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GOE 611 AIRFOIL (goe611-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 611 AIRFOIL (goe611-il)
Reynolds number: 200,000
Max Cl/Cd: 77.33 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe611-il-200000.txt
Download as CSV file: xf-goe611-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1437   0.08894   0.08573  -0.0737   0.9668   0.0341
  -8.000  -0.1279   0.08413   0.08091  -0.0849   0.9588   0.0353
  -7.750  -0.1110   0.07872   0.07542  -0.0985   0.9468   0.0358
  -7.500  -0.0965   0.07318   0.06980  -0.1043   0.9393   0.0361
  -7.250  -0.0840   0.06966   0.06635  -0.1018   0.9344   0.0369
  -7.000  -0.0650   0.06652   0.06319  -0.1030   0.9299   0.0382
  -6.750  -0.0516   0.06339   0.06001  -0.1052   0.9203   0.0398
  -6.500  -0.0305   0.05928   0.05577  -0.1102   0.9136   0.0424
  -6.250  -0.0055   0.05624   0.05212  -0.1168   0.9025   0.0448
  -6.000   0.0048   0.05060   0.04660  -0.1171   0.8956   0.0459
  -5.750   0.0212   0.04797   0.04397  -0.1170   0.8883   0.0472
  -5.500   0.0398   0.04552   0.04142  -0.1174   0.8808   0.0494
  -5.250   0.0711   0.04489   0.04007  -0.1188   0.8727   0.0559
  -5.000   0.0845   0.03939   0.03463  -0.1193   0.8653   0.0578
  -4.750   0.1046   0.03735   0.03260  -0.1192   0.8579   0.0611
  -4.500   0.1302   0.03560   0.03028  -0.1193   0.8498   0.0706
  -4.250   0.1511   0.03295   0.02770  -0.1194   0.8425   0.0737
  -4.000   0.1768   0.03189   0.02614  -0.1191   0.8342   0.0853
  -3.750   0.1991   0.02939   0.02372  -0.1192   0.8268   0.0900
  -3.500   0.2230   0.02790   0.02200  -0.1190   0.8183   0.1036
  -3.250   0.2478   0.02648   0.02044  -0.1190   0.8108   0.1206
  -3.000   0.2713   0.02529   0.01916  -0.1187   0.8016   0.1397
  -2.000   0.3931   0.01902   0.01125  -0.1156   0.7688   0.0765
  -1.750   0.4232   0.01880   0.01065  -0.1149   0.7607   0.0695
  -1.500   0.4504   0.01782   0.00954  -0.1145   0.7513   0.0698
  -1.250   0.4776   0.01712   0.00877  -0.1140   0.7421   0.0689
  -1.000   0.5055   0.01633   0.00789  -0.1137   0.7338   0.0684
  -0.750   0.5317   0.01580   0.00735  -0.1132   0.7236   0.0686
  -0.500   0.5590   0.01539   0.00688  -0.1129   0.7148   0.0692
  -0.250   0.5852   0.01478   0.00630  -0.1126   0.7052   0.0725
   0.000   0.6117   0.01450   0.00600  -0.1123   0.6952   0.0749
   0.250   0.6395   0.01429   0.00568  -0.1121   0.6864   0.0780
   0.500   0.6663   0.01416   0.00546  -0.1118   0.6756   0.0826
   0.750   0.6930   0.01400   0.00528  -0.1115   0.6646   0.0962
   1.000   0.7250   0.01181   0.00528  -0.1121   0.6542   1.0000
   1.250   0.7512   0.01190   0.00514  -0.1116   0.6435   1.0000
   1.500   0.7763   0.01202   0.00513  -0.1110   0.6316   1.0000
   1.750   0.8020   0.01216   0.00514  -0.1106   0.6210   1.0000
   2.000   0.8285   0.01232   0.00514  -0.1104   0.6120   1.0000
   2.250   0.8539   0.01249   0.00523  -0.1100   0.6018   1.0000
   2.500   0.8799   0.01267   0.00533  -0.1097   0.5927   1.0000
   2.750   0.9062   0.01287   0.00539  -0.1095   0.5839   1.0000
   3.000   0.9314   0.01306   0.00556  -0.1091   0.5742   1.0000
   3.250   0.9577   0.01328   0.00568  -0.1089   0.5659   1.0000
   3.500   0.9829   0.01348   0.00584  -0.1086   0.5564   1.0000
   3.750   1.0082   0.01371   0.00601  -0.1082   0.5472   1.0000
