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GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 426 AIRFOIL (goe426-il)
Reynolds number: 500,000
Max Cl/Cd: 110.42 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe426-il-500000-n5.txt
Download as CSV file: xf-goe426-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 426 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2975   0.11460   0.11216  -0.0432   1.0000   0.0200
 -11.500  -0.2982   0.11042   0.10799  -0.0447   1.0000   0.0205
 -11.250  -0.3074   0.10239   0.09996  -0.0494   0.9856   0.0215
 -11.000  -0.2845   0.09959   0.09714  -0.0538   0.9733   0.0217
 -10.750  -0.2601   0.09619   0.09371  -0.0592   0.9618   0.0221
 -10.500  -0.2384   0.09142   0.08891  -0.0660   0.9496   0.0224
 -10.250  -0.2183   0.08616   0.08359  -0.0733   0.9340   0.0226
 -10.000  -0.2029   0.08126   0.07859  -0.0794   0.9125   0.0231
  -9.750  -0.1996   0.07652   0.07377  -0.0832   0.8850   0.0232
  -9.500  -0.2031   0.07206   0.06920  -0.0856   0.8554   0.0235
  -9.250  -0.2127   0.06719   0.06422  -0.0878   0.8262   0.0237
  -9.000  -0.2369   0.05997   0.05691  -0.0916   0.7989   0.0242
  -8.750  -0.3353   0.04014   0.03660  -0.1046   0.7741   0.0242
  -8.500  -0.3654   0.03041   0.02604  -0.1052   0.7601   0.0247
  -8.250  -0.3611   0.02609   0.02109  -0.1046   0.7483   0.0252
  -8.000  -0.3447   0.02402   0.01862  -0.1040   0.7373   0.0255
  -7.750  -0.3251   0.02249   0.01687  -0.1037   0.7275   0.0258
  -7.500  -0.3033   0.02136   0.01555  -0.1033   0.7174   0.0260
  -7.250  -0.2799   0.02048   0.01451  -0.1030   0.7079   0.0262
  -7.000  -0.2563   0.01966   0.01352  -0.1027   0.6985   0.0265
  -6.750  -0.2318   0.01886   0.01257  -0.1024   0.6893   0.0267
  -6.500  -0.2072   0.01811   0.01167  -0.1021   0.6808   0.0269
  -6.250  -0.1819   0.01740   0.01081  -0.1019   0.6719   0.0272
  -6.000  -0.1566   0.01674   0.01000  -0.1016   0.6631   0.0275
  -5.750  -0.1309   0.01612   0.00925  -0.1014   0.6531   0.0278
  -5.500  -0.1050   0.01553   0.00853  -0.1011   0.6433   0.0280
  -5.000  -0.0528   0.01451   0.00727  -0.1006   0.6231   0.0287
  -4.750  -0.0265   0.01411   0.00676  -0.1004   0.6137   0.0292
  -4.500   0.0000   0.01375   0.00630  -0.1002   0.6036   0.0296
  -4.250   0.0266   0.01343   0.00588  -0.0999   0.5941   0.0300
  -3.750   0.0795   0.01270   0.00500  -0.0995   0.5774   0.0306
  -3.500   0.1057   0.01233   0.00457  -0.0992   0.5699   0.0310
  -3.250   0.1325   0.01206   0.00426  -0.0991   0.5632   0.0315
  -3.000   0.1594   0.01185   0.00402  -0.0989   0.5565   0.0320
  -2.750   0.1863   0.01167   0.00379  -0.0987   0.5509   0.0325
  -2.500   0.2136   0.01148   0.00358  -0.0986   0.5454   0.0331
  -2.250   0.2408   0.01133   0.00338  -0.0985   0.5399   0.0337
  -2.000   0.2680   0.01121   0.00320  -0.0984   0.5351   0.0344
  -1.750   0.2957   0.01108   0.00305  -0.0983   0.5304   0.0353
  -1.500   0.3232   0.01099   0.00293  -0.0982   0.5255   0.0362
  -1.250   0.3503   0.01085   0.00276  -0.0981   0.5209   0.0375
  -1.000   0.3780   0.01075   0.00265  -0.0981   0.5169   0.0388
  -0.750   0.4058   0.01068   0.00256  -0.0980   0.5129   0.0403
  -0.500   0.4335   0.01063   0.00249  -0.0980   0.5087   0.0420
  -0.250   0.4609   0.01059   0.00242  -0.0979   0.5048   0.0445
   0.000   0.4886   0.01054   0.00237  -0.0978   0.5014   0.0486
   0.250   0.5164   0.01047   0.00232  -0.0978   0.4979   0.0573
   0.500   0.5436   0.01024   0.00231  -0.0978   0.4942   0.1285
   0.750   0.5687   0.00956   0.00233  -0.0978   0.4905   0.3822
   1.000   0.5948   0.00936   0.00239  -0.0977   0.4869   0.4793
   1.250   0.6216   0.00922   0.00247  -0.0975   0.4839   0.5604
   1.500   0.6483   0.00913   0.00255  -0.0973   0.4803   0.6216
   1.750   0.6740   0.00902   0.00265  -0.0968   0.4763   0.6905
