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GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il)
Reynolds number: 500,000
Max Cl/Cd: 95.84 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe602m-il-500000-n5.txt
Download as CSV file: xf-goe602m-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 MOD. AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3810   0.10992   0.10759  -0.0341   1.0000   0.0062
 -10.500  -0.3824   0.10601   0.10371  -0.0348   1.0000   0.0062
  -9.500  -0.5575   0.03073   0.02792  -0.0964   0.9777   0.0060
  -9.250  -0.5402   0.02633   0.02304  -0.0996   0.9723   0.0063
  -9.000  -0.5169   0.02329   0.01958  -0.1017   0.9686   0.0067
  -8.750  -0.4896   0.02098   0.01689  -0.1036   0.9665   0.0071
  -8.500  -0.4638   0.01928   0.01488  -0.1045   0.9631   0.0073
  -8.250  -0.4396   0.01754   0.01285  -0.1049   0.9586   0.0077
  -8.000  -0.4105   0.01646   0.01160  -0.1059   0.9558   0.0083
  -7.750  -0.3796   0.01567   0.01064  -0.1071   0.9536   0.0088
  -7.500  -0.3523   0.01488   0.00970  -0.1073   0.9496   0.0095
  -7.250  -0.3252   0.01419   0.00886  -0.1075   0.9450   0.0103
  -7.000  -0.2956   0.01343   0.00796  -0.1082   0.9416   0.0114
  -6.750  -0.2636   0.01301   0.00752  -0.1092   0.9389   0.0129
  -6.500  -0.2368   0.01266   0.00711  -0.1091   0.9335   0.0143
  -6.250  -0.2078   0.01226   0.00661  -0.1094   0.9288   0.0158
  -6.000  -0.1768   0.01190   0.00620  -0.1102   0.9250   0.0178
  -5.750  -0.1490   0.01181   0.00609  -0.1102   0.9192   0.0202
  -5.500  -0.1200   0.01157   0.00576  -0.1105   0.9136   0.0227
  -5.250  -0.0903   0.01142   0.00554  -0.1108   0.9083   0.0242
  -5.000  -0.0638   0.01103   0.00506  -0.1106   0.9011   0.0258
  -4.750  -0.0358   0.01056   0.00452  -0.1107   0.8946   0.0283
  -4.500  -0.0094   0.01032   0.00423  -0.1104   0.8863   0.0303
  -4.250   0.0183   0.01006   0.00388  -0.1103   0.8790   0.0318
  -4.000   0.0451   0.00983   0.00359  -0.1101   0.8708   0.0333
  -3.750   0.0722   0.00960   0.00327  -0.1099   0.8631   0.0341
  -3.500   0.0993   0.00938   0.00296  -0.1096   0.8546   0.0346
  -3.250   0.1260   0.00919   0.00270  -0.1094   0.8456   0.0351
  -3.000   0.1532   0.00904   0.00248  -0.1091   0.8364   0.0356
  -2.750   0.1801   0.00886   0.00221  -0.1088   0.8260   0.0366
  -2.500   0.2068   0.00870   0.00197  -0.1085   0.8146   0.0387
  -2.250   0.2336   0.00857   0.00178  -0.1082   0.8025   0.0425
  -2.000   0.2602   0.00844   0.00164  -0.1078   0.7898   0.0521
  -1.750   0.2862   0.00822   0.00153  -0.1075   0.7758   0.0989
  -1.500   0.3123   0.00810   0.00142  -0.1071   0.7612   0.1278
  -1.250   0.3373   0.00780   0.00135  -0.1066   0.7463   0.2198
  -1.000   0.3631   0.00773   0.00134  -0.1062   0.7308   0.2704
  -0.750   0.3891   0.00774   0.00131  -0.1058   0.7156   0.2912
  -0.500   0.4149   0.00774   0.00130  -0.1053   0.6996   0.3133
  -0.250   0.4407   0.00775   0.00129  -0.1048   0.6842   0.3329
   0.000   0.4661   0.00774   0.00130  -0.1043   0.6682   0.3595
   0.250   0.4907   0.00762   0.00135  -0.1037   0.6521   0.4346
   0.500   0.5151   0.00756   0.00144  -0.1031   0.6348   0.5163
   0.750   0.5395   0.00761   0.00150  -0.1023   0.6121   0.5569
   1.000   0.5633   0.00771   0.00155  -0.1015   0.5855   0.5881
   1.250   0.5872   0.00780   0.00161  -0.1006   0.5616   0.6164
   1.500   0.6106   0.00778   0.00170  -0.0997   0.5410   0.6655
   1.750   0.6282   0.00742   0.00183  -0.0973   0.5226   0.8629
   2.250   0.7017   0.00769   0.00203  -0.1014   0.4810   1.0000
   2.500   0.7265   0.00788   0.00213  -0.1008   0.4648   1.0000
   2.750   0.7514   0.00806   0.00225  -0.1002   0.4501   1.0000
   3.000   0.7765   0.00823   0.00238  -0.0997   0.4366   1.0000
   3.250   0.8014   0.00842   0.00251  -0.0991   0.4223   1.0000
   3.500   0.8257   0.00865   0.00266  -0.0984   0.4047   1.0000
