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GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 417 AIRFOIL (goe417-il)
Reynolds number: 50,000
Max Cl/Cd: 38.36 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe417-il-50000.txt
Download as CSV file: xf-goe417-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 417 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3022   0.10690   0.10056  -0.0222   1.0000   0.0972
  -7.250  -0.3112   0.10712   0.10091  -0.0226   1.0000   0.0982
  -7.000  -0.3165   0.10754   0.10144  -0.0248   1.0000   0.0987
  -6.750  -0.3061   0.09996   0.09390  -0.0194   1.0000   0.1020
  -6.500  -0.3048   0.09740   0.09141  -0.0180   1.0000   0.1053
  -6.250  -0.3056   0.09564   0.08970  -0.0177   1.0000   0.1089
  -6.000  -0.3060   0.09505   0.08917  -0.0200   1.0000   0.1120
  -5.750  -0.3017   0.09431   0.08849  -0.0241   1.0000   0.1136
  -5.500  -0.3013   0.08899   0.08325  -0.0179   1.0000   0.1177
  -5.250  -0.2967   0.08691   0.08121  -0.0183   1.0000   0.1243
  -5.000  -0.2860   0.08552   0.07983  -0.0232   1.0000   0.1288
  -4.750  -0.2854   0.08169   0.07608  -0.0190   1.0000   0.1343
  -4.500  -0.2649   0.08081   0.07513  -0.0265   1.0000   0.1431
  -4.250  -0.2661   0.07660   0.07104  -0.0216   1.0000   0.1475
  -4.000  -0.2433   0.07502   0.06937  -0.0278   1.0000   0.1581
  -3.750  -0.2419   0.07131   0.06575  -0.0240   1.0000   0.1642
  -3.500  -0.2237   0.06878   0.06317  -0.0271   1.0000   0.1751
  -3.250  -0.2049   0.06632   0.06066  -0.0298   1.0000   0.1885
  -3.000  -0.1888   0.06365   0.05798  -0.0311   1.0000   0.2030
  -2.750  -0.1760   0.06087   0.05523  -0.0310   1.0000   0.2196
  -2.500  -0.1551   0.05862   0.05292  -0.0335   1.0000   0.2457
  -2.250  -0.1368   0.05631   0.05058  -0.0347   1.0000   0.2739
  -2.000  -0.1230   0.05358   0.04786  -0.0344   1.0000   0.3039
  -1.750  -0.1125   0.05091   0.04527  -0.0328   1.0000   0.3388
  -0.750  -0.0930   0.04091   0.03571  -0.0185   1.0000   0.5727
  -0.500  -0.0824   0.03874   0.03360  -0.0160   1.0000   0.6188
  -0.250  -0.0606   0.03693   0.03178  -0.0167   1.0000   0.6539
   0.000   0.0057   0.03508   0.02978  -0.0266   0.9874   0.6779
   0.250   0.2308   0.03852   0.03100  -0.0750   0.9605   0.3349
   0.500   0.3138   0.03805   0.02946  -0.0841   0.9434   0.2111
   0.750   0.3756   0.03697   0.02781  -0.0896   0.9270   0.1804
   1.000   0.4248   0.03623   0.02663  -0.0931   0.9079   0.1737
   1.250   0.4768   0.03546   0.02547  -0.0968   0.8887   0.1702
   1.500   0.5344   0.03454   0.02419  -0.1010   0.8710   0.1683
   1.750   0.5863   0.03371   0.02311  -0.1040   0.8518   0.1712
   2.000   0.6322   0.03288   0.02227  -0.1062   0.8312   0.1832
   2.250   0.6864   0.03168   0.02120  -0.1092   0.8133   0.2187
   2.500   0.7430   0.02905   0.01975  -0.1120   0.7971   1.0000
   2.750   0.7777   0.02894   0.01925  -0.1118   0.7743   1.0000
   3.000   0.8223   0.02829   0.01838  -0.1126   0.7551   1.0000
   3.250   0.8589   0.02795   0.01789  -0.1125   0.7343   1.0000
