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GOE 646 AIRFOIL (goe646-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 646 AIRFOIL (goe646-il)
Reynolds number: 50,000
Max Cl/Cd: 5.16 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe646-il-50000.txt
Download as CSV file: xf-goe646-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 646 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2639   0.13891   0.13151  -0.0273   1.0000   0.2868
 -10.500  -0.2755   0.13835   0.13102  -0.0257   1.0000   0.2939
 -10.250  -0.3176   0.14086   0.13367  -0.0240   1.0000   0.2969
 -10.000  -0.2812   0.13405   0.12685  -0.0227   1.0000   0.3021
  -9.750  -0.2804   0.13231   0.12515  -0.0209   1.0000   0.3091
  -9.500  -0.3101   0.13327   0.12623  -0.0191   1.0000   0.3153
  -9.250  -0.3196   0.13109   0.12413  -0.0176   1.0000   0.3179
  -9.000  -0.2971   0.12730   0.12034  -0.0159   1.0000   0.3248
  -8.750  -0.3131   0.12694   0.12006  -0.0139   1.0000   0.3333
  -8.500  -0.3569   0.12857   0.12183  -0.0115   1.0000   0.3361
  -8.250  -0.3234   0.12300   0.11625  -0.0104   1.0000   0.3420
  -8.000  -0.3269   0.12177   0.11508  -0.0083   1.0000   0.3505
  -7.750  -0.3698   0.12305   0.11649  -0.0057   1.0000   0.3560
  -7.500  -0.3589   0.11935   0.11283  -0.0044   1.0000   0.3603
  -7.250  -0.3511   0.11742   0.11092  -0.0026   1.0000   0.3687
  -7.000  -0.3867   0.11788   0.11149   0.0002   1.0000   0.3760
  -6.750  -0.4348   0.11843   0.11217   0.0033   1.0000   0.3776
  -6.500  -0.5661   0.09727   0.09102  -0.0092   1.0000   0.2602
  -6.250  -0.5795   0.09299   0.08672  -0.0095   1.0000   0.2587
  -6.000  -0.5956   0.08773   0.08144  -0.0109   1.0000   0.2580
  -5.750  -0.6140   0.08048   0.07409  -0.0148   1.0000   0.2575
  -5.500  -0.6358   0.06772   0.06087  -0.0249   1.0000   0.2600
  -5.000  -0.5984   0.06167   0.05435  -0.0312   0.9923   0.2780
  -4.750  -0.5536   0.06546   0.05843  -0.0299   0.9786   0.2875
  -4.500  -0.5399   0.05979   0.05230  -0.0356   0.9742   0.2990
  -4.250  -0.5839   0.05674   0.04922  -0.0263   1.0000   0.2988
  -4.000  -0.5715   0.05717   0.04977  -0.0237   1.0000   0.3059
  -3.750  -0.5553   0.05417   0.04640  -0.0261   1.0000   0.3188
  -3.500  -0.5421   0.05424   0.04655  -0.0242   1.0000   0.3275
  -3.250  -0.5256   0.05253   0.04461  -0.0251   1.0000   0.3403
  -3.000  -0.5098   0.05184   0.04378  -0.0248   1.0000   0.3531
  -2.750  -0.4954   0.05144   0.04339  -0.0237   1.0000   0.3638
  -2.500  -0.4773   0.05035   0.04202  -0.0246   1.0000   0.3793
  -2.250  -0.4640   0.05054   0.04232  -0.0227   1.0000   0.3895
  -2.000  -0.4473   0.04997   0.04162  -0.0227   1.0000   0.4035
  -1.750  -0.4298   0.04965   0.04111  -0.0228   1.0000   0.4186
  -1.500  -0.4166   0.04978   0.04137  -0.0210   1.0000   0.4292
  -1.250  -0.3991   0.04949   0.04091  -0.0212   1.0000   0.4442
  -1.000  -0.3844   0.04966   0.04111  -0.0200   1.0000   0.4565
