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GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 54 AIRFOIL (goe54-il)
Reynolds number: 50,000
Max Cl/Cd: 29.29 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe54-il-50000-n5.txt
Download as CSV file: xf-goe54-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 54 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5473   0.12435   0.11754   0.0378   1.0000   0.0611
  -9.000  -0.5456   0.12192   0.11517   0.0346   1.0000   0.0630
  -8.750  -0.5470   0.12011   0.11344   0.0299   1.0000   0.0637
  -8.500  -0.5311   0.11423   0.10758   0.0329   1.0000   0.0665
  -8.250  -0.5248   0.11096   0.10436   0.0314   1.0000   0.0692
  -8.000  -0.5216   0.10825   0.10171   0.0281   1.0000   0.0715
  -7.750  -0.5167   0.10595   0.09946   0.0199   1.0000   0.0728
  -7.500  -0.5062   0.10090   0.09449   0.0226   1.0000   0.0747
  -7.250  -0.4955   0.09714   0.09074   0.0220   1.0000   0.0778
  -7.000  -0.4838   0.09377   0.08739   0.0170   1.0000   0.0820
  -6.750  -0.4688   0.09016   0.08377   0.0088   1.0000   0.0849
  -6.500  -0.4587   0.08607   0.07977   0.0120   1.0000   0.0896
  -6.000  -0.4272   0.07858   0.07230   0.0048   1.0000   0.1011
  -5.750  -0.4013   0.07547   0.06900  -0.0045   1.0000   0.1102
  -5.500  -0.3907   0.07124   0.06492  -0.0014   1.0000   0.1149
  -5.000  -0.3463   0.06434   0.05788  -0.0095   1.0000   0.1395
  -4.750  -0.3281   0.06094   0.05452  -0.0104   1.0000   0.1558
  -4.500  -0.3116   0.05781   0.05148  -0.0102   1.0000   0.1766
  -4.250  -0.2943   0.05489   0.04862  -0.0106   1.0000   0.2096
  -3.750  -0.2694   0.04955   0.04363  -0.0067   1.0000   0.3062
  -3.500  -0.2557   0.04732   0.04154  -0.0046   1.0000   0.3641
  -3.250  -0.2456   0.04474   0.03919   0.0000   1.0000   0.4125
  -3.000  -0.2336   0.04216   0.03683   0.0041   1.0000   0.4561
  -2.750  -0.2056   0.03943   0.03417   0.0021   1.0000   0.4787
  -2.250  -0.0057   0.03330   0.02480  -0.0340   0.7557   0.1340
  -2.000   0.0255   0.03238   0.02294  -0.0327   0.6850   0.1115
  -1.750   0.0535   0.03115   0.02121  -0.0319   0.6394   0.1013
  -1.500   0.0836   0.03045   0.01991  -0.0313   0.6052   0.0949
  -1.250   0.1120   0.02933   0.01843  -0.0310   0.5779   0.0932
  -1.000   0.1407   0.02840   0.01711  -0.0306   0.5556   0.0903
  -0.750   0.1708   0.02782   0.01607  -0.0301   0.5353   0.0858
  -0.500   0.1999   0.02730   0.01521  -0.0296   0.5167   0.0831
  -0.250   0.2282   0.02655   0.01425  -0.0292   0.4993   0.0815
   0.000   0.2564   0.02599   0.01347  -0.0287   0.4830   0.0800
   0.250   0.2844   0.02554   0.01284  -0.0280   0.4680   0.0794
   0.500   0.3126   0.02523   0.01232  -0.0274   0.4542   0.0806
   0.750   0.3407   0.02498   0.01188  -0.0269   0.4409   0.0818
   1.000   0.3689   0.02473   0.01155  -0.0264   0.4271   0.0819
   1.250   0.3967   0.02455   0.01129  -0.0259   0.4145   0.0818
   1.500   0.4243   0.02448   0.01110  -0.0255   0.4038   0.0819
   1.750   0.4521   0.02448   0.01102  -0.0252   0.3935   0.0824
   2.000   0.4802   0.02458   0.01107  -0.0250   0.3833   0.0835
   2.250   0.5080   0.02462   0.01099  -0.0248   0.3749   0.0871
   2.500   0.5367   0.02481   0.01122  -0.0249   0.3646   0.0918
   2.750   0.5646   0.02507   0.01136  -0.0247   0.3572   0.0952
   3.000   0.5930   0.02538   0.01173  -0.0247   0.3483   0.0992
   3.250   0.6209   0.02568   0.01198  -0.0246   0.3407   0.1066
   3.500   0.6459   0.02470   0.01252  -0.0244   0.3324   0.6201
   4.000   0.6983   0.02524   0.01328  -0.0231   0.3165   1.0000
   4.250   0.7251   0.02581   0.01374  -0.0228   0.3091   1.0000
   4.500   0.7519   0.02644   0.01435  -0.0226   0.3012   1.0000
   4.750   0.7783   0.02704   0.01486  -0.0223   0.2945   1.0000
   5.000   0.8047   0.02785   0.01573  -0.0223   0.2868   1.0000
   5.250   0.8308   0.02836   0.01609  -0.0218   0.2815   1.0000
   5.500   0.8567   0.02948   0.01745  -0.0221   0.2735   1.0000
   5.750   0.8824   0.03025   0.01820  -0.0218   0.2679   1.0000
   6.000   0.9078   0.03123   0.01922  -0.0216   0.2631   1.0000
   6.250   0.9324   0.03275   0.02105  -0.0219   0.2567   1.0000
   6.500   0.9572   0.03373   0.02209  -0.0217   0.2517   1.0000
   6.750   0.9819   0.03469   0.02305  -0.0214   0.2473   1.0000
   7.000   1.0039   0.03676   0.02554  -0.0219   0.2402   1.0000
   7.250   1.0274   0.03797   0.02689  -0.0217   0.2354   1.0000
   7.500   1.0516   0.03894   0.02787  -0.0213   0.2321   1.0000
   7.750   1.0687   0.04227   0.03174  -0.0224   0.2267   1.0000
   8.000   1.0862   0.04505   0.03487  -0.0230   0.2220   1.0000
   8.250   1.1068   0.04663   0.03662  -0.0228   0.2180   1.0000
   8.500   1.1306   0.04735   0.03732  -0.0219   0.2147   1.0000
   8.750   1.1254   0.05474   0.04549  -0.0256   0.2078   1.0000
   9.000   1.1389   0.05719   0.04813  -0.0259   0.2028   1.0000
   9.250   1.1695   0.05563   0.04651  -0.0234   0.1979   1.0000
   9.500   1.1248   0.06879   0.06026  -0.0319   0.1895   1.0000
   9.750   1.1960   0.05884   0.05010  -0.0233   0.1836   1.0000
  10.000   1.0607   0.08997   0.08154  -0.0477   0.1774   1.0000
  10.250   1.0669   0.09238   0.08401  -0.0480   0.1718   1.0000
  10.500   1.0559   0.09833   0.08996  -0.0511   0.1666   1.0000
  10.750   1.0353   0.10623   0.09787  -0.0557   0.1605   1.0000
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