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GOE 611 AIRFOIL (goe611-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 611 AIRFOIL (goe611-il)
Reynolds number: 500,000
Max Cl/Cd: 106.56 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe611-il-500000.txt
Download as CSV file: xf-goe611-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.0620   0.08936   0.08722  -0.0784   0.9416   0.0189
  -9.750  -0.0622   0.08553   0.08336  -0.0803   0.9277   0.0189
  -9.500  -0.0626   0.08175   0.07954  -0.0819   0.9137   0.0190
  -9.250  -0.0599   0.07776   0.07551  -0.0817   0.9010   0.0191
  -9.000  -0.0514   0.07495   0.07265  -0.0806   0.8893   0.0194
  -8.750  -0.0461   0.07204   0.06969  -0.0806   0.8790   0.0196
  -8.500  -0.0425   0.06900   0.06659  -0.0810   0.8698   0.0198
  -8.250  -0.0394   0.06583   0.06340  -0.0819   0.8607   0.0201
  -8.000  -0.0370   0.06259   0.06012  -0.0829   0.8529   0.0204
  -7.750  -0.0352   0.05922   0.05673  -0.0843   0.8450   0.0208
  -7.500  -0.1002   0.06903   0.06650  -0.0891   0.8603   0.0199
  -7.250  -0.0889   0.06556   0.06297  -0.0927   0.8516   0.0203
  -7.000  -0.0759   0.06187   0.05920  -0.0966   0.8433   0.0208
  -6.750  -0.0608   0.05795   0.05519  -0.1006   0.8359   0.0215
  -6.500  -0.0348   0.05146   0.04840  -0.1084   0.8284   0.0233
  -6.250  -0.0152   0.04688   0.04353  -0.1108   0.8221   0.0234
  -6.000  -0.0028   0.04198   0.03850  -0.1120   0.8154   0.0237
  -5.750   0.0145   0.03986   0.03631  -0.1123   0.8095   0.0241
  -5.500   0.0342   0.03808   0.03448  -0.1128   0.8028   0.0247
  -5.250   0.0559   0.03595   0.03220  -0.1132   0.7965   0.0258
  -5.000   0.0866   0.03323   0.02891  -0.1131   0.7907   0.0288
  -4.250   0.1521   0.02534   0.02058  -0.1137   0.7714   0.0312
  -4.000   0.1786   0.02406   0.01906  -0.1135   0.7650   0.0341
  -3.750   0.2047   0.02166   0.01622  -0.1130   0.7584   0.0372
  -3.500   0.2303   0.02044   0.01494  -0.1132   0.7512   0.0386
  -3.250   0.2573   0.01952   0.01387  -0.1131   0.7440   0.0415
  -3.000   0.2847   0.01822   0.01222  -0.1128   0.7362   0.0468
  -2.750   0.3112   0.01734   0.01133  -0.1130   0.7283   0.0499
  -2.500   0.3389   0.01667   0.01037  -0.1129   0.7199   0.0583
  -2.250   0.3658   0.01574   0.00946  -0.1130   0.7106   0.0621
  -2.000   0.3930   0.01514   0.00867  -0.1129   0.7006   0.0728
  -1.750   0.4202   0.01468   0.00817  -0.1129   0.6892   0.0802
  -1.500   0.4519   0.01314   0.00614  -0.1115   0.6783   0.0453
  -1.250   0.4790   0.01231   0.00526  -0.1112   0.6669   0.0437
  -1.000   0.5062   0.01189   0.00476  -0.1110   0.6556   0.0439
  -0.750   0.5333   0.01159   0.00437  -0.1108   0.6438   0.0443
  -0.500   0.5601   0.01123   0.00396  -0.1106   0.6312   0.0443
  -0.250   0.5870   0.01100   0.00367  -0.1104   0.6186   0.0446
   0.000   0.6139   0.01082   0.00343  -0.1103   0.6069   0.0450
   0.250   0.6407   0.01061   0.00314  -0.1101   0.5961   0.0458
   0.500   0.6678   0.01048   0.00296  -0.1101   0.5851   0.0483
   0.750   0.6951   0.01044   0.00287  -0.1100   0.5747   0.0501
   1.000   0.7222   0.01046   0.00282  -0.1100   0.5649   0.0525
   1.250   0.7493   0.01050   0.00279  -0.1099   0.5551   0.0557
   1.500   0.7765   0.01049   0.00281  -0.1099   0.5458   0.0818
   1.750   0.8023   0.00858   0.00306  -0.1099   0.5373   1.0000
   2.000   0.8288   0.00870   0.00310  -0.1097   0.5283   1.0000
