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GOE 797 AIRFOIL (goe797-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 797 AIRFOIL (goe797-il)
Reynolds number: 100,000
Max Cl/Cd: 48.92 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe797-il-100000.txt
Download as CSV file: xf-goe797-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 797 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2450   0.10488   0.09999  -0.0600   0.9644   0.1546
  -8.000  -0.2403   0.10170   0.09681  -0.0636   0.9574   0.1599
  -7.750  -0.3106   0.09760   0.09277  -0.0762   0.9396   0.1643
  -7.500  -0.2582   0.09423   0.08939  -0.0710   0.9407   0.1663
  -7.250  -0.2165   0.09120   0.08630  -0.0721   0.9390   0.1716
  -7.000  -0.2301   0.08930   0.08444  -0.0716   0.9280   0.1760
  -6.750  -0.2822   0.08412   0.07919  -0.0804   0.9126   0.1823
  -6.500  -0.2484   0.08171   0.07684  -0.0777   0.9100   0.1847
  -6.250  -0.3082   0.06220   0.05632  -0.0913   0.8970   0.1318
  -6.000  -0.2900   0.05909   0.05321  -0.0917   0.8921   0.1301
  -5.750  -0.2688   0.05409   0.04788  -0.0947   0.8886   0.1287
  -5.500  -0.2610   0.05046   0.04388  -0.0944   0.8825   0.1280
  -5.250  -0.2495   0.04707   0.04005  -0.0940   0.8760   0.1280
  -5.000  -0.2205   0.04358   0.03587  -0.0961   0.8724   0.1308
  -4.750  -0.1846   0.04126   0.03326  -0.0987   0.8700   0.1350
  -4.500  -0.1806   0.04109   0.03309  -0.0954   0.8624   0.1372
  -4.250  -0.1545   0.04005   0.03182  -0.0958   0.8575   0.1419
  -4.000  -0.1177   0.03840   0.02962  -0.0979   0.8543   0.1485
  -3.750  -0.0778   0.03736   0.02863  -0.1004   0.8521   0.1551
  -3.500  -0.0786   0.03765   0.02881  -0.0964   0.8437   0.1589
  -3.250  -0.0475   0.03673   0.02759  -0.0973   0.8393   0.1663
  -3.000  -0.0093   0.03607   0.02691  -0.0993   0.8363   0.1757
  -2.750   0.0334   0.03514   0.02584  -0.1020   0.8343   0.1864
  -2.500   0.0284   0.03592   0.02663  -0.0975   0.8247   0.1908
  -2.250   0.0626   0.03541   0.02599  -0.0987   0.8208   0.2019
  -2.000   0.1037   0.03489   0.02542  -0.1010   0.8181   0.2154
  -1.750   0.1114   0.03539   0.02598  -0.0985   0.8103   0.2224
  -1.500   0.1391   0.03539   0.02590  -0.0987   0.8049   0.2350
  -1.250   0.1813   0.03469   0.02529  -0.1009   0.8015   0.2507
  -1.000   0.1980   0.03489   0.02555  -0.0994   0.7924   0.2616
  -0.750   0.2387   0.03404   0.02477  -0.1010   0.7861   0.2804
  -0.500   0.2950   0.03254   0.02337  -0.1046   0.7830   0.3083
  -0.250   0.3000   0.03318   0.02414  -0.1014   0.7713   0.3237
   0.000   0.3430   0.03209   0.02335  -0.1033   0.7677   0.3722
   0.250   0.3783   0.02966   0.02278  -0.1024   0.7660   0.7730
   0.500   0.4007   0.03062   0.02380  -0.1019   0.7555   1.0000
   0.750   0.4406   0.03029   0.02323  -0.1034   0.7511   1.0000
   1.000   0.4914   0.02950   0.02222  -0.1064   0.7488   1.0000
   1.250   0.5428   0.02858   0.02112  -0.1094   0.7470   1.0000
   1.500   0.5336   0.03020   0.02271  -0.1042   0.7330   1.0000
   1.750   0.5841   0.02924   0.02161  -0.1070   0.7308   1.0000
   2.000   0.6345   0.02828   0.02052  -0.1097   0.7289   1.0000
   2.250   0.6288   0.02981   0.02204  -0.1050   0.7148   1.0000
   2.500   0.6788   0.02879   0.02091  -0.1076   0.7125   1.0000
   2.750   0.6810   0.02998   0.02208  -0.1039   0.6995   1.0000
   3.000   0.7297   0.02892   0.02094  -0.1062   0.6963   1.0000
   3.250   0.7809   0.02779   0.01971  -0.1090   0.6935   1.0000
   3.500   0.7857   0.02876   0.02069  -0.1055   0.6802   1.0000
   3.750   0.8346   0.02772   0.01958  -0.1079   0.6766   1.0000
   4.000   0.8456   0.02841   0.02028  -0.1052   0.6645   1.0000
   4.250   0.8913   0.02750   0.01930  -0.1073   0.6595   1.0000
   4.500   0.9096   0.02782   0.01962  -0.1055   0.6484   1.0000
   4.750   0.9524   0.02699   0.01873  -0.1071   0.6419   1.0000
