Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 413 AIRFOIL (goe413-il)
Reynolds number: 500,000
Max Cl/Cd: 98.62 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe413-il-500000-n5.txt
Download as CSV file: xf-goe413-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 413 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.7978   0.06221   0.05836  -0.0724   0.9222   0.0366
 -14.000  -0.8293   0.05408   0.04990  -0.0791   0.8968   0.0367
 -13.750  -0.8466   0.04775   0.04330  -0.0851   0.8814   0.0368
 -13.500  -0.8552   0.04263   0.03793  -0.0905   0.8702   0.0369
 -13.250  -0.8558   0.03866   0.03376  -0.0951   0.8606   0.0371
 -13.000  -0.8497   0.03574   0.03070  -0.0985   0.8529   0.0372
 -12.750  -0.8413   0.03346   0.02830  -0.1012   0.8455   0.0373
 -12.500  -0.8265   0.03186   0.02659  -0.1026   0.8389   0.0375
 -12.250  -0.8094   0.03056   0.02518  -0.1035   0.8332   0.0376
 -12.000  -0.7902   0.02937   0.02391  -0.1042   0.8278   0.0378
 -11.750  -0.7699   0.02831   0.02277  -0.1048   0.8226   0.0380
 -11.500  -0.7485   0.02737   0.02174  -0.1052   0.8174   0.0382
 -11.250  -0.7262   0.02650   0.02077  -0.1056   0.8124   0.0384
 -11.000  -0.7030   0.02565   0.01985  -0.1060   0.8069   0.0387
 -10.750  -0.6795   0.02482   0.01891  -0.1062   0.8011   0.0390
 -10.500  -0.6557   0.02399   0.01797  -0.1065   0.7958   0.0393
 -10.250  -0.6311   0.02317   0.01706  -0.1067   0.7909   0.0396
 -10.000  -0.6061   0.02239   0.01618  -0.1070   0.7849   0.0399
  -9.750  -0.5808   0.02166   0.01535  -0.1071   0.7785   0.0402
  -9.500  -0.5551   0.02096   0.01455  -0.1073   0.7722   0.0405
  -9.250  -0.5288   0.02031   0.01380  -0.1074   0.7648   0.0408
  -9.000  -0.5025   0.01971   0.01310  -0.1076   0.7575   0.0410
  -8.750  -0.4755   0.01916   0.01246  -0.1077   0.7501   0.0413
  -8.500  -0.4488   0.01856   0.01178  -0.1078   0.7410   0.0415
  -8.250  -0.4221   0.01794   0.01113  -0.1079   0.7315   0.0418
  -8.000  -0.3950   0.01746   0.01060  -0.1080   0.7195   0.0421
  -7.750  -0.3675   0.01703   0.01012  -0.1081   0.7066   0.0425
  -7.500  -0.3400   0.01665   0.00966  -0.1082   0.6936   0.0429
  -7.000  -0.2845   0.01590   0.00876  -0.1084   0.6693   0.0436
  -6.750  -0.2567   0.01556   0.00833  -0.1085   0.6588   0.0439
  -6.500  -0.2286   0.01523   0.00792  -0.1086   0.6487   0.0443
  -6.250  -0.2004   0.01493   0.00753  -0.1087   0.6398   0.0447
  -6.000  -0.1719   0.01462   0.00717  -0.1088   0.6321   0.0451
  -5.750  -0.1434   0.01436   0.00683  -0.1089   0.6251   0.0455
  -5.500  -0.1147   0.01411   0.00653  -0.1091   0.6194   0.0459
  -5.250  -0.0857   0.01388   0.00624  -0.1093   0.6136   0.0462
  -5.000  -0.0572   0.01350   0.00585  -0.1095   0.6076   0.0467
  -4.500   0.0007   0.01301   0.00531  -0.1099   0.5975   0.0479
  -4.250   0.0300   0.01279   0.00508  -0.1101   0.5928   0.0485
  -4.000   0.0591   0.01260   0.00485  -0.1103   0.5878   0.0490
  -3.750   0.0883   0.01243   0.00464  -0.1104   0.5829   0.0496
  -3.500   0.1177   0.01227   0.00444  -0.1106   0.5788   0.0502
  -3.250   0.1472   0.01210   0.00426  -0.1108   0.5745   0.0508
  -3.000   0.1767   0.01198   0.00411  -0.1110   0.5698   0.0513
  -2.750   0.2060   0.01178   0.00389  -0.1112   0.5650   0.0521
  -2.500   0.2353   0.01164   0.00372  -0.1114   0.5603   0.0530
  -2.250   0.2649   0.01150   0.00358  -0.1117   0.5555   0.0540
  -2.000   0.2944   0.01140   0.00346  -0.1118   0.5503   0.0552
  -1.750   0.3238   0.01133   0.00336  -0.1120   0.5455   0.0563
  -1.500   0.3531   0.01127   0.00326  -0.1121   0.5411   0.0575
  -1.250   0.3828   0.01116   0.00316  -0.1123   0.5373   0.0592
  -1.000   0.4124   0.01108   0.00308  -0.1125   0.5329   0.0611
  -0.750   0.4419   0.01102   0.00301  -0.1127   0.5283   0.0640
  -0.500   0.4712   0.01090   0.00293  -0.1129   0.5239   0.0749
  -0.250   0.5007   0.01059   0.00289  -0.1133   0.5201   0.1509
   0.000   0.5303   0.01052   0.00289  -0.1136   0.5157   0.1702
   0.250   0.5597   0.01048   0.00290  -0.1138   0.5109   0.1859
   0.500   0.5890   0.01047   0.00291  -0.1139   0.5064   0.2010
   0.750   0.6181   0.01045   0.00294  -0.1141   0.5021   0.2199
