02630   0.01624  -0.0696   0.3370   1.0000
   8.000   1.3303   0.02709   0.01713  -0.0688   0.3297   1.0000
   8.500   1.3749   0.02882   0.01892  -0.0676   0.3166   1.0000
   8.750   1.3984   0.02965   0.01976  -0.0671   0.3105   1.0000
   9.000   1.4222   0.03068   0.02078  -0.0668   0.3049   1.0000
   9.250   1.4387   0.03172   0.02204  -0.0655   0.2986   1.0000
   9.500   1.4639   0.03257   0.02283  -0.0653   0.2926   1.0000
   9.750   1.4813   0.03381   0.02423  -0.0642   0.2868   1.0000
  10.000   1.4976   0.03495   0.02554  -0.0629   0.2808   1.0000
  10.250   1.5242   0.03595   0.02644  -0.0630   0.2756   1.0000
  10.500   1.5360   0.03748   0.02826  -0.0613   0.2703   1.0000
  10.750   1.5493   0.03876   0.02972  -0.0598   0.2645   1.0000
  11.000   1.5767   0.03973   0.03058  -0.0600   0.2592   1.0000
  11.250   1.5821   0.04155   0.03271  -0.0577   0.2543   1.0000
  11.500   1.5906   0.04301   0.03440  -0.0557   0.2488   1.0000
  11.750   1.6186   0.04376   0.03503  -0.0559   0.2432   1.0000
  12.000   1.6185   0.04580   0.03736  -0.0532   0.2387   1.0000
  12.250   1.6180   0.04763   0.03946  -0.0505   0.2339   1.0000
  12.500   1.6363   0.04864   0.04048  -0.0497   0.2290   1.0000
  12.750   1.6525   0.05028   0.04218  -0.0489   0.2247   1.0000
  13.000   1.6267   0.05313   0.04541  -0.0440   0.2218   1.0000
  13.250   1.6049   0.05603   0.04857  -0.0400   0.2188   1.0000
  13.500   1.6087   0.05775   0.05039  -0.0383   0.2148   1.0000
  13.750   1.3936   0.08067   0.07403  -0.0368   0.2183   1.0000
  14.000   1.3997   0.08285   0.07627  -0.0365   0.2143   1.0000
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