   2.000   0.6985   0.00892   0.00276  -0.0960   0.4727   0.7652
   2.250   0.7233   0.00887   0.00284  -0.0952   0.4695   0.8151
   2.500   0.7478   0.00876   0.00290  -0.0943   0.4661   0.8712
   2.750   0.7929   0.00871   0.00296  -0.0979   0.4616   1.0000
   3.000   0.8198   0.00883   0.00303  -0.0978   0.4574   1.0000
   3.250   0.8465   0.00896   0.00312  -0.0976   0.4536   1.0000
   3.500   0.8739   0.00904   0.00321  -0.0976   0.4500   1.0000
   3.750   0.9010   0.00915   0.00330  -0.0974   0.4458   1.0000
   4.000   0.9277   0.00928   0.00341  -0.0973   0.4414   1.0000
   4.250   0.9541   0.00942   0.00352  -0.0971   0.4371   1.0000
   4.500   0.9812   0.00952   0.00363  -0.0969   0.4324   1.0000
   4.750   1.0077   0.00965   0.00376  -0.0968   0.4278   1.0000
   5.000   1.0337   0.00981   0.00390  -0.0965   0.4233   1.0000
   5.250   1.0602   0.00993   0.00404  -0.0963   0.4186   1.0000
   5.500   1.0864   0.01008   0.00419  -0.0961   0.4129   1.0000
   5.750   1.1116   0.01026   0.00435  -0.0957   0.4068   1.0000
   6.000   1.1376   0.01040   0.00451  -0.0954   0.4002   1.0000
   6.250   1.1626   0.01059   0.00470  -0.0950   0.3939   1.0000
   6.500   1.1879   0.01077   0.00489  -0.0947   0.3884   1.0000
   6.750   1.2124   0.01098   0.00509  -0.0942   0.3802   1.0000
   7.000   1.2361   0.01122   0.00532  -0.0936   0.3698   1.0000
   7.250   1.2588   0.01150   0.00556  -0.0928   0.3591   1.0000
   7.500   1.2818   0.01176   0.00582  -0.0921   0.3492   1.0000
   7.750   1.3036   0.01208   0.00611  -0.0912   0.3366   1.0000
   8.000   1.3244   0.01244   0.00643  -0.0902   0.3233   1.0000
   8.250   1.3442   0.01283   0.00678  -0.0890   0.3096   1.0000
   8.500   1.3624   0.01328   0.00717  -0.0876   0.2931   1.0000
   8.750   1.3780   0.01383   0.00763  -0.0858   0.2729   1.0000
   9.000   1.3899   0.01445   0.00815  -0.0833   0.2502   1.0000
   9.250   1.3950   0.01529   0.00883  -0.0798   0.2195   1.0000
   9.500   1.3931   0.01650   0.00981  -0.0755   0.1806   1.0000
   9.750   1.3868   0.01801   0.01110  -0.0709   0.1415   1.0000
  10.000   1.3862   0.01937   0.01233  -0.0675   0.1180   1.0000
  10.250   1.3886   0.02065   0.01356  -0.0646   0.1023   1.0000
  10.500   1.3910   0.02203   0.01489  -0.0621   0.0864   1.0000
  10.750   1.3894   0.02378   0.01655  -0.0595   0.0672   1.0000
  11.000   1.3869   0.02574   0.01845  -0.0571   0.0517   1.0000
  11.250   1.3859   0.02776   0.02045  -0.0552   0.0404   1.0000
  11.500   1.3853   0.02989   0.02257  -0.0536   0.0310   1.0000
  11.750   1.3856   0.03209   0.02477  -0.0523   0.0247   1.0000
  12.000   1.3873   0.03426   0.02697  -0.0513   0.0216   1.0000
  12.250   1.3892   0.03649   0.02926  -0.0504   0.0196   1.0000
  12.500   1.3916   0.03874   0.03158  -0.0497   0.0184   1.0000
  12.750   1.3944   0.04101   0.03392  -0.0491   0.0174   1.0000
  13.000   1.3963   0.04346   0.03643  -0.0486   0.0167   1.0000
  13.250   1.3963   0.04617   0.03922  -0.0482   0.0158   1.0000
  13.500   1.3958   0.04903   0.04214  -0.0479   0.0152   1.0000
  13.750   1.3969   0.05178   0.04497  -0.0478   0.0147   1.0000
  14.000   1.3981   0.05459   0.04788  -0.0477   0.0143   1.0000
  14.250   1.3985   0.05755   0.05093  -0.0477   0.0139   1.0000
  14.500   1.3987   0.06060   0.05405  -0.0479   0.0134   1.0000
  14.750   1.3983   0.06378   0.05732  -0.0481   0.0132   1.0000
  15.000   1.3971   0.06712   0.06074  -0.0485   0.0129   1.0000
  15.250   1.3952   0.07061   0.06430  -0.0489   0.0125   1.0000
  15.500   1.3923   0.07430   0.06807  -0.0495   0.0123   1.0000
  15.750   1.3880   0.07827   0.07212  -0.0502   0.0120   1.0000
  16.000   1.3858   0.08201   0.07595  -0.0509   0.0118   1.0000
  16.250   1.3853   0.08554   0.07957  -0.0516   0.0115   1.0000
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