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GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 796 AIRFOIL (goe796-il)
Reynolds number: 100,000
Max Cl/Cd: 55.62 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe796-il-100000-n5.txt
Download as CSV file: xf-goe796-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 796 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4044   0.09233   0.08701  -0.0490   1.0000   0.0403
  -9.500  -0.4114   0.08866   0.08342  -0.0494   1.0000   0.0401
  -9.250  -0.4221   0.08503   0.07987  -0.0495   1.0000   0.0399
  -9.000  -0.4381   0.08148   0.07641  -0.0491   1.0000   0.0398
  -8.750  -0.4612   0.07825   0.07331  -0.0478   1.0000   0.0395
  -8.500  -0.4907   0.07508   0.07026  -0.0461   1.0000   0.0393
  -8.250  -0.5057   0.06594   0.06106  -0.0539   0.9945   0.0389
  -8.000  -0.5247   0.04789   0.04227  -0.0678   0.9823   0.0383
  -7.750  -0.5179   0.03985   0.03341  -0.0717   0.9734   0.0386
  -7.500  -0.4990   0.03516   0.02803  -0.0736   0.9667   0.0392
  -7.250  -0.4739   0.03185   0.02412  -0.0751   0.9608   0.0401
  -7.000  -0.4427   0.02955   0.02143  -0.0770   0.9569   0.0411
  -6.750  -0.4167   0.02832   0.02007  -0.0775   0.9494   0.0424
  -6.500  -0.3837   0.02697   0.01853  -0.0792   0.9452   0.0443
  -6.250  -0.3531   0.02557   0.01686  -0.0802   0.9399   0.0472
  -6.000  -0.3246   0.02432   0.01538  -0.0807   0.9331   0.0507
  -5.750  -0.2909   0.02345   0.01445  -0.0823   0.9289   0.0562
  -5.500  -0.2636   0.02280   0.01371  -0.0825   0.9214   0.0630
  -5.250  -0.2317   0.02228   0.01306  -0.0834   0.9157   0.0715
  -5.000  -0.1978   0.02206   0.01277  -0.0848   0.9111   0.0801
  -4.750  -0.1716   0.02185   0.01250  -0.0846   0.9025   0.0876
  -4.500  -0.1382   0.02148   0.01192  -0.0856   0.8979   0.0968
  -4.250  -0.1120   0.02127   0.01172  -0.0855   0.8898   0.1051
  -4.000  -0.0811   0.02078   0.01111  -0.0861   0.8842   0.1134
  -3.750  -0.0524   0.02031   0.01063  -0.0864   0.8779   0.1204
  -3.250   0.0072   0.01932   0.00955  -0.0870   0.8665   0.1357
  -3.000   0.0320   0.01903   0.00921  -0.0864   0.8579   0.1446
  -2.750   0.0621   0.01863   0.00882  -0.0868   0.8528   0.1545
  -2.500   0.0883   0.01834   0.00855  -0.0865   0.8455   0.1637
  -2.250   0.1170   0.01805   0.00823  -0.0866   0.8394   0.1753
  -2.000   0.1455   0.01776   0.00799  -0.0867   0.8338   0.1912
  -1.750   0.1716   0.01753   0.00786  -0.0864   0.8265   0.2135
  -1.500   0.2015   0.01715   0.00759  -0.0867   0.8217   0.2447
  -1.250   0.2265   0.01691   0.00751  -0.0862   0.8140   0.2868
  -1.000   0.2548   0.01641   0.00732  -0.0863   0.8082   0.3689
  -0.750   0.2785   0.01575   0.00727  -0.0854   0.8007   0.5294
  -0.500   0.3023   0.01498   0.00728  -0.0834   0.7934   0.7654
  -0.250   0.3662   0.01469   0.00713  -0.0897   0.7856   0.9630
   0.000   0.4141   0.01456   0.00682  -0.0935   0.7764   1.0000
   0.250   0.4375   0.01459   0.00672  -0.0925   0.7654   1.0000
   0.500   0.4634   0.01460   0.00658  -0.0918   0.7567   1.0000
   0.750   0.4879   0.01468   0.00656  -0.0911   0.7480   1.0000
   1.000   0.5135   0.01476   0.00654  -0.0905   0.7407   1.0000
   1.250   0.5383   0.01486   0.00657  -0.0898   0.7324   1.0000
   1.500   0.5638   0.01496   0.00658  -0.0892   0.7246   1.0000
   1.750   0.5889   0.01507   0.00664  -0.0886   0.7162   1.0000
   2.000   0.6141   0.01520   0.00671  -0.0880   0.7081   1.0000
   2.250   0.6396   0.01532   0.00678  -0.0874   0.6997   1.0000
   2.500   0.6642   0.01547   0.00691  -0.0867   0.6906   1.0000