  -0.750  -0.3651   0.04986   0.04126  -0.0201   0.9986   0.4694
  -0.500  -0.3328   0.05102   0.04225  -0.0227   0.9928   0.4863
  -0.250  -0.3096   0.05173   0.04298  -0.0232   0.9864   0.4990
   0.000  -0.2780   0.05327   0.04445  -0.0253   0.9794   0.5137
   0.250  -0.2484   0.05406   0.04512  -0.0275   0.9689   0.5291
   0.500  -0.2259   0.05484   0.04592  -0.0281   0.9600   0.5416
   0.750  -0.1957   0.05633   0.04736  -0.0300   0.9506   0.5564
   1.000  -0.1607   0.05804   0.04899  -0.0328   0.9373   0.5729
   1.250  -0.1433   0.05827   0.04923  -0.0326   0.9251   0.5862
   1.500  -0.1213   0.05927   0.05023  -0.0332   0.9144   0.5998
   1.750  -0.0861   0.06140   0.05231  -0.0358   0.9023   0.6182
   2.000  -0.0585   0.06241   0.05328  -0.0373   0.8864   0.6355
   2.250  -0.0446   0.06290   0.05376  -0.0369   0.8747   0.6506
   2.500  -0.0111   0.06505   0.05589  -0.0393   0.8640   0.6720
   2.750   0.0262   0.06694   0.05779  -0.0419   0.8461   0.6962
   3.000   0.0290   0.06673   0.05763  -0.0403   0.8355   0.7138
   3.250   0.1533   0.06447   0.05546  -0.0461   0.7250   0.7836
   3.500   0.2026   0.06476   0.05615  -0.0491   0.7097   0.8611
   3.750   0.2784   0.06595   0.05724  -0.0602   0.6919   1.0000
   4.000   0.2693   0.06792   0.05906  -0.0596   0.6829   1.0000
   4.250   0.3105   0.06940   0.06025  -0.0627   0.6700   1.0000
   4.500   0.3154   0.07132   0.06206  -0.0624   0.6610   1.0000
   4.750   0.3436   0.07291   0.06348  -0.0634   0.6494   1.0000
   5.000   0.3467   0.07516   0.06567  -0.0630   0.6431   1.0000
   5.250   0.3790   0.07666   0.06703  -0.0641   0.6308   1.0000
   5.500   0.3762   0.07917   0.06951  -0.0633   0.6258   1.0000
   5.750   0.4152   0.08050   0.07072  -0.0645   0.6125   1.0000
   6.000   0.4077   0.08340   0.07361  -0.0637   0.6096   1.0000
   6.250   0.4080   0.08620   0.07640  -0.0635   0.6075   1.0000
   6.500   0.4130   0.08945   0.07963  -0.0640   0.6101   1.0000
   6.750   0.4316   0.09306   0.08322  -0.0655   0.6137   1.0000
   7.000   0.4487   0.09403   0.08414  -0.0647   0.5929   1.0000
   7.250   0.4753   0.09514   0.08519  -0.0645   0.5735   1.0000
   7.500   0.4901   0.09879   0.08884  -0.0657   0.5759   1.0000
   7.750   0.5143   0.09971   0.08971  -0.0651   0.5555   1.0000
   8.000   0.4334   0.10761   0.09780  -0.0659   0.6195   1.0000
   8.250   0.4571   0.11128   0.10144  -0.0672   0.6133   1.0000
   8.500   0.4548   0.11246   0.10262  -0.0662   0.6014   1.0000
   8.750   0.4948   0.11718   0.10732  -0.0685   0.5948   1.0000
   9.000   0.4756   0.11746   0.10762  -0.0666   0.5842   1.0000
   9.250   0.5137   0.12166   0.11180  -0.0684   0.5764   1.0000
   9.500   0.5018   0.12324   0.11339  -0.0676   0.5713   1.0000
   9.750   0.5119   0.12536   0.11552  -0.0678   0.5616   1.0000
  10.000   0.5542   0.13079   0.12095  -0.0699   0.5560   1.0000
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