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GOE 611 AIRFOIL (goe611-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 611 AIRFOIL (goe611-il)
Reynolds number: 100,000
Max Cl/Cd: 56.36 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe611-il-100000-n5.txt
Download as CSV file: xf-goe611-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1786   0.10888   0.10434  -0.0652   0.9701   0.0373
  -9.000  -0.1677   0.10519   0.10066  -0.0712   0.9615   0.0375
  -8.750  -0.1576   0.10146   0.09691  -0.0770   0.9520   0.0377
  -8.500  -0.1393   0.09567   0.09113  -0.0761   0.9491   0.0388
  -8.250  -0.1220   0.09206   0.08751  -0.0764   0.9429   0.0407
  -8.000  -0.1085   0.08848   0.08393  -0.0796   0.9353   0.0425
  -7.750  -0.1008   0.08520   0.08066  -0.0824   0.9245   0.0440
  -7.500  -0.0938   0.08181   0.07726  -0.0860   0.9136   0.0455
  -7.250  -0.0822   0.07785   0.07324  -0.0943   0.9026   0.0477
  -7.000  -0.0637   0.07365   0.06881  -0.1044   0.8935   0.0487
  -6.750  -0.0514   0.07025   0.06521  -0.1078   0.8833   0.0489
  -6.500  -0.0391   0.06512   0.06026  -0.1064   0.8789   0.0504
  -6.250  -0.0265   0.06230   0.05742  -0.1061   0.8706   0.0520
  -6.000  -0.0076   0.05920   0.05422  -0.1080   0.8640   0.0556
  -5.750   0.0145   0.05559   0.05011  -0.1137   0.8547   0.0626
  -5.500   0.0306   0.05228   0.04694  -0.1131   0.8489   0.0656
  -5.250   0.0578   0.05156   0.04553  -0.1159   0.8401   0.0761
  -5.000   0.0818   0.04409   0.03789  -0.1164   0.8344   0.0479
  -4.750   0.1024   0.04082   0.03447  -0.1169   0.8275   0.0456
  -4.500   0.1274   0.03800   0.03127  -0.1173   0.8201   0.0465
  -4.250   0.1537   0.03515   0.02805  -0.1177   0.8140   0.0455
  -4.000   0.1780   0.03272   0.02525  -0.1175   0.8059   0.0445
  -3.750   0.2081   0.03060   0.02262  -0.1178   0.8003   0.0463
  -3.500   0.2327   0.02902   0.02064  -0.1171   0.7913   0.0473
  -3.250   0.2624   0.02729   0.01848  -0.1172   0.7853   0.0474
  -3.000   0.2883   0.02648   0.01725  -0.1164   0.7763   0.0489
  -2.750   0.3167   0.02467   0.01524  -0.1167   0.7699   0.0508
  -2.500   0.3422   0.02369   0.01407  -0.1161   0.7609   0.0513
  -2.250   0.3715   0.02269   0.01285  -0.1161   0.7542   0.0519
  -2.000   0.3965   0.02205   0.01214  -0.1155   0.7446   0.0540
  -1.750   0.4254   0.02137   0.01131  -0.1154   0.7378   0.0566
  -1.500   0.4504   0.02081   0.01068  -0.1148   0.7280   0.0573
  -1.250   0.4776   0.02024   0.01003  -0.1144   0.7202   0.0581
  -1.000   0.5033   0.01979   0.00954  -0.1139   0.7112   0.0592
  -0.750   0.5291   0.01944   0.00910  -0.1134   0.7024   0.0604
  -0.500   0.5558   0.01907   0.00866  -0.1131   0.6941   0.0635
  -0.250   0.5813   0.01885   0.00839  -0.1126   0.6847   0.0674
   0.000   0.6097   0.01862   0.00800  -0.1125   0.6771   0.0704
   0.250   0.6350   0.01857   0.00786  -0.1120   0.6670   0.0742
   0.500   0.6624   0.01843   0.00764  -0.1118   0.6587   0.0818
   0.750   0.6862   0.01714   0.00766  -0.1117   0.6499   0.5335
   1.000   0.7191   0.01628   0.00760  -0.1118   0.6411   1.0000
   1.250   0.7456   0.01641   0.00751  -0.1115   0.6327   1.0000
   1.500   0.7706   0.01660   0.00756  -0.1110   0.6234   1.0000
