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GOE 410 AIRFOIL (goe410-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 410 AIRFOIL (goe410-il)
Reynolds number: 100,000
Max Cl/Cd: 37.12 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe410-il-100000.txt
Download as CSV file: xf-goe410-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 410 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.9056   0.07927   0.07302  -0.0251   1.0000   0.1433
 -13.000  -0.9907   0.06625   0.05974  -0.0318   1.0000   0.1417
 -12.750  -1.0454   0.05942   0.05265  -0.0331   1.0000   0.1412
 -12.500  -1.0855   0.05524   0.04820  -0.0312   1.0000   0.1418
 -12.250  -1.1160   0.05219   0.04484  -0.0278   1.0000   0.1429
 -12.000  -1.1377   0.04948   0.04172  -0.0246   1.0000   0.1444
 -11.750  -1.1040   0.04757   0.04006  -0.0255   1.0000   0.1489
 -11.500  -1.0927   0.04594   0.03837  -0.0244   1.0000   0.1527
 -11.250  -1.0938   0.04384   0.03598  -0.0223   1.0000   0.1558
 -11.000  -1.0971   0.04197   0.03365  -0.0197   1.0000   0.1586
 -10.750  -1.0749   0.03980   0.03160  -0.0197   1.0000   0.1627
 -10.500  -1.0561   0.03849   0.03027  -0.0189   1.0000   0.1670
 -10.250  -1.0437   0.03698   0.02854  -0.0176   1.0000   0.1710
 -10.000  -1.0349   0.03559   0.02675  -0.0157   1.0000   0.1743
  -9.750  -1.0095   0.03366   0.02498  -0.0157   1.0000   0.1782
  -9.500  -0.9885   0.03241   0.02370  -0.0151   1.0000   0.1822
  -9.250  -0.9698   0.03114   0.02227  -0.0141   1.0000   0.1863
  -9.000  -0.9526   0.02996   0.02080  -0.0128   1.0000   0.1898
  -8.750  -0.9265   0.02846   0.01946  -0.0127   1.0000   0.1939
  -8.500  -0.9031   0.02743   0.01848  -0.0122   1.0000   0.1987
  -8.250  -0.8821   0.02643   0.01734  -0.0113   1.0000   0.2037
  -8.000  -0.8588   0.02529   0.01623  -0.0107   1.0000   0.2085
  -7.750  -0.8351   0.02439   0.01546  -0.0101   1.0000   0.2144
  -7.500  -0.8142   0.02357   0.01453  -0.0090   1.0000   0.2214
  -7.250  -0.7916   0.02267   0.01386  -0.0082   1.0000   0.2286
  -7.000  -0.7712   0.02194   0.01310  -0.0071   1.0000   0.2374
  -6.750  -0.7511   0.02117   0.01255  -0.0059   1.0000   0.2465
  -6.500  -0.7330   0.02049   0.01198  -0.0044   1.0000   0.2581
  -6.250  -0.7170   0.01989   0.01149  -0.0026   1.0000   0.2723
  -6.000  -0.7040   0.01935   0.01112  -0.0004   1.0000   0.2888
  -5.750  -0.6956   0.01890   0.01090   0.0024   1.0000   0.3077
  -5.500  -0.6908   0.01861   0.01085   0.0056   1.0000   0.3296
  -5.250  -0.6689   0.01851   0.01098   0.0055   0.9939   0.3655
  -5.000  -0.6143   0.01878   0.01133   0.0002   0.9759   0.4131
  -4.750  -0.5595   0.01921   0.01188  -0.0045   0.9592   0.4433
  -4.500  -0.5070   0.01944   0.01203  -0.0088   0.9424   0.4686
  -4.250  -0.4598   0.01962   0.01223  -0.0118   0.9237   0.4877
  -4.000  -0.4180   0.01979   0.01249  -0.0134   0.9037   0.5030
  -3.750  -0.3831   0.01987   0.01258  -0.0138   0.8828   0.5162
  -3.500  -0.3549   0.01985   0.01244  -0.0132   0.8622   0.5294
  -3.250  -0.3277   0.01995   0.01254  -0.0121   0.8425   0.5400
  -3.000  -0.3034   0.01993   0.01243  -0.0109   0.8238   0.5509
  -2.750  -0.2788   0.02002   0.01249  -0.0096   0.8063   0.5623
  -2.500  -0.2541   0.02005   0.01251  -0.0084   0.7900   0.5725
  -2.250  -0.2297   0.02005   0.01243  -0.0074   0.7752   0.5835
  -2.000  -0.2042   0.02006   0.01243  -0.0062   0.7626   0.5928
  -1.750  -0.1797   0.02004   0.01234  -0.0054   0.7488   0.6043
  -1.500  -0.1538   0.02005   0.01239  -0.0045   0.7364   0.6127
  -1.250  -0.1288   0.02001   0.01224  -0.0036   0.7260   0.6240
  -1.000  -0.1030   0.02008   0.01240  -0.0028   0.7135   0.6336
  -0.750  -0.0779   0.02004   0.01223  -0.0019   0.7045   0.6459
