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GOE 611 AIRFOIL (goe611-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 611 AIRFOIL (goe611-il)
Reynolds number: 200,000
Max Cl/Cd: 75.77 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe611-il-200000-n5.txt
Download as CSV file: xf-goe611-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 611 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1052   0.08965   0.08616  -0.0847   0.9100   0.0228
  -8.500  -0.0980   0.08595   0.08243  -0.0873   0.8971   0.0228
  -8.250  -0.0921   0.08230   0.07876  -0.0899   0.8848   0.0228
  -8.000  -0.0863   0.07865   0.07507  -0.0930   0.8739   0.0228
  -7.750  -0.0770   0.07467   0.07102  -0.0967   0.8641   0.0228
  -7.500  -0.0668   0.07071   0.06701  -0.0999   0.8549   0.0228
  -7.250  -0.0559   0.06699   0.06320  -0.1021   0.8473   0.0227
  -7.000  -0.0475   0.06482   0.06104  -0.1004   0.8395   0.0219
  -6.750  -0.0350   0.06099   0.05710  -0.1034   0.8322   0.0212
  -6.500  -0.0185   0.05637   0.05236  -0.1081   0.8244   0.0220
  -6.250  -0.0011   0.05204   0.04784  -0.1113   0.8177   0.0221
  -6.000   0.0158   0.04844   0.04409  -0.1131   0.8107   0.0216
  -5.750   0.0349   0.04456   0.04000  -0.1149   0.8040   0.0213
  -5.500   0.0558   0.04066   0.03583  -0.1163   0.7981   0.0212
  -5.250   0.0781   0.03664   0.03147  -0.1172   0.7911   0.0218
  -5.000   0.1014   0.03351   0.02799  -0.1177   0.7853   0.0238
  -4.750   0.1243   0.03169   0.02600  -0.1178   0.7781   0.0248
  -4.500   0.1489   0.02902   0.02297  -0.1178   0.7717   0.0253
  -4.250   0.1744   0.02673   0.02030  -0.1176   0.7651   0.0266
  -4.000   0.2022   0.02482   0.01778  -0.1170   0.7580   0.0290
  -3.750   0.2276   0.02260   0.01521  -0.1169   0.7517   0.0299
  -3.500   0.2533   0.02154   0.01406  -0.1169   0.7437   0.0312
  -3.250   0.2801   0.02074   0.01308  -0.1169   0.7367   0.0334
  -3.000   0.3073   0.01964   0.01171  -0.1166   0.7284   0.0345
  -2.750   0.3350   0.01869   0.01050  -0.1164   0.7210   0.0353
  -2.500   0.3625   0.01821   0.00979  -0.1161   0.7122   0.0372
  -2.250   0.3901   0.01763   0.00901  -0.1159   0.7040   0.0379
  -2.000   0.4170   0.01665   0.00790  -0.1157   0.6952   0.0385
  -1.750   0.4437   0.01595   0.00714  -0.1155   0.6861   0.0392
  -1.500   0.4705   0.01546   0.00659  -0.1153   0.6774   0.0409
  -1.250   0.4972   0.01509   0.00620  -0.1151   0.6674   0.0425
  -1.000   0.5239   0.01474   0.00578  -0.1149   0.6580   0.0431
  -0.750   0.5505   0.01445   0.00542  -0.1146   0.6483   0.0438
  -0.500   0.5772   0.01421   0.00514  -0.1145   0.6383   0.0446
  -0.250   0.6039   0.01405   0.00489  -0.1143   0.6285   0.0456
   0.000   0.6304   0.01394   0.00468  -0.1141   0.6173   0.0467
   0.250   0.6568   0.01390   0.00454  -0.1138   0.6052   0.0488
   0.500   0.6831   0.01384   0.00438  -0.1136   0.5937   0.0518
   0.750   0.7093   0.01385   0.00429  -0.1133   0.5822   0.0544
   1.000   0.7354   0.01389   0.00424  -0.1131   0.5709   0.0586
   1.250   0.7617   0.01390   0.00424  -0.1129   0.5605   0.0771
   1.750   0.8127   0.01214   0.00449  -0.1121   0.5410   1.0000
   2.000   0.8381   0.01233   0.00456  -0.1118   0.5314   1.0000
   2.250   0.8632   0.01254   0.00463  -0.1114   0.5226   1.0000
   2.500   0.8887   0.01272   0.00475  -0.1111   0.5138   1.0000
   2.750   0.9138   0.01294   0.00487  -0.1107   0.5060   1.0000
