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GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il)
Reynolds number: 100,000
Max Cl/Cd: 62.77 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe610bm-il-100000.txt
Download as CSV file: xf-goe610bm-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610-B MOD. 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.2995   0.09589   0.09149  -0.0273   1.0000   0.0560
  -6.750  -0.3053   0.09532   0.09102  -0.0292   1.0000   0.0571
  -6.500  -0.3090   0.09495   0.09074  -0.0326   1.0000   0.0577
  -6.250  -0.3069   0.09400   0.08981  -0.0369   1.0000   0.0581
  -6.000  -0.3109   0.08964   0.08555  -0.0341   1.0000   0.0588
  -5.750  -0.3165   0.08595   0.08194  -0.0272   1.0000   0.0601
  -5.500  -0.3180   0.08358   0.07962  -0.0247   1.0000   0.0615
  -5.250  -0.3172   0.08139   0.07747  -0.0239   1.0000   0.0633
  -5.000  -0.3130   0.07907   0.07518  -0.0246   1.0000   0.0656
  -4.750  -0.3026   0.07652   0.07262  -0.0276   1.0000   0.0688
  -4.500  -0.2485   0.07095   0.06685  -0.0443   0.9956   0.0737
  -4.250  -0.2266   0.06687   0.06280  -0.0446   0.9900   0.0778
  -4.000  -0.1642   0.06127   0.05696  -0.0597   0.9840   0.0889
  -3.750  -0.1138   0.05698   0.05246  -0.0694   0.9770   0.1027
  -3.500  -0.0648   0.05274   0.04803  -0.0775   0.9713   0.1171
  -3.250  -0.0246   0.04898   0.04415  -0.0828   0.9643   0.1320
  -3.000   0.0145   0.04559   0.04074  -0.0868   0.9581   0.1501
  -2.750   0.0632   0.04296   0.03788  -0.0935   0.9510   0.1857
  -1.750   0.2915   0.02811   0.02119  -0.1202   0.9282   0.1483
  -1.500   0.3413   0.02497   0.01720  -0.1230   0.9198   0.1108
  -1.250   0.3892   0.02302   0.01481  -0.1261   0.9132   0.1079
  -1.000   0.4266   0.02181   0.01313  -0.1269   0.9015   0.1026
  -0.750   0.4613   0.02086   0.01198  -0.1273   0.8895   0.1018
  -0.500   0.4938   0.01981   0.01087  -0.1274   0.8771   0.1030
  -0.250   0.5235   0.01901   0.01010  -0.1270   0.8636   0.1075
   0.000   0.5517   0.01849   0.00952  -0.1261   0.8492   0.1157
   0.250   0.5787   0.01789   0.00896  -0.1251   0.8343   0.1229
   0.500   0.6062   0.01747   0.00850  -0.1242   0.8191   0.1373
   0.750   0.6292   0.01557   0.00835  -0.1228   0.8049   0.7071
   1.000   0.6550   0.01524   0.00785  -0.1209   0.7894   1.0000
   1.250   0.6815   0.01534   0.00768  -0.1200   0.7744   1.0000
   1.500   0.7081   0.01548   0.00762  -0.1192   0.7598   1.0000
   1.750   0.7347   0.01567   0.00763  -0.1186   0.7456   1.0000
   2.000   0.7613   0.01590   0.00771  -0.1180   0.7319   1.0000
   2.250   0.7881   0.01617   0.00786  -0.1176   0.7189   1.0000
   2.500   0.8149   0.01645   0.00806  -0.1172   0.7065   1.0000
   2.750   0.8420   0.01673   0.00824  -0.1168   0.6953   1.0000
   3.000   0.8690   0.01703   0.00846  -0.1165   0.6843   1.0000
   3.250   0.8957   0.01740   0.00881  -0.1163   0.6727   1.0000
   3.500   0.9225   0.01776   0.00919  -0.1161   0.6621   1.0000
   3.750   0.9497   0.01807   0.00945  -0.1159   0.6531   1.0000
   4.000   0.9764   0.01844   0.00984  -0.1157   0.6430   1.0000
   4.250   1.0029   0.01883   0.01028  -0.1155   0.6328   1.0000
   4.500   1.0293   0.01906   0.01054  -0.1150   0.6216   1.0000
