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GOE 506 AIRFOIL (goe506-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 506 AIRFOIL (goe506-il)
Reynolds number: 200,000
Max Cl/Cd: 48.36 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe506-il-200000-n5.txt
Download as CSV file: xf-goe506-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 506 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.3667   0.07224   0.06814  -0.1125   0.9630   0.0183
 -12.750  -0.3950   0.06280   0.05847  -0.1209   0.9578   0.0183
 -12.500  -0.4086   0.05592   0.05139  -0.1279   0.9531   0.0182
 -12.250  -0.4197   0.04903   0.04420  -0.1366   0.9495   0.0183
 -12.000  -0.4214   0.04553   0.04056  -0.1400   0.9441   0.0185
 -11.750  -0.4140   0.04330   0.03826  -0.1424   0.9394   0.0189
 -11.500  -0.4062   0.04066   0.03544  -0.1453   0.9357   0.0193
 -11.250  -0.4011   0.03871   0.03333  -0.1459   0.9307   0.0197
 -11.000  -0.4027   0.03708   0.03152  -0.1442   0.9234   0.0202
 -10.750  -0.3972   0.03508   0.02925  -0.1434   0.9190   0.0207
 -10.500  -0.3996   0.03374   0.02771  -0.1399   0.9120   0.0211
 -10.250  -0.3945   0.03209   0.02577  -0.1377   0.9066   0.0217
 -10.000  -0.3808   0.03040   0.02371  -0.1368   0.9032   0.0224
  -9.750  -0.3725   0.02929   0.02245  -0.1343   0.8980   0.0230
  -9.500  -0.3611   0.02844   0.02155  -0.1322   0.8927   0.0236
  -9.250  -0.3418   0.02761   0.02064  -0.1315   0.8893   0.0246
  -9.000  -0.3188   0.02658   0.01946  -0.1314   0.8868   0.0257
  -8.750  -0.3099   0.02591   0.01865  -0.1283   0.8809   0.0265
  -8.500  -0.2944   0.02512   0.01769  -0.1263   0.8762   0.0274
  -8.250  -0.2726   0.02417   0.01660  -0.1257   0.8733   0.0283
  -8.000  -0.2487   0.02314   0.01558  -0.1256   0.8711   0.0295
  -7.750  -0.2391   0.02269   0.01510  -0.1224   0.8651   0.0306
  -7.500  -0.2216   0.02208   0.01442  -0.1207   0.8603   0.0319
  -7.250  -0.1968   0.02132   0.01356  -0.1204   0.8570   0.0332
  -7.000  -0.1681   0.02068   0.01279  -0.1207   0.8547   0.0345
  -6.750  -0.1667   0.02018   0.01231  -0.1159   0.8471   0.0357
  -6.500  -0.1467   0.01952   0.01164  -0.1146   0.8432   0.0371
  -6.250  -0.1203   0.01887   0.01091  -0.1146   0.8402   0.0387
  -6.000  -0.1099   0.01858   0.01057  -0.1112   0.8336   0.0399
  -5.750  -0.0891   0.01817   0.01007  -0.1098   0.8288   0.0417
  -5.500  -0.0614   0.01751   0.00933  -0.1099   0.8251   0.0437
  -5.250  -0.0495   0.01723   0.00899  -0.1067   0.8182   0.0454
  -5.000  -0.0271   0.01685   0.00853  -0.1056   0.8134   0.0476
  -4.750   0.0024   0.01643   0.00800  -0.1059   0.8101   0.0511
  -4.500   0.0172   0.01616   0.00773  -0.1033   0.8039   0.0551
  -4.250   0.0396   0.01576   0.00731  -0.1021   0.7980   0.0633
  -4.000   0.0640   0.01471   0.00673  -0.1018   0.7934   0.1627
  -3.750   0.0774   0.01460   0.00669  -0.0989   0.7851   0.2020
  -3.500   0.1071   0.01435   0.00643  -0.0991   0.7802   0.2248
  -3.250   0.1282   0.01425   0.00633  -0.0977   0.7747   0.2403
  -3.000   0.1503   0.01416   0.00618  -0.0965   0.7685   0.2489
  -2.750   0.1816   0.01393   0.00592  -0.0971   0.7639   0.2593
  -2.500   0.1989   0.01389   0.00587  -0.0949   0.7570   0.2683
  -2.250   0.2257   0.01371   0.00567  -0.0946   0.7503   0.2796
  -2.000   0.2478   0.01358   0.00555  -0.0934   0.7428   0.2912
  -1.750   0.2728   0.01343   0.00539  -0.0927   0.7347   0.3041
  -1.500   0.2937   0.01332   0.00528  -0.0913   0.7256   0.3185
  -1.250   0.3205   0.01314   0.00511  -0.0910   0.7165   0.3362
  -1.000   0.3370   0.01305   0.00505  -0.0886   0.7051   0.3531
  -0.750   0.3551   0.01293   0.00494  -0.0865   0.6908   0.3708
  -0.500   0.3717   0.01283   0.00484  -0.0841   0.6732   0.3905
  -0.250   0.3865   0.01274   0.00473  -0.0813   0.6478   0.4129
   0.000   0.4010   0.01267   0.00454  -0.0784   0.5955   0.4396
   0.250   0.4026   0.01294   0.00446  -0.0729   0.5347   0.4672
   0.500   0.4063   0.01321   0.00465  -0.0682   0.5034   0.5047
   0.750   0.4140   0.01335   0.00485  -0.0643   0.4821   0.5630
   1.000   0.4225   0.01339   0.00509  -0.0605   0.4631   0.6464
   1.250   0.4414   0.01336   0.00539  -0.0587   0.4451   0.7711