   5.000   0.9721   0.02720   0.01893  -0.1055   0.6303   1.0000
   5.250   1.0156   0.02639   0.01805  -0.1073   0.6234   1.0000
   5.500   1.0315   0.02677   0.01846  -0.1052   0.6110   1.0000
   5.750   1.0781   0.02594   0.01754  -0.1076   0.6045   1.0000
   6.000   1.0910   0.02646   0.01810  -0.1051   0.5914   1.0000
   6.250   1.1198   0.02640   0.01800  -0.1050   0.5816   1.0000
   6.500   1.1511   0.02618   0.01774  -0.1052   0.5717   1.0000
   6.750   1.1688   0.02655   0.01813  -0.1034   0.5599   1.0000
   7.000   1.2135   0.02586   0.01729  -0.1056   0.5520   1.0000
   7.250   1.2233   0.02647   0.01798  -0.1026   0.5393   1.0000
   7.500   1.2456   0.02664   0.01813  -0.1016   0.5284   1.0000
   7.750   1.2810   0.02633   0.01770  -0.1025   0.5189   1.0000
   8.000   1.2911   0.02701   0.01847  -0.0997   0.5077   1.0000
   8.250   1.3224   0.02703   0.01841  -0.1001   0.4988   1.0000
   8.500   1.3375   0.02762   0.01906  -0.0981   0.4891   1.0000
   8.750   1.3631   0.02795   0.01937  -0.0978   0.4807   1.0000
   9.000   1.3816   0.02845   0.01990  -0.0964   0.4716   1.0000
   9.250   1.4033   0.02894   0.02040  -0.0955   0.4631   1.0000
   9.500   1.4235   0.02941   0.02089  -0.0944   0.4541   1.0000
   9.750   1.4413   0.03002   0.02154  -0.0929   0.4455   1.0000
  10.000   1.4644   0.03041   0.02191  -0.0923   0.4363   1.0000
  10.250   1.4754   0.03122   0.02280  -0.0898   0.4275   1.0000
  10.500   1.5060   0.03145   0.02295  -0.0903   0.4178   1.0000
  10.750   1.5036   0.03250   0.02416  -0.0858   0.4090   1.0000
  11.000   1.5376   0.03274   0.02428  -0.0868   0.3984   1.0000
  11.250   1.5300   0.03388   0.02558  -0.0816   0.3893   1.0000
  11.500   1.5489   0.03447   0.02615  -0.0804   0.3787   1.0000
  11.750   1.5647   0.03509   0.02673  -0.0788   0.3675   1.0000
  12.000   1.5594   0.03642   0.02820  -0.0744   0.3575   1.0000
  12.250   1.5784   0.03705   0.02876  -0.0733   0.3456   1.0000
  12.500   1.5812   0.03814   0.02989  -0.0702   0.3344   1.0000
  12.750   1.5773   0.03968   0.03153  -0.0665   0.3238   1.0000
  13.000   1.5946   0.04042   0.03217  -0.0654   0.3122   1.0000
  13.250   1.5859   0.04218   0.03406  -0.0615   0.3021   1.0000
  13.500   1.5882   0.04366   0.03558  -0.0590   0.2924   1.0000
  13.750   1.5986   0.04466   0.03655  -0.0574   0.2824   1.0000
  14.000   1.5863   0.04704   0.03911  -0.0540   0.2743   1.0000
  14.250   1.6045   0.04766   0.03961  -0.0531   0.2652   1.0000
  14.500   1.5860   0.05063   0.04284  -0.0497   0.2581   1.0000
  14.750   1.6003   0.05146   0.04359  -0.0487   0.2501   1.0000
  15.000   1.5872   0.05441   0.04676  -0.0461   0.2435   1.0000
  15.250   1.5919   0.05599   0.04836  -0.0447   0.2363   1.0000
  15.500   1.5901   0.05824   0.05070  -0.0432   0.2299   1.0000
  15.750   1.5827   0.06094   0.05353  -0.0415   0.2234   1.0000
  16.000   1.5936   0.06211   0.05463  -0.0406   0.2165   1.0000
  16.250   1.5759   0.06598   0.05874  -0.0390   0.2108   1.0000
  16.500   1.5951   0.06624   0.05881  -0.0384   0.2029   1.0000
  16.750   1.5710   0.07104   0.06391  -0.0372   0.1979   1.0000
  17.000   1.5944   0.07076   0.06335  -0.0366   0.1891   1.0000
  17.250   1.5661   0.07628   0.06921  -0.0359   0.1849   1.0000
  17.500   1.5665   0.07861   0.07153  -0.0354   0.1780   1.0000
  17.750   1.5640   0.08149   0.07445  -0.0350   0.1721   1.0000
  18.000   1.5470   0.08623   0.07939  -0.0350   0.1672   1.0000
  18.250   1.5719   0.08580   0.07876  -0.0342   0.1598   1.0000
  18.500   1.5415   0.09240   0.08570  -0.0349   0.1566   1.0000
  18.750   1.5299   0.09676   0.09020  -0.0354   0.1518   1.0000
  19.000   1.5472   0.09717   0.09048  -0.0348   0.1453   1.0000
  19.250   1.5127   0.10497   0.09863  -0.0367   0.1424   1.0000
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