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GOE 438 AIRFOIL (goe438-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 438 AIRFOIL (goe438-il)
Reynolds number: 200,000
Max Cl/Cd: 68.39 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe438-il-200000.txt
Download as CSV file: xf-goe438-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 438 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3625   0.09920   0.09554  -0.0394   1.0000   0.0654
  -9.250  -0.3830   0.09629   0.09272  -0.0427   1.0000   0.0658
  -9.000  -0.4074   0.09351   0.09004  -0.0439   1.0000   0.0659
  -8.750  -0.3656   0.08898   0.08545  -0.0376   1.0000   0.0678
  -8.500  -0.3614   0.08694   0.08343  -0.0358   1.0000   0.0690
  -8.250  -0.3654   0.08492   0.08147  -0.0342   1.0000   0.0702
  -8.000  -0.3769   0.08309   0.07972  -0.0322   1.0000   0.0716
  -7.750  -0.3986   0.08174   0.07846  -0.0290   1.0000   0.0724
  -7.500  -0.4216   0.08019   0.07699  -0.0264   1.0000   0.0732
  -7.250  -0.4412   0.07778   0.07462  -0.0259   1.0000   0.0749
  -7.000  -0.4341   0.06707   0.06366  -0.0430   0.9926   0.0793
  -6.750  -0.4097   0.06514   0.06177  -0.0427   0.9888   0.0809
  -6.500  -0.3816   0.06219   0.05879  -0.0460   0.9844   0.0840
  -6.250  -0.3587   0.05412   0.05021  -0.0571   0.9746   0.0932
  -6.000  -0.3279   0.05178   0.04795  -0.0589   0.9713   0.0952
  -5.750  -0.3017   0.04949   0.04560  -0.0607   0.9648   0.0991
  -5.500  -0.2716   0.04470   0.04038  -0.0662   0.9581   0.1089
  -5.250  -0.2393   0.04254   0.03825  -0.0684   0.9538   0.1121
  -5.000  -0.2120   0.03959   0.03484  -0.0710   0.9449   0.1237
  -4.750  -0.1743   0.03734   0.03268  -0.0739   0.9418   0.1276
  -4.500  -0.1467   0.03519   0.03017  -0.0753   0.9325   0.1399
  -4.250  -0.1080   0.03297   0.02799  -0.0781   0.9284   0.1448
  -4.000  -0.0668   0.03077   0.02559  -0.0817   0.9252   0.1585
  -3.750  -0.0384   0.02488   0.01848  -0.0806   0.9145   0.1093
  -3.500   0.0026   0.02181   0.01467  -0.0819   0.9102   0.0928
  -3.250   0.0316   0.02057   0.01325  -0.0817   0.8999   0.0928
  -3.000   0.0698   0.01915   0.01166  -0.0833   0.8941   0.0930
  -2.750   0.0981   0.01820   0.01056  -0.0829   0.8825   0.0928
  -2.500   0.1297   0.01716   0.00941  -0.0832   0.8726   0.0931
  -2.250   0.1622   0.01621   0.00837  -0.0836   0.8628   0.0937
  -2.000   0.1899   0.01550   0.00762  -0.0831   0.8497   0.0950
  -1.750   0.2180   0.01497   0.00707  -0.0828   0.8366   0.0975
  -1.500   0.2462   0.01450   0.00656  -0.0824   0.8234   0.0997
  -1.250   0.2739   0.01406   0.00606  -0.0819   0.8102   0.1016
  -1.000   0.3011   0.01369   0.00562  -0.0813   0.7966   0.1036
  -0.750   0.3265   0.01341   0.00529  -0.0804   0.7816   0.1058
  -0.500   0.3507   0.01297   0.00488  -0.0794   0.7664   0.1093
  -0.250   0.3755   0.01273   0.00464  -0.0785   0.7512   0.1149
   0.000   0.4006   0.01255   0.00442  -0.0776   0.7357   0.1212
   0.250   0.4252   0.01230   0.00418  -0.0766   0.7202   0.1312
   0.500   0.4497   0.01204   0.00397  -0.0756   0.7044   0.1579
   0.750   0.5464   0.00979   0.00393  -0.0894   0.6851   1.0000
   1.000   0.5686   0.00991   0.00388  -0.0880   0.6679   1.0000
   1.250   0.5909   0.01007   0.00387  -0.0867   0.6512   1.0000
   1.500   0.6132   0.01024   0.00390  -0.0854   0.6347   1.0000
   1.750   0.6355   0.01044   0.00395  -0.0841   0.6183   1.0000
   2.000   0.6576   0.01065   0.00403  -0.0828   0.6014   1.0000
   2.250   0.6796   0.01085   0.00413  -0.0815   0.5846   1.0000
   2.500   0.7017   0.01105   0.00423  -0.0801   0.5680   1.0000
   2.750   0.7237   0.01125   0.00433  -0.0788   0.5513   1.0000
   3.000   0.7456   0.01146   0.00445  -0.0775   0.5346   1.0000