   1.000   0.6476   0.01041   0.00298  -0.1143   0.4975   0.2415
   1.250   0.6769   0.01038   0.00303  -0.1145   0.4924   0.2679
   1.500   0.7059   0.01036   0.00309  -0.1146   0.4875   0.2959
   1.750   0.7348   0.01038   0.00316  -0.1148   0.4822   0.3217
   2.000   0.7640   0.01037   0.00322  -0.1149   0.4753   0.3482
   2.250   0.7925   0.01042   0.00330  -0.1150   0.4678   0.3729
   2.500   0.8213   0.01044   0.00338  -0.1151   0.4607   0.3975
   2.750   0.8498   0.01047   0.00348  -0.1152   0.4518   0.4262
   3.000   0.8781   0.01050   0.00360  -0.1153   0.4433   0.4681
   3.250   0.9064   0.01053   0.00374  -0.1153   0.4340   0.5175
   3.500   0.9345   0.01062   0.00388  -0.1153   0.4262   0.5506
   4.000   0.9898   0.01085   0.00416  -0.1152   0.4051   0.6015
   4.250   1.0166   0.01100   0.00434  -0.1150   0.3930   0.6332
   4.500   1.0432   0.01105   0.00456  -0.1148   0.3807   0.6980
   4.750   1.0667   0.01105   0.00481  -0.1138   0.3686   0.8123
   5.000   1.0838   0.01099   0.00494  -0.1113   0.3576   1.0000
   5.250   1.1104   0.01126   0.00515  -0.1111   0.3461   1.0000
   5.500   1.1362   0.01159   0.00540  -0.1109   0.3337   1.0000
   5.750   1.1614   0.01195   0.00567  -0.1105   0.3214   1.0000
   6.000   1.1871   0.01226   0.00593  -0.1102   0.3108   1.0000
   6.250   1.2122   0.01260   0.00622  -0.1098   0.3005   1.0000
   6.500   1.2361   0.01301   0.00654  -0.1093   0.2889   1.0000
   6.750   1.2607   0.01336   0.00685  -0.1089   0.2774   1.0000
   7.000   1.2835   0.01381   0.00722  -0.1082   0.2636   1.0000
   7.250   1.3052   0.01432   0.00764  -0.1075   0.2482   1.0000
   7.500   1.3256   0.01489   0.00811  -0.1065   0.2313   1.0000
   7.750   1.3434   0.01558   0.00868  -0.1052   0.2109   1.0000
   8.000   1.3578   0.01642   0.00937  -0.1035   0.1874   1.0000
   8.250   1.3657   0.01747   0.01025  -0.1009   0.1608   1.0000
   8.500   1.3542   0.01982   0.01223  -0.0965   0.1000   1.0000
   8.750   1.3564   0.02153   0.01380  -0.0941   0.0778   1.0000
   9.000   1.3687   0.02263   0.01489  -0.0928   0.0726   1.0000
   9.250   1.3812   0.02374   0.01600  -0.0916   0.0694   1.0000
   9.500   1.3945   0.02483   0.01712  -0.0906   0.0673   1.0000
   9.750   1.4079   0.02593   0.01825  -0.0896   0.0658   1.0000
  10.000   1.4203   0.02714   0.01948  -0.0886   0.0646   1.0000
  10.250   1.4317   0.02845   0.02083  -0.0876   0.0634   1.0000
  10.500   1.4418   0.02989   0.02229  -0.0866   0.0624   1.0000
  10.750   1.4510   0.03143   0.02387  -0.0856   0.0616   1.0000
  11.000   1.4589   0.03314   0.02562  -0.0846   0.0607   1.0000
  11.250   1.4684   0.03472   0.02726  -0.0838   0.0603   1.0000
  11.500   1.4771   0.03642   0.02900  -0.0830   0.0599   1.0000
  11.750   1.4848   0.03824   0.03088  -0.0822   0.0594   1.0000
  12.000   1.4916   0.04018   0.03289  -0.0815   0.0590   1.0000
  12.250   1.4974   0.04225   0.03502  -0.0808   0.0585   1.0000
  12.500   1.5024   0.04446   0.03729  -0.0802   0.0581   1.0000
  12.750   1.5068   0.04678   0.03968  -0.0797   0.0577   1.0000
  13.000   1.5105   0.04922   0.04218  -0.0792   0.0574   1.0000
  13.250   1.5136   0.05176   0.04479  -0.0788   0.0570   1.0000
  13.500   1.5158   0.05446   0.04755  -0.0784   0.0566   1.0000
  13.750   1.5171   0.05731   0.05046  -0.0781   0.0562   1.0000
  14.000   1.5179   0.06020   0.05342  -0.0779   0.0558   1.0000
  14.250   1.5177   0.06327   0.05655  -0.0777   0.0555   1.0000
  14.500   1.5165   0.06649   0.05984  -0.0775   0.0552   1.0000
  14.750   1.5154   0.06973   0.06315  -0.0775   0.0549   1.0000
  15.000   1.5130   0.07316   0.06665  -0.0774   0.0546   1.0000
  15.250   1.5100   0.07671   0.07026  -0.0775   0.0543   1.0000
  15.500   1.5074   0.08022   0.07385  -0.0776   0.0541   1.0000
  15.750   1.5061   0.08364   0.07733  -0.0778   0.0539   1.0000
  16.000   1.5069   0.08675   0.08052  -0.0779   0.0538   1.0000
  16.250   1.5067   0.09004   0.08389  -0.0782   0.0536   1.0000
  16.500   1.5074   0.09320   0.08712  -0.0784   0.0535   1.0000
<< Back to GOE 413 AIRFOIL (goe413-il)

Polar data table (+)

Polar graphs


<< Back to GOE 413 AIRFOIL (goe413-il)