   3.000   0.9391   0.01313   0.00501  -0.1104   0.4975   1.0000
   3.250   0.9640   0.01335   0.00516  -0.1100   0.4899   1.0000
   3.500   0.9887   0.01356   0.00533  -0.1096   0.4807   1.0000
   3.750   1.0131   0.01379   0.00551  -0.1092   0.4717   1.0000
   4.000   1.0371   0.01403   0.00570  -0.1087   0.4626   1.0000
   4.250   1.0616   0.01426   0.00591  -0.1082   0.4544   1.0000
   4.500   1.0853   0.01452   0.00612  -0.1077   0.4464   1.0000
   4.750   1.1093   0.01475   0.00636  -0.1072   0.4383   1.0000
   5.000   1.1323   0.01503   0.00661  -0.1066   0.4302   1.0000
   5.250   1.1558   0.01528   0.00688  -0.1060   0.4216   1.0000
   5.500   1.1780   0.01558   0.00715  -0.1053   0.4136   1.0000
   5.750   1.2010   0.01585   0.00746  -0.1046   0.4054   1.0000
   6.000   1.2226   0.01617   0.00777  -0.1038   0.3978   1.0000
   6.250   1.2440   0.01648   0.00810  -0.1029   0.3880   1.0000
   6.500   1.2642   0.01683   0.00847  -0.1018   0.3779   1.0000
   6.750   1.2833   0.01721   0.00885  -0.1006   0.3688   1.0000
   7.000   1.3033   0.01756   0.00924  -0.0995   0.3596   1.0000
   7.250   1.3214   0.01797   0.00966  -0.0980   0.3512   1.0000
   7.500   1.3380   0.01837   0.01012  -0.0963   0.3421   1.0000
   7.750   1.3527   0.01885   0.01062  -0.0944   0.3306   1.0000
   8.000   1.3633   0.01951   0.01123  -0.0918   0.3127   1.0000
   8.250   1.3714   0.02035   0.01197  -0.0890   0.2908   1.0000
   8.500   1.3767   0.02139   0.01289  -0.0860   0.2643   1.0000
   8.750   1.3824   0.02252   0.01394  -0.0832   0.2384   1.0000
   9.000   1.3852   0.02392   0.01519  -0.0803   0.2098   1.0000
   9.250   1.3853   0.02560   0.01671  -0.0774   0.1777   1.0000
  10.000   1.3906   0.03093   0.02182  -0.0705   0.1294   1.0000
  10.250   1.3945   0.03272   0.02363  -0.0687   0.1224   1.0000
  10.500   1.3995   0.03445   0.02540  -0.0672   0.1142   1.0000
  10.750   1.4020   0.03645   0.02742  -0.0657   0.1073   1.0000
  11.000   1.4104   0.03800   0.02905  -0.0646   0.0994   1.0000
  11.250   1.4141   0.04000   0.03103  -0.0633   0.0737   1.0000
  11.500   1.3896   0.04471   0.03540  -0.0608   0.0292   1.0000
  11.750   1.3775   0.04851   0.03918  -0.0592   0.0205   1.0000
  12.000   1.3763   0.05133   0.04209  -0.0583   0.0178   1.0000
  12.250   1.3779   0.05393   0.04483  -0.0575   0.0167   1.0000
  12.500   1.3786   0.05670   0.04776  -0.0569   0.0159   1.0000
  12.750   1.3779   0.05971   0.05092  -0.0564   0.0150   1.0000
  13.000   1.3757   0.06296   0.05432  -0.0560   0.0143   1.0000
  13.250   1.3710   0.06659   0.05812  -0.0556   0.0135   1.0000
  13.500   1.3710   0.06975   0.06142  -0.0555   0.0129   1.0000
  13.750   1.3701   0.07306   0.06489  -0.0555   0.0125   1.0000
  14.000   1.3678   0.07662   0.06861  -0.0556   0.0121   1.0000
  14.250   1.3643   0.08040   0.07254  -0.0558   0.0118   1.0000
  14.500   1.3596   0.08441   0.07671  -0.0561   0.0115   1.0000
  14.750   1.3538   0.08868   0.08115  -0.0567   0.0112   1.0000
  15.000   1.3469   0.09319   0.08581  -0.0574   0.0110   1.0000
  15.250   1.3390   0.09791   0.09069  -0.0583   0.0108   1.0000
  15.500   1.3301   0.10285   0.09578  -0.0594   0.0106   1.0000
  15.750   1.3202   0.10807   0.10113  -0.0607   0.0104   1.0000
  16.000   1.3098   0.11346   0.10666  -0.0622   0.0102   1.0000
  16.250   1.2991   0.11896   0.11229  -0.0639   0.0101   1.0000
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