   3.250   0.7674   0.01167   0.00457  -0.0762   0.5181   1.0000
   3.500   0.7893   0.01189   0.00471  -0.0749   0.5024   1.0000
   3.750   0.8115   0.01215   0.00487  -0.0737   0.4881   1.0000
   4.000   0.8338   0.01243   0.00504  -0.0725   0.4746   1.0000
   4.250   0.8561   0.01270   0.00525  -0.0713   0.4613   1.0000
   4.500   0.8786   0.01298   0.00548  -0.0702   0.4486   1.0000
   4.750   0.9011   0.01329   0.00574  -0.0692   0.4366   1.0000
   5.000   0.9236   0.01362   0.00598  -0.0681   0.4249   1.0000
   5.500   0.9671   0.01419   0.00647  -0.0657   0.3997   1.0000
   5.750   0.9893   0.01449   0.00675  -0.0646   0.3887   1.0000
   6.000   1.0119   0.01485   0.00703  -0.0636   0.3792   1.0000
   6.250   1.0341   0.01512   0.00736  -0.0626   0.3697   1.0000
   6.500   1.0567   0.01548   0.00769  -0.0617   0.3612   1.0000
   6.750   1.0789   0.01578   0.00802  -0.0606   0.3526   1.0000
   7.000   1.1014   0.01614   0.00839  -0.0597   0.3448   1.0000
   7.250   1.1232   0.01646   0.00873  -0.0586   0.3365   1.0000
   7.500   1.1446   0.01679   0.00910  -0.0575   0.3277   1.0000
   7.750   1.1657   0.01712   0.00943  -0.0563   0.3194   1.0000
   8.000   1.1863   0.01744   0.00984  -0.0551   0.3108   1.0000
   8.250   1.2067   0.01781   0.01019  -0.0538   0.3026   1.0000
   8.500   1.2263   0.01809   0.01061  -0.0524   0.2937   1.0000
   8.750   1.2456   0.01848   0.01098  -0.0510   0.2855   1.0000
   9.000   1.2640   0.01877   0.01142  -0.0494   0.2762   1.0000
   9.250   1.2812   0.01912   0.01182  -0.0477   0.2665   1.0000
   9.500   1.2967   0.01950   0.01221  -0.0457   0.2562   1.0000
   9.750   1.3119   0.01983   0.01266  -0.0436   0.2441   1.0000
  10.000   1.3237   0.02021   0.01311  -0.0410   0.2304   1.0000
  10.250   1.3325   0.02070   0.01361  -0.0379   0.2140   1.0000
  10.500   1.3396   0.02135   0.01424  -0.0348   0.1910   1.0000
  10.750   1.3419   0.02236   0.01512  -0.0314   0.1611   1.0000
  11.000   1.3398   0.02379   0.01636  -0.0277   0.1334   1.0000
  11.250   1.3367   0.02544   0.01787  -0.0243   0.1155   1.0000
  11.500   1.3362   0.02705   0.01944  -0.0215   0.1035   1.0000
  11.750   1.3394   0.02853   0.02095  -0.0192   0.0944   1.0000
  12.000   1.3404   0.03022   0.02267  -0.0170   0.0880   1.0000
  12.250   1.3424   0.03194   0.02443  -0.0152   0.0823   1.0000
  12.500   1.3411   0.03401   0.02651  -0.0134   0.0784   1.0000
  12.750   1.3431   0.03594   0.02854  -0.0120   0.0745   1.0000
  13.000   1.3401   0.03839   0.03102  -0.0108   0.0710   1.0000
  13.250   1.3350   0.04117   0.03384  -0.0097   0.0680   1.0000
  13.500   1.3343   0.04370   0.03650  -0.0090   0.0649   1.0000
  13.750   1.3297   0.04670   0.03955  -0.0085   0.0619   1.0000
  14.000   1.3217   0.05007   0.04285  -0.0077   0.0588   1.0000
  14.250   1.3202   0.05303   0.04601  -0.0076   0.0559   1.0000
  14.500   1.3164   0.05624   0.04928  -0.0075   0.0529   1.0000
  14.750   1.3160   0.05888   0.05179  -0.0063   0.0495   1.0000
  15.000   1.3130   0.06227   0.05540  -0.0068   0.0474   1.0000
  15.250   1.3120   0.06540   0.05864  -0.0071   0.0451   1.0000
  15.500   1.3139   0.06810   0.06133  -0.0070   0.0429   1.0000
  15.750   1.3180   0.07058   0.06382  -0.0065   0.0407   1.0000
  16.000   1.3138   0.07438   0.06782  -0.0075   0.0391   1.0000
  16.250   1.3136   0.07766   0.07123  -0.0081   0.0377   1.0000
  16.500   1.3148   0.08076   0.07440  -0.0087   0.0365   1.0000
  16.750   1.3195   0.08325   0.07687  -0.0088   0.0352   1.0000
  17.000   1.3210   0.08639   0.08010  -0.0090   0.0341   1.0000
  17.250   1.3133   0.09107   0.08501  -0.0109   0.0333   1.0000
  17.500   1.3082   0.09546   0.08960  -0.0124   0.0326   1.0000
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