   1.500   0.5613   0.01398   0.00606  -0.0786   0.4146   0.9344
   1.750   0.6071   0.01441   0.00635  -0.0828   0.3988   0.9756
   2.000   0.6417   0.01485   0.00666  -0.0847   0.3878   0.9980
   2.250   0.6585   0.01515   0.00685  -0.0829   0.3802   1.0000
   2.500   0.6717   0.01538   0.00700  -0.0803   0.3730   1.0000
   2.750   0.6849   0.01565   0.00717  -0.0777   0.3671   1.0000
   3.000   0.7000   0.01591   0.00736  -0.0755   0.3617   1.0000
   3.250   0.7159   0.01616   0.00755  -0.0735   0.3563   1.0000
   3.500   0.7313   0.01646   0.00777  -0.0714   0.3515   1.0000
   3.750   0.7477   0.01675   0.00800  -0.0695   0.3471   1.0000
   4.000   0.7657   0.01700   0.00822  -0.0679   0.3428   1.0000
   4.250   0.7835   0.01729   0.00846  -0.0664   0.3387   1.0000
   4.500   0.8011   0.01760   0.00872  -0.0648   0.3354   1.0000
   4.750   0.8189   0.01792   0.00899  -0.0633   0.3326   1.0000
   5.000   0.8386   0.01819   0.00925  -0.0621   0.3299   1.0000
   5.250   0.8585   0.01846   0.00953  -0.0609   0.3272   1.0000
   5.500   0.8782   0.01875   0.00982  -0.0598   0.3247   1.0000
   5.750   0.8975   0.01906   0.01012  -0.0586   0.3218   1.0000
   6.000   0.9166   0.01939   0.01044  -0.0574   0.3192   1.0000
   6.250   0.9361   0.01973   0.01076  -0.0563   0.3171   1.0000
   6.500   0.9556   0.02010   0.01109  -0.0552   0.3148   1.0000
   6.750   0.9761   0.02039   0.01144  -0.0543   0.3126   1.0000
   7.000   0.9965   0.02070   0.01180  -0.0534   0.3102   1.0000
   7.250   1.0162   0.02104   0.01217  -0.0524   0.3074   1.0000
   7.500   1.0348   0.02141   0.01256  -0.0513   0.3040   1.0000
   7.750   1.0531   0.02182   0.01298  -0.0501   0.3010   1.0000
   8.000   1.0717   0.02225   0.01340  -0.0490   0.2985   1.0000
   8.250   1.0915   0.02261   0.01383  -0.0482   0.2961   1.0000
   8.500   1.1112   0.02298   0.01428  -0.0473   0.2935   1.0000
   8.750   1.1298   0.02339   0.01477  -0.0463   0.2904   1.0000
   9.000   1.1478   0.02383   0.01526  -0.0452   0.2874   1.0000
   9.250   1.1642   0.02434   0.01579  -0.0440   0.2838   1.0000
   9.500   1.1814   0.02483   0.01633  -0.0429   0.2804   1.0000
   9.750   1.1986   0.02531   0.01694  -0.0418   0.2758   1.0000
  10.000   1.2112   0.02595   0.01761  -0.0402   0.2687   1.0000
  10.250   1.2259   0.02655   0.01828  -0.0389   0.2617   1.0000
  10.500   1.2371   0.02730   0.01906  -0.0372   0.2521   1.0000
  10.750   1.2485   0.02810   0.01990  -0.0357   0.2372   1.0000
  11.000   1.2584   0.02903   0.02082  -0.0341   0.2188   1.0000
  11.250   1.2625   0.03034   0.02202  -0.0320   0.1978   1.0000
  11.500   1.2635   0.03197   0.02352  -0.0298   0.1831   1.0000
  12.000   1.2747   0.03484   0.02639  -0.0265   0.1703   1.0000
  12.250   1.2748   0.03675   0.02829  -0.0246   0.1629   1.0000
  12.500   1.2824   0.03815   0.02977  -0.0233   0.1592   1.0000
  12.750   1.2877   0.03978   0.03147  -0.0220   0.1532   1.0000
  13.000   1.2903   0.04168   0.03342  -0.0206   0.1488   1.0000
  13.250   1.2955   0.04342   0.03524  -0.0195   0.1429   1.0000
  13.500   1.2965   0.04559   0.03745  -0.0184   0.1329   1.0000
  13.750   1.3037   0.04728   0.03922  -0.0176   0.1150   1.0000
  14.000   1.2810   0.05191   0.04359  -0.0160   0.0766   1.0000
  14.750   1.2216   0.06674   0.05837  -0.0140   0.0261   1.0000
  15.000   1.2130   0.07087   0.06262  -0.0142   0.0238   1.0000
  15.250   1.2045   0.07516   0.06703  -0.0146   0.0219   1.0000
  15.500   1.1952   0.07965   0.07165  -0.0153   0.0208   1.0000
  15.750   1.1856   0.08428   0.07642  -0.0161   0.0201   1.0000
  16.000   1.1763   0.08892   0.08119  -0.0170   0.0194   1.0000
  16.250   1.1683   0.09342   0.08584  -0.0180   0.0188   1.0000
  16.500   1.1585   0.09828   0.09084  -0.0191   0.0183   1.0000
  16.750   1.1494   0.10307   0.09577  -0.0204   0.0180   1.0000
  17.000   1.1392   0.10809   0.10093  -0.0218   0.0177   1.0000
  17.250   1.1275   0.11341   0.10638  -0.0234   0.0171   1.0000
  17.500   1.1182   0.11843   0.11153  -0.0250   0.0170   1.0000
  17.750   1.1078   0.12369   0.11691  -0.0268   0.0167   1.0000
  18.000   1.0974   0.12899   0.12233  -0.0287   0.0164   1.0000
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