  -0.500  -0.0517   0.02011   0.01243  -0.0012   0.6930   0.6543
  -0.250  -0.0261   0.02004   0.01222  -0.0006   0.6847   0.6656
   0.000   0.0000   0.02010   0.01240   0.0000   0.6734   0.6734
   0.250   0.0261   0.02004   0.01221   0.0006   0.6655   0.6847
   0.500   0.0517   0.02011   0.01243   0.0012   0.6543   0.6929
   0.750   0.0779   0.02004   0.01223   0.0019   0.6459   0.7045
   1.000   0.1030   0.02008   0.01239   0.0028   0.6335   0.7136
   1.250   0.1287   0.02001   0.01224   0.0036   0.6240   0.7260
   1.500   0.1538   0.02005   0.01239   0.0045   0.6127   0.7364
   1.750   0.1798   0.02004   0.01234   0.0054   0.6043   0.7488
   2.000   0.2043   0.02006   0.01242   0.0062   0.5928   0.7626
   2.250   0.2297   0.02005   0.01243   0.0074   0.5835   0.7752
   2.500   0.2541   0.02006   0.01252   0.0084   0.5726   0.7900
   2.750   0.2788   0.02002   0.01249   0.0096   0.5623   0.8062
   3.000   0.3034   0.01992   0.01243   0.0109   0.5509   0.8238
   3.250   0.3277   0.01995   0.01254   0.0121   0.5400   0.8425
   3.500   0.3549   0.01985   0.01243   0.0132   0.5294   0.8622
   3.750   0.3831   0.01987   0.01258   0.0138   0.5162   0.8828
   4.000   0.4180   0.01979   0.01249   0.0134   0.5031   0.9037
   4.250   0.4598   0.01962   0.01223   0.0118   0.4877   0.9237
   4.500   0.5070   0.01944   0.01203   0.0088   0.4687   0.9424
   4.750   0.5596   0.01921   0.01188   0.0045   0.4433   0.9593
   5.000   0.6143   0.01878   0.01132  -0.0002   0.4131   0.9759
   5.250   0.6690   0.01851   0.01098  -0.0055   0.3654   0.9939
   5.500   0.6908   0.01861   0.01085  -0.0056   0.3297   1.0000
   5.750   0.6955   0.01890   0.01090  -0.0024   0.3077   1.0000
   6.000   0.7040   0.01935   0.01112   0.0004   0.2889   1.0000
   6.250   0.7170   0.01989   0.01150   0.0026   0.2724   1.0000
   6.500   0.7330   0.02049   0.01198   0.0044   0.2581   1.0000
   6.750   0.7511   0.02117   0.01255   0.0059   0.2465   1.0000
   7.000   0.7713   0.02193   0.01310   0.0071   0.2375   1.0000
   7.250   0.7916   0.02267   0.01385   0.0082   0.2286   1.0000
   7.500   0.8142   0.02356   0.01453   0.0090   0.2213   1.0000
   7.750   0.8352   0.02439   0.01546   0.0100   0.2144   1.0000
   8.000   0.8588   0.02529   0.01623   0.0107   0.2086   1.0000
   8.250   0.8822   0.02643   0.01734   0.0113   0.2037   1.0000
   8.500   0.9032   0.02744   0.01848   0.0122   0.1987   1.0000
   8.750   0.9265   0.02846   0.01946   0.0127   0.1939   1.0000
   9.000   0.9526   0.02996   0.02080   0.0128   0.1898   1.0000
   9.250   0.9699   0.03114   0.02227   0.0141   0.1863   1.0000
   9.500   0.9885   0.03241   0.02370   0.0151   0.1822   1.0000
   9.750   1.0095   0.03366   0.02498   0.0157   0.1782   1.0000
  10.000   1.0348   0.03558   0.02675   0.0157   0.1742   1.0000
  10.250   1.0438   0.03697   0.02854   0.0175   0.1710   1.0000
  10.500   1.0562   0.03848   0.03027   0.0189   0.1669   1.0000
  10.750   1.0751   0.03978   0.03157   0.0197   0.1626   1.0000
  11.000   1.0972   0.04197   0.03365   0.0197   0.1586   1.0000
  11.250   1.0939   0.04384   0.03597   0.0223   0.1558   1.0000
  11.500   1.0930   0.04593   0.03835   0.0244   0.1526   1.0000
  11.750   1.1047   0.04753   0.04002   0.0254   0.1489   1.0000
  12.000   1.1376   0.04947   0.04171   0.0246   0.1445   1.0000
  12.250   1.1160   0.05218   0.04483   0.0278   0.1428   1.0000
  12.500   1.0858   0.05525   0.04821   0.0312   0.1418   1.0000
  12.750   1.0458   0.05944   0.05267   0.0331   0.1412   1.0000
  13.000   0.9902   0.06633   0.05983   0.0317   0.1417   1.0000
  13.250   0.9048   0.07946   0.07321   0.0249   0.1433   1.0000
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