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GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il)
Reynolds number: 50,000
Max Cl/Cd: 19.94 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe300-il-50000.txt
Download as CSV file: xf-goe300-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2712   0.11781   0.11087  -0.0264   1.0000   0.1057
  -9.000  -0.2709   0.11644   0.10959  -0.0278   1.0000   0.1082
  -8.750  -0.2775   0.11649   0.10977  -0.0294   1.0000   0.1094
  -8.500  -0.2899   0.11706   0.11051  -0.0301   1.0000   0.1099
  -8.250  -0.2704   0.10981   0.10326  -0.0289   1.0000   0.1118
  -8.000  -0.2613   0.10582   0.09932  -0.0277   1.0000   0.1146
  -7.750  -0.2628   0.10376   0.09737  -0.0266   1.0000   0.1171
  -7.500  -0.2702   0.10242   0.09617  -0.0249   1.0000   0.1192
  -7.250  -0.2804   0.10150   0.09538  -0.0235   1.0000   0.1212
  -7.000  -0.2927   0.10117   0.09519  -0.0229   1.0000   0.1228
  -6.750  -0.3061   0.10155   0.09569  -0.0236   1.0000   0.1239
  -6.500  -0.3169   0.10248   0.09667  -0.0261   1.0000   0.1245
  -6.250  -0.3125   0.09581   0.09014  -0.0191   1.0000   0.1270
  -6.000  -0.3156   0.09354   0.08795  -0.0167   1.0000   0.1300
  -5.750  -0.3205   0.09199   0.08647  -0.0158   1.0000   0.1333
  -5.500  -0.3239   0.09124   0.08576  -0.0175   1.0000   0.1371
  -5.250  -0.3218   0.09079   0.08530  -0.0221   1.0000   0.1393
  -5.000  -0.3244   0.08676   0.08137  -0.0177   1.0000   0.1415
  -4.750  -0.3233   0.08437   0.07903  -0.0164   1.0000   0.1452
  -4.500  -0.3151   0.08290   0.07752  -0.0193   1.0000   0.1514
  -4.250  -0.3050   0.08061   0.07520  -0.0221   1.0000   0.1549
  -4.000  -0.3016   0.07768   0.07232  -0.0204   1.0000   0.1594
  -3.750  -0.2816   0.07618   0.07068  -0.0258   1.0000   0.1692
  -3.500  -0.2437   0.07246   0.06686  -0.0323   0.9920   0.1843
  -3.250  -0.2045   0.06847   0.06277  -0.0383   0.9830   0.2007
  -3.000  -0.1573   0.06631   0.06035  -0.0468   0.9719   0.2291
  -2.750  -0.1350   0.06189   0.05604  -0.0477   0.9629   0.2500
  -2.500  -0.0986   0.05871   0.05278  -0.0523   0.9532   0.2955
  -2.000  -0.0557   0.05277   0.04696  -0.0525   0.9321   0.4375
  -1.750  -0.0326   0.04915   0.04348  -0.0503   0.9227   0.5075
  -1.500  -0.0066   0.04661   0.04096  -0.0502   0.9104   0.5572
  -1.250   0.0239   0.04429   0.03864  -0.0509   0.8981   0.5980
  -1.000   0.0763   0.04208   0.03628  -0.0573   0.8859   0.6241
  -0.750   0.1791   0.04061   0.03412  -0.0770   0.8723   0.5652
  -0.500   0.2956   0.04210   0.03401  -0.0971   0.8578   0.3708
  -0.250   0.3388   0.04197   0.03338  -0.0999   0.8442   0.3204
   0.000   0.3779   0.04176   0.03276  -0.1017   0.8313   0.2842
   0.250   0.4188   0.04136   0.03202  -0.1036   0.8193   0.2697
   0.500   0.4762   0.04040   0.03065  -0.1074   0.8098   0.2550
   0.750   0.5041   0.04042   0.03044  -0.1074   0.7962   0.2479
   1.000   0.5332   0.04034   0.03020  -0.1075   0.7830   0.2495
   1.250   0.5683   0.04017   0.02980  -0.1080   0.7710   0.2504
   1.500   0.6159   0.03935   0.02874  -0.1095   0.7619   0.2505
   1.750   0.6389   0.03975   0.02906  -0.1088   0.7482   0.2546
   2.000   0.6627   0.04014   0.02938  -0.1080   0.7351   0.2625
   2.250   0.6920   0.04013   0.02937  -0.1077   0.7238   0.2707
   2.500   0.7274   0.03972   0.02895  -0.1077   0.7143   0.2810
   2.750   0.7421   0.04088   0.03017  -0.1066   0.7013   0.2941
   3.000   0.7628   0.04163   0.03104  -0.1061   0.6901   0.3188
   3.250   0.7968   0.03997   0.03079  -0.1057   0.6821   1.0000
   3.500   0.8051   0.04218   0.03283  -0.1042   0.6694   1.0000
   3.750   0.8284   0.04342   0.03381  -0.1035   0.6608   1.0000
   4.000   0.8430   0.04528   0.03550  -0.1026   0.6511   1.0000
   4.250   0.8436   0.04830   0.03844  -0.1015   0.6405   1.0000
   4.500   0.8771   0.04864   0.03861  -0.1012   0.6335   1.0000
   4.750   0.8565   0.05337   0.04336  -0.0995   0.6231   1.0000
   5.000   0.9214   0.05090   0.04076  -0.0996   0.6156   1.0000
   5.250   0.9024   0.05530   0.04518  -0.0978   0.6025   1.0000
   5.500   0.9071   0.05753   0.04738  -0.0962   0.5896   1.0000
   5.750   0.9303   0.05805   0.04788  -0.0947   0.5764   1.0000
   6.000   1.0116   0.05299   0.04282  -0.0937   0.5675   1.0000
   6.250   0.9817   0.05889   0.04876  -0.0922   0.5541   1.0000
   6.500   0.9699   0.06308   0.05299  -0.0910   0.5422   1.0000
   6.750   1.0042   0.06267   0.05262  -0.0897   0.5316   1.0000
   7.000   1.0386   0.06196   0.05198  -0.0881   0.5203   1.0000
   7.250   1.0247   0.06645   0.05651  -0.0870   0.5060   1.0000
   7.500   1.0227   0.06968   0.05982  -0.0857   0.4920   1.0000
   7.750   1.0314   0.07172   0.06192  -0.0843   0.4776   1.0000
   8.000   1.0441   0.07327   0.06354  -0.0827   0.4628   1.0000
   8.250   1.0561   0.07496   0.06530  -0.0812   0.4482   1.0000
   8.500   1.1473   0.06656   0.05709  -0.0769   0.4400   1.0000
   8.750   1.1305   0.07184   0.06242  -0.0762   0.4246   1.0000
   9.000   1.1000   0.07943   0.07001  -0.0767   0.4096   1.0000
   9.250   1.0546   0.08924   0.07980  -0.0784   0.3969   1.0000
   9.500   1.0475   0.09428   0.08488  -0.0786   0.3883   1.0000
   9.750   1.0385   0.09959   0.09023  -0.0792   0.3804   1.0000
  10.000   1.0309   0.10481   0.09548  -0.0797   0.3734   1.0000
  10.250   1.0064   0.11231   0.10300  -0.0817   0.3691   1.0000
  10.500   0.9940   0.11863   0.10936  -0.0834   0.3677   1.0000
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