   4.750   1.0554   0.01920   0.01067  -0.1143   0.6088   1.0000
   5.000   1.0812   0.01931   0.01077  -0.1136   0.5948   1.0000
   5.250   1.1070   0.01947   0.01092  -0.1129   0.5810   1.0000
   5.500   1.1331   0.01968   0.01117  -0.1122   0.5683   1.0000
   5.750   1.1590   0.02000   0.01153  -0.1117   0.5563   1.0000
   6.000   1.1844   0.02034   0.01197  -0.1112   0.5434   1.0000
   6.250   1.2088   0.02048   0.01210  -0.1101   0.5247   1.0000
   6.500   1.2320   0.02064   0.01235  -0.1090   0.5039   1.0000
   6.750   1.2547   0.02070   0.01240  -0.1077   0.4803   1.0000
   7.000   1.2763   0.02072   0.01243  -0.1063   0.4542   1.0000
   7.250   1.2982   0.02090   0.01281  -0.1051   0.4314   1.0000
   7.500   1.3193   0.02107   0.01310  -0.1038   0.4042   1.0000
   7.750   1.3382   0.02132   0.01342  -0.1022   0.3647   1.0000
   8.000   1.3560   0.02188   0.01391  -0.1006   0.3155   1.0000
   8.250   1.3718   0.02282   0.01466  -0.0988   0.2612   1.0000
   8.500   1.3811   0.02447   0.01587  -0.0965   0.1984   1.0000
   8.750   1.3873   0.02649   0.01748  -0.0939   0.1477   1.0000
   9.000   1.3946   0.02838   0.01912  -0.0913   0.0985   1.0000
   9.500   1.3993   0.03253   0.02291  -0.0849   0.0489   1.0000
   9.750   1.4007   0.03429   0.02478  -0.0814   0.0452   1.0000
  10.000   1.4009   0.03619   0.02684  -0.0781   0.0428   1.0000
  10.250   1.3998   0.03835   0.02915  -0.0752   0.0411   1.0000
  10.500   1.3970   0.04082   0.03175  -0.0725   0.0399   1.0000
  10.750   1.3929   0.04358   0.03463  -0.0701   0.0389   1.0000
  11.000   1.3907   0.04634   0.03749  -0.0680   0.0380   1.0000
  11.250   1.3933   0.04879   0.04011  -0.0662   0.0370   1.0000
  11.500   1.3969   0.05126   0.04273  -0.0645   0.0357   1.0000
  11.750   1.4019   0.05372   0.04532  -0.0628   0.0345   1.0000
  12.000   1.4106   0.05607   0.04784  -0.0609   0.0340   1.0000
  12.250   1.4232   0.05844   0.05036  -0.0590   0.0337   1.0000
  12.500   1.4372   0.06110   0.05324  -0.0571   0.0336   1.0000
  12.750   1.4482   0.06435   0.05677  -0.0554   0.0338   1.0000
  13.000   1.4513   0.06824   0.06100  -0.0540   0.0342   1.0000
  13.250   1.4469   0.07262   0.06573  -0.0529   0.0346   1.0000
  13.500   1.4372   0.07739   0.07084  -0.0522   0.0350   1.0000
  13.750   1.4235   0.08254   0.07630  -0.0522   0.0354   1.0000
  14.000   1.4073   0.08804   0.08209  -0.0527   0.0358   1.0000
  14.250   1.3891   0.09395   0.08828  -0.0540   0.0361   1.0000
  14.500   1.3697   0.10025   0.09483  -0.0560   0.0364   1.0000
  14.750   1.3492   0.10702   0.10183  -0.0588   0.0367   1.0000
  15.000   1.3282   0.11430   0.10932  -0.0624   0.0370   1.0000
  15.250   1.3068   0.12218   0.11739  -0.0669   0.0372   1.0000
  15.500   1.2853   0.13074   0.12612  -0.0722   0.0375   1.0000
  15.750   1.2640   0.13995   0.13548  -0.0782   0.0378   1.0000
  16.000   1.2446   0.14956   0.14519  -0.0845   0.0381   1.0000
  16.250   1.2235   0.16089   0.15666  -0.0927   0.0387   1.0000
  16.500   1.1562   0.19756   0.19318  -0.1173   0.0453   1.0000
  16.750   1.1600   0.20269   0.19830  -0.1193   0.0470   1.0000
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