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GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 123 AIRFOIL (goe123-il)
Reynolds number: 500,000
Max Cl/Cd: 118.76 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe123-il-500000.txt
Download as CSV file: xf-goe123-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 123 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3096   0.10035   0.09814  -0.0270   1.0000   0.0162
  -8.250  -0.3030   0.09762   0.09545  -0.0273   1.0000   0.0164
  -8.000  -0.3073   0.09622   0.09409  -0.0254   1.0000   0.0166
  -7.750  -0.2939   0.09324   0.09112  -0.0284   0.9964   0.0171
  -7.500  -0.2739   0.08956   0.08743  -0.0334   0.9919   0.0178
  -7.250  -0.2514   0.08560   0.08346  -0.0393   0.9866   0.0186
  -7.000  -0.2194   0.08140   0.07923  -0.0498   0.9805   0.0197
  -6.750  -0.1847   0.07711   0.07490  -0.0622   0.9723   0.0198
  -6.500  -0.1563   0.07296   0.07069  -0.0698   0.9645   0.0199
  -6.250  -0.1473   0.06857   0.06630  -0.0689   0.9582   0.0202
  -6.000  -0.1337   0.06584   0.06356  -0.0690   0.9515   0.0206
  -5.750  -0.1156   0.06318   0.06087  -0.0711   0.9437   0.0211
  -5.500  -0.0944   0.06033   0.05797  -0.0742   0.9361   0.0218
  -5.250  -0.0711   0.05734   0.05492  -0.0776   0.9282   0.0229
  -5.000  -0.0255   0.05401   0.05141  -0.0868   0.9197   0.0247
  -4.750   0.0066   0.05079   0.04804  -0.0910   0.9123   0.0248
  -4.500   0.0272   0.04603   0.04322  -0.0936   0.9053   0.0253
  -4.250   0.0465   0.04365   0.04080  -0.0941   0.8992   0.0257
  -4.000   0.0702   0.04145   0.03854  -0.0954   0.8939   0.0264
  -3.750   0.0978   0.03917   0.03617  -0.0975   0.8876   0.0274
  -3.500   0.1279   0.03679   0.03367  -0.0996   0.8824   0.0289
  -3.250   0.1723   0.03492   0.03153  -0.1029   0.8771   0.0313
  -3.000   0.2022   0.03044   0.02685  -0.1055   0.8712   0.0320
  -2.750   0.2257   0.02858   0.02492  -0.1061   0.8656   0.0327
  -2.500   0.2517   0.02707   0.02335  -0.1067   0.8574   0.0337
  -2.250   0.2792   0.02554   0.02168  -0.1072   0.8498   0.0351
  -2.000   0.3095   0.02388   0.01986  -0.1078   0.8410   0.0376
  -1.750   0.3444   0.02121   0.01680  -0.1086   0.8350   0.0410
  -1.500   0.3707   0.01998   0.01553  -0.1091   0.8275   0.0421
  -1.250   0.3978   0.01904   0.01450  -0.1094   0.8213   0.0438
  -1.000   0.4271   0.01804   0.01337  -0.1096   0.8140   0.0480
  -0.750   0.4573   0.01642   0.01148  -0.1099   0.8077   0.0530
  -0.500   0.4845   0.01578   0.01081  -0.1100   0.7999   0.0556
  -0.250   0.5140   0.01641   0.01123  -0.1093   0.7922   0.0629
   0.000  -0.5859   0.07804   0.07523   0.1106   0.8724   0.0700
   0.500   0.6025   0.01031   0.00432  -0.1095   0.7683   0.0434
   0.750   0.6304   0.00976   0.00361  -0.1092   0.7591   0.0413
   1.000   0.6580   0.00935   0.00313  -0.1089   0.7483   0.0412
   1.250   0.6853   0.00900   0.00274  -0.1087   0.7348   0.0416
   1.500   0.7123   0.00878   0.00244  -0.1083   0.7177   0.0421
   1.750   0.7394   0.00862   0.00226  -0.1081   0.6986   0.0442
   2.000   0.7666   0.00853   0.00213  -0.1079   0.6796   0.0450
   2.250   0.7938   0.00850   0.00203  -0.1076   0.6609   0.0460
   2.500   0.8208   0.00851   0.00198  -0.1074   0.6394   0.0481
   2.750   0.8473   0.00860   0.00197  -0.1070   0.6127   0.0523
   3.000   0.8734   0.00869   0.00209  -0.1067   0.5803   0.1079
   3.250   0.8991   0.00890   0.00224  -0.1063   0.5492   0.1534
   3.500   0.9250   0.00899   0.00242  -0.1061   0.5212   0.2646