   2.250   0.8549   0.00886   0.00317  -0.1095   0.5200   1.0000
   2.500   0.8812   0.00901   0.00325  -0.1093   0.5115   1.0000
   2.750   0.9075   0.00916   0.00334  -0.1092   0.5036   1.0000
   3.000   0.9334   0.00933   0.00344  -0.1089   0.4947   1.0000
   3.250   0.9597   0.00948   0.00355  -0.1088   0.4860   1.0000
   3.500   0.9852   0.00967   0.00367  -0.1085   0.4777   1.0000
   3.750   1.0116   0.00981   0.00379  -0.1084   0.4691   1.0000
   4.000   1.0370   0.01000   0.00393  -0.1081   0.4610   1.0000
   4.250   1.0629   0.01016   0.00408  -0.1080   0.4522   1.0000
   4.500   1.0883   0.01035   0.00423  -0.1077   0.4440   1.0000
   4.750   1.1136   0.01054   0.00440  -0.1074   0.4352   1.0000
   5.000   1.1388   0.01072   0.00458  -0.1072   0.4266   1.0000
   5.500   1.1881   0.01115   0.00495  -0.1064   0.4079   1.0000
   5.750   1.2121   0.01139   0.00517  -0.1059   0.3978   1.0000
   6.000   1.2354   0.01165   0.00541  -0.1054   0.3880   1.0000
   6.250   1.2588   0.01191   0.00564  -0.1048   0.3759   1.0000
   6.500   1.2804   0.01224   0.00592  -0.1039   0.3603   1.0000
   6.750   1.3006   0.01263   0.00624  -0.1028   0.3428   1.0000
   7.000   1.3205   0.01303   0.00657  -0.1017   0.3239   1.0000
   7.250   1.3383   0.01352   0.00697  -0.1002   0.3028   1.0000
   7.500   1.3548   0.01405   0.00740  -0.0985   0.2822   1.0000
   7.750   1.3664   0.01473   0.00795  -0.0959   0.2556   1.0000
   8.000   1.3750   0.01557   0.00861  -0.0929   0.2242   1.0000
   8.250   1.3770   0.01681   0.00959  -0.0890   0.1786   1.0000
   8.500   1.3798   0.01810   0.01066  -0.0854   0.1455   1.0000
   8.750   1.3900   0.01903   0.01152  -0.0831   0.1345   1.0000
   9.000   1.4024   0.01984   0.01234  -0.0813   0.1277   1.0000
   9.250   1.4123   0.02085   0.01333  -0.0792   0.1204   1.0000
   9.500   1.4265   0.02161   0.01413  -0.0777   0.1148   1.0000
   9.750   1.4356   0.02273   0.01523  -0.0758   0.1078   1.0000
  10.000   1.4505   0.02351   0.01603  -0.0746   0.0997   1.0000
  10.250   1.4613   0.02461   0.01709  -0.0730   0.0862   1.0000
  10.500   1.4404   0.02811   0.02023  -0.0686   0.0315   1.0000
  10.750   1.4383   0.03040   0.02250  -0.0662   0.0193   1.0000
  11.000   1.4452   0.03203   0.02422  -0.0648   0.0176   1.0000
  11.250   1.4507   0.03383   0.02612  -0.0634   0.0166   1.0000
  11.500   1.4546   0.03580   0.02820  -0.0620   0.0157   1.0000
  11.750   1.4564   0.03802   0.03055  -0.0606   0.0150   1.0000
  12.000   1.4596   0.04018   0.03283  -0.0594   0.0146   1.0000
  12.250   1.4621   0.04246   0.03522  -0.0584   0.0143   1.0000
  12.500   1.4630   0.04498   0.03785  -0.0574   0.0138   1.0000
  12.750   1.4625   0.04774   0.04072  -0.0565   0.0134   1.0000
  13.000   1.4603   0.05077   0.04386  -0.0557   0.0130   1.0000
  13.250   1.4564   0.05411   0.04731  -0.0551   0.0126   1.0000
  13.500   1.4508   0.05775   0.05106  -0.0547   0.0124   1.0000
  13.750   1.4433   0.06175   0.05518  -0.0544   0.0121   1.0000
  14.000   1.4346   0.06602   0.05958  -0.0543   0.0119   1.0000
  14.250   1.4232   0.07073   0.06440  -0.0544   0.0118   1.0000
  14.500   1.4105   0.07572   0.06951  -0.0546   0.0116   1.0000
  14.750   1.3969   0.08092   0.07483  -0.0550   0.0115   1.0000
  15.000   1.3851   0.08590   0.07991  -0.0555   0.0114   1.0000
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