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GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 101 AIRFOIL (goe101-il)
Reynolds number: 200,000
Max Cl/Cd: 77.17 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe101-il-200000-n5.txt
Download as CSV file: xf-goe101-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 101 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3515   0.09491   0.09151  -0.0204   1.0000   0.0210
  -7.750  -0.3489   0.09221   0.08886  -0.0214   1.0000   0.0211
  -7.500  -0.3486   0.08961   0.08632  -0.0223   1.0000   0.0211
  -7.000  -0.3411   0.08356   0.08037  -0.0263   1.0000   0.0213
  -6.750  -0.3342   0.08029   0.07713  -0.0287   1.0000   0.0213
  -6.500  -0.3259   0.07692   0.07378  -0.0313   1.0000   0.0214
  -6.250  -0.3164   0.07346   0.07031  -0.0338   1.0000   0.0215
  -6.000  -0.3082   0.06991   0.06677  -0.0352   1.0000   0.0214
  -5.750  -0.2967   0.06508   0.06197  -0.0357   0.9938   0.0192
  -5.500  -0.2640   0.05910   0.05590  -0.0441   0.9843   0.0170
  -5.250  -0.2266   0.05255   0.04919  -0.0530   0.9746   0.0158
  -5.000  -0.1899   0.04689   0.04334  -0.0600   0.9645   0.0157
  -4.750  -0.1551   0.04271   0.03899  -0.0649   0.9540   0.0168
  -4.500  -0.1184   0.03831   0.03432  -0.0695   0.9423   0.0189
  -4.250  -0.0825   0.03333   0.02898  -0.0731   0.9297   0.0193
  -4.000  -0.0472   0.02838   0.02351  -0.0755   0.9160   0.0203
  -3.750  -0.0158   0.02545   0.02017  -0.0769   0.9006   0.0234
  -3.500   0.0141   0.02345   0.01788  -0.0778   0.8834   0.0251
  -3.250   0.0435   0.02128   0.01528  -0.0780   0.8637   0.0273
  -3.000   0.0731   0.01960   0.01308  -0.0777   0.8425   0.0307
  -2.750   0.1009   0.01808   0.01105  -0.0773   0.8199   0.0321
  -2.250   0.1530   0.01593   0.00840  -0.0765   0.7749   0.0370
  -1.750   0.2059   0.01443   0.00633  -0.0753   0.7329   0.0389
  -1.500   0.2320   0.01403   0.00571  -0.0747   0.7127   0.0408
  -1.250   0.2582   0.01364   0.00513  -0.0742   0.6937   0.0417
  -1.000   0.2843   0.01315   0.00451  -0.0737   0.6755   0.0415
  -0.750   0.3103   0.01275   0.00398  -0.0732   0.6584   0.0414
  -0.500   0.3363   0.01242   0.00356  -0.0727   0.6418   0.0413
  -0.250   0.3624   0.01217   0.00321  -0.0722   0.6256   0.0414
   0.000   0.3885   0.01198   0.00292  -0.0718   0.6100   0.0416
   0.250   0.4148   0.01185   0.00269  -0.0714   0.5955   0.0421
   0.500   0.4413   0.01178   0.00250  -0.0711   0.5823   0.0428
   0.750   0.4679   0.01171   0.00234  -0.0708   0.5706   0.0449
   1.000   0.4945   0.01169   0.00225  -0.0705   0.5598   0.0495
   1.500   0.5527   0.00961   0.00235  -0.0713   0.5395   1.0000
   1.750   0.5791   0.00977   0.00238  -0.0709   0.5305   1.0000
   2.000   0.6055   0.00994   0.00244  -0.0706   0.5213   1.0000
   2.250   0.6319   0.01010   0.00252  -0.0703   0.5109   1.0000
   2.500   0.6580   0.01028   0.00262  -0.0699   0.4998   1.0000