   3.750   0.9453   0.00796   0.00263  -0.1048   0.4966   1.0000
   4.000   0.9711   0.00825   0.00280  -0.1044   0.4713   1.0000
   4.250   0.9968   0.00855   0.00298  -0.1041   0.4461   1.0000
   4.500   1.0220   0.00889   0.00318  -0.1037   0.4169   1.0000
   4.750   1.0467   0.00928   0.00340  -0.1033   0.3853   1.0000
   5.000   1.0716   0.00966   0.00366  -0.1029   0.3600   1.0000
   5.250   1.0966   0.01001   0.00391  -0.1025   0.3380   1.0000
   5.750   1.1464   0.01072   0.00446  -0.1017   0.2993   1.0000
   6.000   1.1712   0.01107   0.00475  -0.1013   0.2793   1.0000
   6.250   1.1954   0.01148   0.00506  -0.1008   0.2562   1.0000
   6.500   1.2192   0.01192   0.00539  -0.1003   0.2294   1.0000
   6.750   1.2414   0.01255   0.00581  -0.0996   0.1893   1.0000
   7.000   1.2610   0.01347   0.00643  -0.0986   0.1354   1.0000
   7.250   1.2759   0.01498   0.00747  -0.0969   0.0612   1.0000
   7.500   1.2940   0.01610   0.00839  -0.0956   0.0336   1.0000
   7.750   1.3132   0.01705   0.00938  -0.0942   0.0280   1.0000
   8.000   1.3342   0.01771   0.01013  -0.0932   0.0258   1.0000
   8.250   1.3541   0.01845   0.01096  -0.0921   0.0237   1.0000
   8.500   1.3717   0.01941   0.01197  -0.0906   0.0220   1.0000
   8.750   1.3819   0.02102   0.01370  -0.0881   0.0203   1.0000
   9.000   1.4014   0.02163   0.01438  -0.0869   0.0194   1.0000
   9.250   1.4182   0.02244   0.01528  -0.0854   0.0183   1.0000
   9.500   1.4326   0.02341   0.01632  -0.0835   0.0174   1.0000
   9.750   1.4441   0.02444   0.01741  -0.0813   0.0166   1.0000
  10.000   1.4513   0.02570   0.01874  -0.0784   0.0160   1.0000
  10.250   1.4519   0.02762   0.02074  -0.0749   0.0154   1.0000
  10.500   1.4532   0.02979   0.02302  -0.0716   0.0150   1.0000
  10.750   1.4641   0.03093   0.02427  -0.0697   0.0147   1.0000
  11.000   1.4738   0.03220   0.02567  -0.0678   0.0142   1.0000
  11.250   1.4825   0.03362   0.02720  -0.0658   0.0137   1.0000
  11.500   1.4903   0.03514   0.02882  -0.0640   0.0132   1.0000
  11.750   1.4971   0.03681   0.03059  -0.0622   0.0127   1.0000
  12.000   1.5028   0.03862   0.03249  -0.0604   0.0124   1.0000
  12.250   1.5078   0.04056   0.03453  -0.0587   0.0121   1.0000
  12.500   1.5116   0.04266   0.03673  -0.0570   0.0118   1.0000
  12.750   1.5142   0.04511   0.03928  -0.0553   0.0116   1.0000
  13.000   1.5151   0.04822   0.04252  -0.0534   0.0113   1.0000
  13.500   1.5067   0.05565   0.05040  -0.0497   0.0110   1.0000
  13.750   1.5004   0.05884   0.05380  -0.0487   0.0109   1.0000
  14.000   1.4925   0.06251   0.05767  -0.0480   0.0109   1.0000
  14.250   1.4826   0.06658   0.06195  -0.0477   0.0108   1.0000
  14.500   1.4705   0.07111   0.06669  -0.0478   0.0108   1.0000
  14.750   1.4569   0.07607   0.07185  -0.0484   0.0107   1.0000
  15.000   1.4420   0.08145   0.07743  -0.0496   0.0107   1.0000
  15.250   1.4262   0.08736   0.08354  -0.0514   0.0106   1.0000
  15.500   1.4096   0.09377   0.09014  -0.0538   0.0106   1.0000
  15.750   1.3922   0.10069   0.09725  -0.0570   0.0106   1.0000
  16.000   1.3744   0.10808   0.10481  -0.0607   0.0106   1.0000
  16.250   1.3553   0.11616   0.11307  -0.0651   0.0107   1.0000
  16.500   1.3368   0.12448   0.12156  -0.0700   0.0107   1.0000
  16.750   1.3175   0.13338   0.13062  -0.0754   0.0108   1.0000
  17.000   1.2975   0.14290   0.14027  -0.0813   0.0109   1.0000
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