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GOE 523 AIRFOIL (goe523-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 523 AIRFOIL (goe523-il)
Reynolds number: 100,000
Max Cl/Cd: 48.76 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe523-il-100000.txt
Download as CSV file: xf-goe523-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 523 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250   0.0754   0.11636   0.11173  -0.0953   0.8453   0.1111
  -7.000   0.0419   0.11818   0.11363  -0.0919   0.8314   0.1123
  -6.750   0.0076   0.11990   0.11542  -0.0889   0.8195   0.1127
  -6.500   0.0637   0.11176   0.10722  -0.0906   0.8178   0.1157
  -6.250   0.0872   0.10849   0.10392  -0.0920   0.8139   0.1199
  -6.000   0.0791   0.10777   0.10324  -0.0898   0.8050   0.1224
  -5.750   0.0621   0.10761   0.10311  -0.0886   0.7966   0.1257
  -5.500   0.0232   0.10951   0.10510  -0.0860   0.7833   0.1269
  -5.250   0.0368   0.10507   0.10065  -0.0885   0.7792   0.1286
  -5.000   0.0737   0.10060   0.09613  -0.0876   0.7776   0.1316
  -4.750   0.0529   0.10096   0.09656  -0.0823   0.7650   0.1326
  -4.500   0.0732   0.09788   0.09345  -0.0848   0.7614   0.1378
  -4.250   0.0565   0.09748   0.09309  -0.0981   0.7469   0.1440
  -4.000   0.0726   0.09358   0.08917  -0.0914   0.7445   0.1456
  -3.750   0.0646   0.09308   0.08873  -0.0862   0.7346   0.1470
  -3.500   0.1137   0.08855   0.08408  -0.1069   0.7285   0.1616
  -3.250   0.1242   0.08545   0.08100  -0.0992   0.7263   0.1634
  -3.000   0.1938   0.07964   0.07503  -0.1180   0.7245   0.1800
  -2.750   0.4318   0.05143   0.04523  -0.1893   0.7271   0.1123
  -2.500   0.5211   0.04564   0.03892  -0.2029   0.7268   0.1076
  -2.250   0.5648   0.04414   0.03692  -0.2083   0.7182   0.1069
  -2.000   0.6220   0.04199   0.03427  -0.2138   0.7145   0.1105
  -1.750   0.6806   0.03953   0.03151  -0.2185   0.7129   0.1158
  -1.500   0.7364   0.03732   0.02913  -0.2221   0.7117   0.1234
  -1.250   0.7943   0.03511   0.02685  -0.2261   0.7105   0.1389
  -1.000   0.8569   0.03271   0.02453  -0.2309   0.7096   0.1747
  -0.750   0.8745   0.03317   0.02526  -0.2301   0.6992   0.2256
  -0.500   0.9296   0.03177   0.02407  -0.2340   0.6962   0.3298
  -0.250   0.9844   0.03048   0.02293  -0.2371   0.6938   0.4122
   0.000   1.0418   0.02940   0.02188  -0.2403   0.6915   0.4755
   0.250   1.0372   0.03070   0.02325  -0.2349   0.6795   0.4953
   0.500   1.0880   0.02984   0.02233  -0.2372   0.6760   0.5325
   0.750   1.1473   0.02884   0.02118  -0.2411   0.6729   0.5639
   1.000   1.1401   0.03007   0.02247  -0.2354   0.6608   0.5774
   1.250   1.1976   0.02918   0.02139  -0.2395   0.6566   0.6074
   1.500   1.1999   0.03012   0.02238  -0.2352   0.6463   0.6215
   1.750   1.2451   0.02963   0.02174  -0.2376   0.6404   0.6488
   2.000   1.2726   0.02972   0.02178  -0.2371   0.6333   0.6727
   2.250   1.2904   0.03012   0.02216  -0.2354   0.6246   0.6946
   2.500   1.3454   0.02936   0.02118  -0.2397   0.6196   0.7207
   2.750   1.3422   0.03054   0.02247  -0.2349   0.6095   0.7342
   3.000   1.3868   0.03012   0.02189  -0.2377   0.6034   0.7550
   3.250   1.4048   0.03068   0.02243  -0.2363   0.5956   0.7716
   3.500   1.4254   0.03105   0.02276  -0.2353   0.5879   0.7886
   3.750   1.4808   0.03044   0.02191  -0.2400   0.5827   0.8108
   4.000   1.4681   0.03185   0.02351  -0.2337   0.5735   0.8232
   4.250   1.5043   0.03169   0.02324  -0.2352   0.5674   0.8447
   4.500   1.5286   0.03189   0.02344  -0.2348   0.5611   0.8683
   4.750   1.5230   0.03277   0.02451  -0.2295   0.5533   0.9068
   5.000   1.5755   0.03248   0.02402  -0.2339   0.5478   1.0000
   5.250   1.5778   0.03384   0.02545  -0.2305   0.5404   1.0000
   5.500   1.5979   0.03454   0.02612  -0.2298   0.5336   1.0000
   5.750   1.6619   0.03408   0.02540  -0.2361   0.5286   1.0000
   6.000   1.6356   0.03621   0.02774  -0.2281   0.5210   1.0000
   6.250   1.6630   0.03663   0.02810  -0.2284   0.5149   1.0000
   6.500   1.7339   0.03595   0.02715  -0.2356   0.5103   1.0000
   6.750   1.6859   0.03886   0.03038  -0.2245   0.5028   1.0000
   7.000   1.7131   0.03929   0.03075  -0.2247   0.4972   1.0000
   7.250   1.7871   0.03829   0.02948  -0.2320   0.4928   1.0000
   7.500   1.7266   0.04201   0.03356  -0.2196   0.4853   1.0000
   7.750   1.7527   0.04240   0.03391  -0.2196   0.4798   1.0000
   8.000   1.8289   0.04100   0.03223  -0.2268   0.4755   1.0000
   8.250   1.7561   0.04586   0.03749  -0.2136   0.4681   1.0000
   8.500   1.7743   0.04672   0.03837  -0.2127   0.4627   1.0000
   8.750   1.8422   0.04522   0.03667  -0.2180   0.4590   1.0000
   9.000   1.7606   0.05182   0.04366  -0.2055   0.4514   1.0000
   9.250   1.7551   0.05440   0.04633  -0.2024   0.4455   1.0000
   9.500   1.8249   0.05196   0.04373  -0.2069   0.4425   1.0000
   9.750   1.5513   0.08097   0.07351  -0.1865   0.4212   1.0000
  10.000   1.6152   0.07629   0.06875  -0.1875   0.4210   1.0000
  10.250   1.6929   0.07067   0.06302  -0.1897   0.4209   1.0000
  10.500   1.8163   0.06206   0.05417  -0.1963   0.4216   1.0000
  10.750   1.1569   0.16738   0.16088  -0.2013   0.3856   1.0000
  11.000   1.0911   0.18219   0.17590  -0.2090   0.4164   1.0000
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