   3.750   0.8501   0.00887   0.00283  -0.0978   0.3873   1.0000
   4.000   0.8732   0.00919   0.00303  -0.0969   0.3593   1.0000
   4.250   0.8956   0.00956   0.00324  -0.0960   0.3249   1.0000
   4.500   0.9179   0.00995   0.00349  -0.0951   0.2918   1.0000
   4.750   0.9380   0.01053   0.00383  -0.0938   0.2446   1.0000
   5.000   0.9560   0.01130   0.00426  -0.0922   0.1831   1.0000
   5.250   0.9703   0.01241   0.00490  -0.0901   0.0996   1.0000
   5.500   0.9911   0.01295   0.00532  -0.0890   0.0790   1.0000
   5.750   1.0082   0.01380   0.00593  -0.0873   0.0264   1.0000
   6.000   1.0296   0.01428   0.00640  -0.0861   0.0168   1.0000
   6.250   1.0516   0.01467   0.00685  -0.0851   0.0145   1.0000
   6.500   1.0727   0.01514   0.00737  -0.0840   0.0125   1.0000
   6.750   1.0924   0.01571   0.00803  -0.0825   0.0106   1.0000
   7.000   1.1136   0.01612   0.00850  -0.0814   0.0098   1.0000
   7.250   1.1335   0.01663   0.00909  -0.0801   0.0090   1.0000
   7.500   1.1523   0.01719   0.00971  -0.0786   0.0084   1.0000
   7.750   1.1700   0.01780   0.01038  -0.0770   0.0079   1.0000
   8.000   1.1846   0.01857   0.01121  -0.0748   0.0074   1.0000
   8.250   1.1956   0.01944   0.01216  -0.0720   0.0069   1.0000
   8.500   1.2103   0.02004   0.01283  -0.0699   0.0065   1.0000
   8.750   1.2237   0.02073   0.01358  -0.0676   0.0061   1.0000
   9.000   1.2346   0.02157   0.01453  -0.0651   0.0059   1.0000
   9.250   1.2465   0.02236   0.01539  -0.0628   0.0055   1.0000
   9.500   1.2553   0.02337   0.01647  -0.0601   0.0054   1.0000
   9.750   1.2645   0.02437   0.01755  -0.0576   0.0052   1.0000
  10.000   1.2729   0.02544   0.01868  -0.0553   0.0050   1.0000
  10.250   1.2784   0.02677   0.02009  -0.0527   0.0049   1.0000
  10.500   1.2781   0.02863   0.02205  -0.0496   0.0047   1.0000
  10.750   1.2830   0.03019   0.02371  -0.0473   0.0046   1.0000
  11.000   1.2883   0.03178   0.02541  -0.0452   0.0046   1.0000
  11.250   1.2928   0.03356   0.02732  -0.0431   0.0044   1.0000
  11.500   1.2976   0.03536   0.02924  -0.0413   0.0043   1.0000
  11.750   1.3027   0.03718   0.03119  -0.0398   0.0041   1.0000
  12.000   1.3067   0.03919   0.03333  -0.0383   0.0040   1.0000
  12.250   1.3104   0.04127   0.03552  -0.0370   0.0038   1.0000
  12.500   1.3138   0.04339   0.03781  -0.0359   0.0037   1.0000
  12.750   1.3161   0.04572   0.04026  -0.0350   0.0036   1.0000
  13.000   1.3162   0.04844   0.04313  -0.0342   0.0035   1.0000
  13.250   1.3150   0.05143   0.04627  -0.0335   0.0035   1.0000
  13.500   1.3149   0.05423   0.04918  -0.0333   0.0034   1.0000
  13.750   1.3121   0.05756   0.05266  -0.0332   0.0033   1.0000
  14.000   1.3098   0.06091   0.05614  -0.0336   0.0033   1.0000
  14.250   1.3061   0.06460   0.05995  -0.0342   0.0032   1.0000
  14.500   1.3007   0.06869   0.06419  -0.0350   0.0032   1.0000
  14.750   1.2941   0.07314   0.06878  -0.0362   0.0032   1.0000
  15.000   1.2854   0.07816   0.07397  -0.0377   0.0032   1.0000
  15.250   1.2745   0.08373   0.07973  -0.0396   0.0032   1.0000
  15.500   1.2672   0.08881   0.08490  -0.0419   0.0031   1.0000
  15.750   1.2553   0.09502   0.09129  -0.0446   0.0031   1.0000
  16.000   1.2419   0.10170   0.09814  -0.0477   0.0031   1.0000
  16.250   1.2289   0.10858   0.10517  -0.0512   0.0031   1.0000
  16.500   1.2151   0.11592   0.11268  -0.0551   0.0031   1.0000
  16.750   1.2011   0.12361   0.12054  -0.0594   0.0031   1.0000
  17.000   1.1864   0.13166   0.12874  -0.0641   0.0031   1.0000
  17.250   1.1716   0.14020   0.13744  -0.0692   0.0031   1.0000
  17.500   1.1568   0.14907   0.14646  -0.0746   0.0031   1.0000
  17.750   1.1388   0.15935   0.15691  -0.0809   0.0031   1.0000
  18.000   1.1201   0.17045   0.16816  -0.0877   0.0031   1.0000
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