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GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 397 AIRFOIL (goe397-il)
Reynolds number: 100,000
Max Cl/Cd: 61.36 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe397-il-100000.txt
Download as CSV file: xf-goe397-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 397 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4014   0.10416   0.09910  -0.0162   1.0000   0.0500
  -8.250  -0.4024   0.10300   0.09803  -0.0189   1.0000   0.0510
  -8.000  -0.4048   0.10175   0.09686  -0.0214   1.0000   0.0514
  -7.750  -0.4017   0.10067   0.09584  -0.0276   1.0000   0.0518
  -7.500  -0.3930   0.09283   0.08804  -0.0214   1.0000   0.0539
  -7.250  -0.3849   0.08924   0.08448  -0.0206   1.0000   0.0560
  -7.000  -0.3787   0.08629   0.08157  -0.0216   1.0000   0.0579
  -6.750  -0.3721   0.08336   0.07865  -0.0235   1.0000   0.0603
  -6.500  -0.3635   0.08065   0.07598  -0.0269   1.0000   0.0632
  -6.250  -0.3434   0.07959   0.07482  -0.0382   1.0000   0.0654
  -6.000  -0.3372   0.07465   0.06995  -0.0378   1.0000   0.0664
  -5.750  -0.3344   0.07069   0.06609  -0.0335   1.0000   0.0684
  -5.500  -0.3257   0.06776   0.06319  -0.0331   1.0000   0.0716
  -5.250  -0.3106   0.06506   0.06045  -0.0360   1.0000   0.0770
  -5.000  -0.2924   0.06194   0.05721  -0.0407   1.0000   0.0805
  -4.750  -0.2926   0.05908   0.05448  -0.0365   1.0000   0.0843
  -4.500  -0.2664   0.05763   0.05268  -0.0424   1.0000   0.0937
  -4.250  -0.2685   0.05392   0.04917  -0.0384   1.0000   0.0959
  -4.000  -0.2618   0.05167   0.04694  -0.0367   1.0000   0.1005
  -3.750  -0.2419   0.04921   0.04422  -0.0392   1.0000   0.1090
  -3.500  -0.2350   0.04684   0.04191  -0.0374   1.0000   0.1141
  -3.250  -0.2167   0.04453   0.03941  -0.0386   1.0000   0.1240
  -3.000  -0.2000   0.04255   0.03727  -0.0391   1.0000   0.1370
  -2.750  -0.1664   0.03958   0.03425  -0.0423   0.9946   0.1568
  -2.500  -0.1276   0.03674   0.03122  -0.0465   0.9878   0.1819
  -1.250   0.0976   0.02451   0.01657  -0.0635   0.9567   0.1171
  -1.000   0.1356   0.02325   0.01468  -0.0646   0.9488   0.1064
  -0.750   0.1778   0.02193   0.01311  -0.0673   0.9430   0.1058
  -0.500   0.2146   0.02077   0.01181  -0.0688   0.9345   0.1031
  -0.250   0.2628   0.01962   0.01051  -0.0723   0.9283   0.1019
   0.000   0.3011   0.01884   0.00966  -0.0739   0.9184   0.1036
   0.250   0.3475   0.01794   0.00880  -0.0771   0.9121   0.1085
   0.500   0.3822   0.01744   0.00835  -0.0781   0.9025   0.1208
   0.750   0.4184   0.01693   0.00795  -0.0795   0.8938   0.1502
   1.000   0.4817   0.01450   0.00726  -0.0863   0.8895   1.0000
   1.250   0.5136   0.01461   0.00723  -0.0868   0.8795   1.0000
   1.500   0.5490   0.01460   0.00715  -0.0877   0.8712   1.0000
   1.750   0.5751   0.01480   0.00733  -0.0872   0.8596   1.0000
   2.000   0.6016   0.01500   0.00750  -0.0866   0.8482   1.0000
   2.250   0.6287   0.01517   0.00767  -0.0861   0.8373   1.0000
   2.500   0.6564   0.01529   0.00781  -0.0855   0.8268   1.0000
   2.750   0.6826   0.01545   0.00800  -0.0846   0.8154   1.0000
   3.000   0.7069   0.01568   0.00831  -0.0835   0.8025   1.0000
   3.250   0.7313   0.01590   0.00860  -0.0824   0.7893   1.0000
   3.500   0.7558   0.01604   0.00882  -0.0811   0.7749   1.0000
   3.750   0.7797   0.01596   0.00878  -0.0791   0.7565   1.0000
   4.000   0.8022   0.01564   0.00852  -0.0763   0.7316   1.0000
   4.250   0.8243   0.01524   0.00811  -0.0734   0.7029   1.0000
   4.750   0.8679   0.01487   0.00779  -0.0685   0.6388   1.0000
   5.000   0.8889   0.01480   0.00777  -0.0661   0.5976   1.0000
   5.250   0.9045   0.01474   0.00760  -0.0623   0.4971   1.0000
   5.500   0.8981   0.01786   0.00840  -0.0565   0.1671   1.0000
   5.750   0.9086   0.02015   0.01018  -0.0539   0.1183   1.0000
   6.000   0.9243   0.02177   0.01175  -0.0518   0.0953   1.0000
   6.250   0.9412   0.02361   0.01347  -0.0499   0.0816   1.0000
   6.500   0.9629   0.02565   0.01546  -0.0485   0.0718   1.0000
   6.750   0.9872   0.02818   0.01788  -0.0478   0.0642   1.0000
   7.000   1.0140   0.03044   0.02046  -0.0468   0.0608   1.0000
   7.250   1.0392   0.03301   0.02332  -0.0457   0.0582   1.0000
   7.500   1.0610   0.03603   0.02637  -0.0451   0.0536   1.0000
   7.750   1.0811   0.04075   0.03146  -0.0441   0.0526   1.0000
   8.000   1.1007   0.04326   0.03442  -0.0422   0.0533   1.0000
   8.250   1.1123   0.04702   0.03924  -0.0385   0.0589   1.0000
   8.500   1.1259   0.05235   0.04517  -0.0361   0.0687   1.0000
  11.250   0.9358   0.12654   0.12171  -0.0554   0.1369   1.0000
  11.500   0.8270   0.12942   0.12497  -0.0459   0.1452   1.0000
  11.750   0.7864   0.13493   0.13037  -0.0530   0.1386   1.0000
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