   2.000   0.8220   0.01695   0.00761  -0.1103   0.6054   1.0000
   2.250   0.8475   0.01712   0.00765  -0.1099   0.5961   1.0000
   2.500   0.8731   0.01730   0.00770  -0.1095   0.5865   1.0000
   2.750   0.8972   0.01753   0.00785  -0.1089   0.5761   1.0000
   3.000   0.9226   0.01774   0.00794  -0.1085   0.5670   1.0000
   3.250   0.9469   0.01798   0.00810  -0.1080   0.5571   1.0000
   3.500   0.9712   0.01824   0.00831  -0.1075   0.5480   1.0000
   3.750   0.9964   0.01848   0.00847  -0.1071   0.5398   1.0000
   4.000   1.0199   0.01878   0.00876  -0.1066   0.5309   1.0000
   4.250   1.0452   0.01904   0.00894  -0.1062   0.5231   1.0000
   4.500   1.0674   0.01936   0.00928  -0.1054   0.5132   1.0000
   4.750   1.0910   0.01965   0.00952  -0.1048   0.5043   1.0000
   5.000   1.1133   0.01996   0.00983  -0.1041   0.4944   1.0000
   5.250   1.1353   0.02030   0.01018  -0.1032   0.4850   1.0000
   5.500   1.1583   0.02061   0.01046  -0.1026   0.4768   1.0000
   5.750   1.1793   0.02099   0.01093  -0.1017   0.4680   1.0000
   6.000   1.2022   0.02133   0.01124  -0.1010   0.4608   1.0000
   6.250   1.2225   0.02174   0.01175  -0.1000   0.4524   1.0000
   6.500   1.2445   0.02210   0.01210  -0.0992   0.4452   1.0000
   6.750   1.2633   0.02253   0.01266  -0.0980   0.4362   1.0000
   7.000   1.2833   0.02293   0.01307  -0.0969   0.4282   1.0000
   7.250   1.3011   0.02339   0.01363  -0.0955   0.4191   1.0000
   7.500   1.3194   0.02384   0.01416  -0.0942   0.4111   1.0000
   7.750   1.3363   0.02433   0.01474  -0.0927   0.4027   1.0000
   8.000   1.3522   0.02484   0.01533  -0.0910   0.3943   1.0000
   8.250   1.3649   0.02536   0.01590  -0.0888   0.3850   1.0000
   8.500   1.3764   0.02599   0.01664  -0.0865   0.3750   1.0000
   8.750   1.3888   0.02662   0.01736  -0.0844   0.3662   1.0000
   9.000   1.4003   0.02735   0.01819  -0.0823   0.3568   1.0000
   9.250   1.4079   0.02821   0.01913  -0.0797   0.3441   1.0000
   9.500   1.4120   0.02927   0.02020  -0.0769   0.3279   1.0000
   9.750   1.4133   0.03056   0.02146  -0.0740   0.3094   1.0000
  10.000   1.4143   0.03205   0.02296  -0.0713   0.2893   1.0000
  10.250   1.4159   0.03366   0.02460  -0.0690   0.2711   1.0000
  10.500   1.4157   0.03552   0.02645  -0.0668   0.2522   1.0000
  10.750   1.4142   0.03761   0.02852  -0.0646   0.2338   1.0000
  11.000   1.4111   0.03996   0.03084  -0.0627   0.2143   1.0000
  11.250   1.4048   0.04272   0.03354  -0.0608   0.1930   1.0000
  11.500   1.3961   0.04586   0.03660  -0.0591   0.1735   1.0000
  11.750   1.3876   0.04913   0.03983  -0.0576   0.1583   1.0000
  12.000   1.3802   0.05246   0.04315  -0.0565   0.1482   1.0000
  12.250   1.3733   0.05588   0.04659  -0.0556   0.1397   1.0000
  12.500   1.3660   0.05950   0.05026  -0.0549   0.1325   1.0000
  12.750   1.3602   0.06308   0.05391  -0.0545   0.1257   1.0000
  13.250   1.3520   0.07016   0.06120  -0.0541   0.1153   1.0000
  13.500   1.3472   0.07394   0.06509  -0.0541   0.1095   1.0000
  13.750   1.3419   0.07789   0.06914  -0.0543   0.1017   1.0000
  14.000   1.3388   0.08165   0.07302  -0.0546   0.0916   1.0000
  14.250   1.3259   0.08682   0.07810  -0.0553   0.0535   1.0000
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