   2.750   0.6906   0.01557   0.00694  -0.0862   0.6820   1.0000
   3.000   0.7142   0.01575   0.00712  -0.0853   0.6715   1.0000
   3.250   0.7396   0.01588   0.00723  -0.0847   0.6619   1.0000
   3.500   0.7647   0.01600   0.00734  -0.0840   0.6513   1.0000
   3.750   0.7883   0.01616   0.00751  -0.0831   0.6387   1.0000
   4.000   0.8122   0.01630   0.00765  -0.0822   0.6251   1.0000
   4.250   0.8360   0.01643   0.00777  -0.0813   0.6102   1.0000
   4.500   0.8596   0.01657   0.00790  -0.0803   0.5945   1.0000
   4.750   0.8830   0.01673   0.00807  -0.0793   0.5785   1.0000
   5.000   0.9063   0.01691   0.00824  -0.0783   0.5619   1.0000
   5.250   0.9293   0.01711   0.00841  -0.0773   0.5441   1.0000
   5.500   0.9515   0.01734   0.00861  -0.0761   0.5244   1.0000
   5.750   0.9733   0.01761   0.00886  -0.0749   0.5035   1.0000
   6.000   0.9948   0.01792   0.00910  -0.0737   0.4828   1.0000
   6.250   1.0162   0.01827   0.00940  -0.0725   0.4643   1.0000
   6.500   1.0375   0.01866   0.00976  -0.0713   0.4468   1.0000
   6.750   1.0582   0.01908   0.01017  -0.0701   0.4297   1.0000
   7.000   1.0785   0.01955   0.01060  -0.0688   0.4133   1.0000
   7.250   1.0981   0.02004   0.01107  -0.0674   0.3968   1.0000
   7.500   1.1165   0.02058   0.01156  -0.0659   0.3791   1.0000
   7.750   1.1336   0.02117   0.01211  -0.0642   0.3608   1.0000
   8.000   1.1502   0.02179   0.01269  -0.0624   0.3434   1.0000
   8.250   1.1665   0.02241   0.01330  -0.0607   0.3270   1.0000
   8.500   1.1820   0.02306   0.01396  -0.0588   0.3108   1.0000
   8.750   1.1967   0.02372   0.01465  -0.0569   0.2943   1.0000
   9.000   1.2099   0.02438   0.01539  -0.0547   0.2771   1.0000
   9.250   1.2213   0.02509   0.01614  -0.0523   0.2592   1.0000
   9.500   1.2319   0.02588   0.01696  -0.0499   0.2412   1.0000
   9.750   1.2412   0.02679   0.01786  -0.0475   0.2237   1.0000
  10.000   1.2494   0.02783   0.01886  -0.0451   0.2079   1.0000
  10.250   1.2570   0.02898   0.01999  -0.0428   0.1942   1.0000
  10.500   1.2646   0.03021   0.02121  -0.0406   0.1825   1.0000
  10.750   1.2717   0.03154   0.02255  -0.0385   0.1717   1.0000
  11.000   1.2770   0.03302   0.02402  -0.0364   0.1616   1.0000
  11.250   1.2823   0.03457   0.02558  -0.0345   0.1510   1.0000
  11.500   1.2890   0.03606   0.02717  -0.0328   0.1399   1.0000
  11.750   1.2944   0.03769   0.02888  -0.0312   0.1298   1.0000
  12.000   1.2982   0.03949   0.03071  -0.0297   0.1208   1.0000
  12.250   1.3051   0.04113   0.03250  -0.0285   0.1116   1.0000
  12.500   1.3088   0.04308   0.03451  -0.0273   0.1040   1.0000
  12.750   1.3110   0.04522   0.03670  -0.0262   0.0962   1.0000
  13.000   1.3132   0.04744   0.03902  -0.0252   0.0888   1.0000
  13.250   1.3111   0.05014   0.04173  -0.0244   0.0826   1.0000
  13.500   1.3124   0.05262   0.04434  -0.0237   0.0760   1.0000
  13.750   1.3083   0.05571   0.04749  -0.0231   0.0711   1.0000
  14.000   1.3074   0.05857   0.05051  -0.0226   0.0656   1.0000
  14.250   1.3023   0.06201   0.05402  -0.0224   0.0610   1.0000
  14.500   1.2980   0.06550   0.05762  -0.0224   0.0565   1.0000
  14.750   1.2929   0.06921   0.06146  -0.0226   0.0524   1.0000
  15.000   1.2840   0.07351   0.06582  -0.0232   0.0496   1.0000
  15.250   1.2794   0.07740   0.06987  -0.0236   0.0464   1.0000
  15.500   1.2727   0.08171   0.07432  -0.0244   0.0438   1.0000
  15.750   1.2639   0.08644   0.07915  -0.0256   0.0419   1.0000
  16.000   1.2549   0.09128   0.08406  -0.0269   0.0403   1.0000
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