   4.000   1.0339   0.01394   0.00615  -0.1080   0.5384   1.0000
   4.250   1.0584   0.01416   0.00640  -0.1075   0.5292   1.0000
   4.500   1.0843   0.01442   0.00658  -0.1073   0.5215   1.0000
   4.750   1.1085   0.01465   0.00684  -0.1068   0.5125   1.0000
   5.000   1.1336   0.01492   0.00708  -0.1065   0.5045   1.0000
   5.250   1.1578   0.01516   0.00733  -0.1060   0.4959   1.0000
   5.500   1.1823   0.01544   0.00760  -0.1056   0.4880   1.0000
   5.750   1.2064   0.01570   0.00786  -0.1052   0.4799   1.0000
   6.000   1.2295   0.01596   0.00817  -0.1045   0.4709   1.0000
   6.250   1.2534   0.01624   0.00840  -0.1040   0.4625   1.0000
   6.500   1.2752   0.01649   0.00875  -0.1031   0.4531   1.0000
   6.750   1.2981   0.01679   0.00905  -0.1025   0.4450   1.0000
   7.000   1.3196   0.01707   0.00939  -0.1016   0.4360   1.0000
   7.250   1.3407   0.01737   0.00973  -0.1006   0.4266   1.0000
   7.500   1.3602   0.01767   0.01003  -0.0993   0.4159   1.0000
   7.750   1.3775   0.01798   0.01037  -0.0976   0.4030   1.0000
   8.000   1.3932   0.01832   0.01074  -0.0957   0.3890   1.0000
   8.250   1.4088   0.01870   0.01116  -0.0938   0.3758   1.0000
   8.500   1.4228   0.01913   0.01163  -0.0916   0.3625   1.0000
   8.750   1.4326   0.01962   0.01214  -0.0887   0.3477   1.0000
   9.000   1.4413   0.02023   0.01274  -0.0858   0.3316   1.0000
   9.250   1.4493   0.02096   0.01345  -0.0829   0.3148   1.0000
   9.500   1.4567   0.02181   0.01429  -0.0801   0.2948   1.0000
   9.750   1.4607   0.02290   0.01532  -0.0771   0.2723   1.0000
  10.000   1.4640   0.02417   0.01652  -0.0742   0.2482   1.0000
  10.250   1.4652   0.02569   0.01796  -0.0714   0.2244   1.0000
  10.500   1.4646   0.02747   0.01963  -0.0687   0.2006   1.0000
  10.750   1.4620   0.02954   0.02158  -0.0660   0.1758   1.0000
  11.000   1.4595   0.03173   0.02367  -0.0637   0.1584   1.0000
  11.250   1.4578   0.03397   0.02585  -0.0617   0.1459   1.0000
  11.500   1.4576   0.03617   0.02805  -0.0600   0.1366   1.0000
  11.750   1.4592   0.03830   0.03022  -0.0585   0.1294   1.0000
  12.000   1.4595   0.04061   0.03258  -0.0571   0.1231   1.0000
  12.250   1.4611   0.04288   0.03491  -0.0559   0.1157   1.0000
  12.500   1.4597   0.04549   0.03756  -0.0547   0.1086   1.0000
  12.750   1.4651   0.04755   0.03971  -0.0539   0.0994   1.0000
  13.000   1.4691   0.04981   0.04201  -0.0532   0.0813   1.0000
  13.250   1.4455   0.05509   0.04694  -0.0521   0.0424   1.0000
  13.500   1.4296   0.05977   0.05159  -0.0513   0.0306   1.0000
  13.750   1.4226   0.06358   0.05546  -0.0509   0.0277   1.0000
  14.000   1.4181   0.06719   0.05917  -0.0506   0.0261   1.0000
  14.250   1.4135   0.07090   0.06302  -0.0505   0.0249   1.0000
  14.500   1.4087   0.07474   0.06700  -0.0505   0.0241   1.0000
  14.750   1.4045   0.07858   0.07099  -0.0507   0.0235   1.0000
  15.000   1.3996   0.08258   0.07515  -0.0510   0.0231   1.0000
  15.250   1.3933   0.08685   0.07959  -0.0515   0.0227   1.0000
  15.500   1.3859   0.09135   0.08425  -0.0521   0.0223   1.0000
  15.750   1.3777   0.09607   0.08913  -0.0530   0.0219   1.0000
  16.000   1.3685   0.10100   0.09421  -0.0541   0.0216   1.0000
  16.250   1.3584   0.10613   0.09949  -0.0553   0.0212   1.0000
  16.500   1.3482   0.11138   0.10488  -0.0567   0.0209   1.0000
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