   2.750   0.6841   0.01047   0.00272  -0.0695   0.4889   1.0000
   3.000   0.7103   0.01063   0.00285  -0.0692   0.4778   1.0000
   3.250   0.7366   0.01081   0.00301  -0.0689   0.4684   1.0000
   3.500   0.7627   0.01101   0.00317  -0.0686   0.4597   1.0000
   3.750   0.7890   0.01117   0.00335  -0.0683   0.4500   1.0000
   4.000   0.8152   0.01136   0.00355  -0.0680   0.4425   1.0000
   4.250   0.8415   0.01154   0.00379  -0.0677   0.4346   1.0000
   4.500   0.8676   0.01173   0.00402  -0.0674   0.4258   1.0000
   5.000   0.9192   0.01213   0.00451  -0.0666   0.4037   1.0000
   5.250   0.9451   0.01233   0.00482  -0.0663   0.3930   1.0000
   5.500   0.9700   0.01257   0.00507  -0.0658   0.3722   1.0000
   5.750   0.9934   0.01289   0.00530  -0.0651   0.3250   1.0000
   6.000   1.0130   0.01371   0.00571  -0.0640   0.2437   1.0000
   6.250   1.0320   0.01475   0.00645  -0.0630   0.1840   1.0000
   6.500   1.0501   0.01593   0.00727  -0.0620   0.1136   1.0000
   6.750   1.0671   0.01724   0.00827  -0.0607   0.0569   1.0000
   7.000   1.0828   0.01873   0.00950  -0.0592   0.0210   1.0000
   7.250   1.1035   0.01955   0.01049  -0.0581   0.0181   1.0000
   7.500   1.1230   0.02049   0.01164  -0.0569   0.0159   1.0000
   7.750   1.1392   0.02177   0.01309  -0.0554   0.0133   1.0000
   8.000   1.1511   0.02342   0.01495  -0.0533   0.0121   1.0000
   8.250   1.1661   0.02463   0.01631  -0.0516   0.0116   1.0000
   8.500   1.1792   0.02601   0.01783  -0.0497   0.0112   1.0000
   8.750   1.1910   0.02750   0.01945  -0.0477   0.0107   1.0000
   9.000   1.2029   0.02894   0.02101  -0.0458   0.0100   1.0000
   9.250   1.2146   0.03033   0.02251  -0.0440   0.0093   1.0000
   9.500   1.2236   0.03171   0.02397  -0.0419   0.0085   1.0000
   9.750   1.2302   0.03348   0.02584  -0.0396   0.0082   1.0000
  10.000   1.2370   0.03552   0.02802  -0.0376   0.0080   1.0000
  10.250   1.2446   0.03809   0.03072  -0.0357   0.0077   1.0000
  10.500   1.2526   0.04113   0.03393  -0.0341   0.0075   1.0000
  10.750   1.2576   0.04346   0.03649  -0.0323   0.0075   1.0000
  11.000   1.2596   0.04594   0.03922  -0.0305   0.0074   1.0000
  11.250   1.2590   0.04874   0.04228  -0.0290   0.0073   1.0000
  11.500   1.2559   0.05183   0.04563  -0.0278   0.0072   1.0000
  11.750   1.2505   0.05525   0.04930  -0.0271   0.0072   1.0000
  12.000   1.2424   0.05906   0.05336  -0.0269   0.0072   1.0000
  12.250   1.2329   0.06323   0.05778  -0.0273   0.0072   1.0000
  12.500   1.2220   0.06781   0.06259  -0.0283   0.0071   1.0000
  12.750   1.2098   0.07283   0.06783  -0.0300   0.0072   1.0000
  13.000   1.1961   0.07834   0.07356  -0.0323   0.0071   1.0000
  13.250   1.1826   0.08415   0.07956  -0.0350   0.0072   1.0000
  13.500   1.1674   0.09057   0.08618  -0.0384   0.0071   1.0000
  13.750   1.1522   0.09732   0.09310  -0.0421   0.0072   1.0000
  14.000   1.1373   0.10444   0.10038  -0.0463   0.0072   1.0000
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