   3.500   0.8938   0.02766   0.01752  -0.1122   0.7133   1.0000
   3.750   0.9331   0.02712   0.01687  -0.1122   0.6948   1.0000
   4.000   0.9586   0.02743   0.01712  -0.1109   0.6724   1.0000
   4.250   0.9919   0.02728   0.01691  -0.1103   0.6529   1.0000
   4.500   1.0186   0.02756   0.01713  -0.1091   0.6319   1.0000
   4.750   1.0455   0.02785   0.01735  -0.1079   0.6110   1.0000
   5.000   1.0752   0.02803   0.01741  -0.1069   0.5916   1.0000
   5.250   1.0953   0.02886   0.01833  -0.1053   0.5708   1.0000
   5.500   1.1200   0.02944   0.01889  -0.1041   0.5517   1.0000
   5.750   1.1462   0.02998   0.01938  -0.1031   0.5337   1.0000
   6.000   1.1676   0.03089   0.02035  -0.1017   0.5157   1.0000
   6.250   1.1881   0.03188   0.02143  -0.1003   0.4976   1.0000
   6.500   1.2099   0.03288   0.02255  -0.0991   0.4806   1.0000
   6.750   1.2322   0.03389   0.02362  -0.0978   0.4639   1.0000
   7.000   1.2541   0.03501   0.02483  -0.0966   0.4481   1.0000
   7.250   1.2743   0.03637   0.02632  -0.0954   0.4334   1.0000
   7.500   1.2920   0.03809   0.02828  -0.0941   0.4204   1.0000
   7.750   1.3081   0.04005   0.03047  -0.0927   0.4089   1.0000
   8.000   1.3295   0.04174   0.03231  -0.0918   0.3991   1.0000
   8.250   1.3417   0.04404   0.03492  -0.0903   0.3894   1.0000
   8.500   1.3494   0.04682   0.03802  -0.0885   0.3811   1.0000
   8.750   1.3674   0.04886   0.04029  -0.0875   0.3735   1.0000
   9.000   1.3633   0.05284   0.04468  -0.0853   0.3680   1.0000
   9.250   1.3468   0.05788   0.05004  -0.0828   0.3634   1.0000
   9.500   1.3701   0.05934   0.05172  -0.0819   0.3554   1.0000
   9.750   1.3262   0.06739   0.05995  -0.0795   0.3556   1.0000
  10.000   1.2548   0.07824   0.07061  -0.0780   0.3569   1.0000
  10.250   1.4556   0.04171   0.03360  -0.0687   0.2272   1.0000
  10.500   1.4384   0.04241   0.03431  -0.0627   0.1978   1.0000
  10.750   1.4184   0.04425   0.03597  -0.0572   0.1703   1.0000
  11.000   1.4009   0.04716   0.03867  -0.0532   0.1457   1.0000
  11.250   1.3886   0.05050   0.04187  -0.0503   0.1274   1.0000
  11.500   1.3801   0.05385   0.04517  -0.0483   0.1144   1.0000
  11.750   1.3749   0.05710   0.04835  -0.0467   0.1048   1.0000
  12.000   1.3747   0.06060   0.05207  -0.0452   0.0971   1.0000
  12.250   1.3792   0.06363   0.05504  -0.0438   0.0911   1.0000
  12.500   1.3804   0.06743   0.05918  -0.0428   0.0869   1.0000
  12.750   1.3822   0.07076   0.06259  -0.0419   0.0828   1.0000
  13.000   1.3845   0.07448   0.06642  -0.0412   0.0794   1.0000
  13.250   1.3744   0.07954   0.07183  -0.0414   0.0781   1.0000
  13.500   1.3608   0.08516   0.07781  -0.0424   0.0772   1.0000
  13.750   1.3434   0.09157   0.08448  -0.0443   0.0771   1.0000
  14.000   1.3216   0.09899   0.09218  -0.0473   0.0778   1.0000
  14.250   1.2974   0.10736   0.10077  -0.0514   0.0787   1.0000
  14.500   1.2740   0.11626   0.10983  -0.0562   0.0798   1.0000
  14.750   1.1436   0.15793   0.15147  -0.0852   0.1021   1.0000
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