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GOE 496 AIRFOIL (goe496-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 496 AIRFOIL (goe496-il)
Reynolds number: 500,000
Max Cl/Cd: 124.31 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe496-il-500000.txt
Download as CSV file: xf-goe496-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 496 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3551   0.10580   0.10347  -0.0395   1.0000   0.0315
 -10.000  -0.3495   0.10433   0.10202  -0.0380   1.0000   0.0320
  -9.750  -0.3462   0.10266   0.10038  -0.0366   1.0000   0.0324
  -9.500  -0.3448   0.10108   0.09882  -0.0352   1.0000   0.0330
  -9.250  -0.3478   0.09918   0.09695  -0.0339   1.0000   0.0335
  -9.000  -0.3371   0.09574   0.09352  -0.0372   0.9987   0.0356
  -8.500  -0.3877   0.02814   0.02452  -0.1243   0.9719   0.0316
  -8.250  -0.3576   0.02609   0.02238  -0.1271   0.9685   0.0326
  -8.000  -0.3275   0.02521   0.02147  -0.1285   0.9639   0.0336
  -7.750  -0.2929   0.02312   0.01912  -0.1318   0.9612   0.0346
  -7.500  -0.2562   0.02125   0.01694  -0.1350   0.9593   0.0358
  -7.250  -0.2182   0.02000   0.01542  -0.1379   0.9579   0.0371
  -7.000  -0.1868   0.01914   0.01433  -0.1390   0.9535   0.0377
  -6.750  -0.1578   0.01667   0.01156  -0.1405   0.9484   0.0386
  -6.500  -0.1244   0.01538   0.01019  -0.1422   0.9452   0.0399
  -6.250  -0.0896   0.01458   0.00932  -0.1439   0.9424   0.0410
  -6.000  -0.0633   0.01388   0.00852  -0.1436   0.9343   0.0419
  -5.750  -0.0311   0.01315   0.00769  -0.1445   0.9293   0.0430
  -5.500  -0.0021   0.01256   0.00700  -0.1447   0.9221   0.0439
  -5.250   0.0281   0.01209   0.00644  -0.1451   0.9150   0.0451
  -5.000   0.0573   0.01173   0.00599  -0.1452   0.9070   0.0459
  -4.750   0.0862   0.01087   0.00502  -0.1455   0.8990   0.0472
  -4.500   0.1138   0.01031   0.00442  -0.1454   0.8896   0.0488
  -4.250   0.1434   0.00992   0.00396  -0.1456   0.8815   0.0507
  -4.000   0.1708   0.00963   0.00361  -0.1454   0.8714   0.0527
  -3.750   0.1992   0.00940   0.00330  -0.1454   0.8624   0.0550
  -3.500   0.2275   0.00910   0.00292  -0.1453   0.8530   0.0583
  -3.250   0.2551   0.00885   0.00265  -0.1451   0.8434   0.0638
  -3.000   0.2834   0.00862   0.00245  -0.1451   0.8347   0.0788
  -2.750   0.3108   0.00851   0.00241  -0.1448   0.8248   0.1109
  -2.500   0.3386   0.00847   0.00234  -0.1446   0.8159   0.1253
  -2.250   0.3663   0.00846   0.00228  -0.1444   0.8068   0.1348
  -2.000   0.3938   0.00837   0.00219  -0.1442   0.7975   0.1433
  -1.500   0.4488   0.00827   0.00205  -0.1438   0.7793   0.1600
  -1.250   0.4764   0.00822   0.00199  -0.1436   0.7705   0.1719
  -1.000   0.5037   0.00813   0.00195  -0.1433   0.7611   0.1950
  -0.750   0.5309   0.00798   0.00196  -0.1432   0.7520   0.2504
  -0.500   0.5581   0.00792   0.00198  -0.1430   0.7426   0.3030
  -0.250   0.5850   0.00786   0.00200  -0.1426   0.7312   0.3422
   0.000   0.6119   0.00784   0.00202  -0.1423   0.7201   0.3734
   0.250   0.6387   0.00785   0.00205  -0.1419   0.7091   0.4017
   0.500   0.6654   0.00785   0.00208  -0.1415   0.6974   0.4302
   0.750   0.6922   0.00785   0.00212  -0.1412   0.6860   0.4591
   1.000   0.7188   0.00787   0.00217  -0.1408   0.6746   0.4890
   1.250   0.7451   0.00787   0.00221  -0.1403   0.6625   0.5240
   1.500   0.7710   0.00780   0.00230  -0.1398   0.6498   0.5849
   1.750   0.7960   0.00765   0.00241  -0.1391   0.6378   0.6989
   2.000   0.8209   0.00718   0.00245  -0.1381   0.6270   1.0000
   2.250   0.8475   0.00732   0.00251  -0.1377   0.6161   1.0000
   2.500   0.8741   0.00745   0.00259  -0.1373   0.6049   1.0000
   2.750   0.9009   0.00758   0.00268  -0.1370   0.5946   1.0000
   3.000   0.9272   0.00774   0.00278  -0.1366   0.5844   1.0000
   3.250   0.9535   0.00789   0.00289  -0.1362   0.5731   1.0000
   3.500   0.9798   0.00804   0.00301  -0.1357   0.5619   1.0000
   3.750   1.0059   0.00820   0.00314  -0.1353   0.5515   1.0000
   4.000   1.0317   0.00839   0.00327  -0.1348   0.5407   1.0000
   4.250   1.0578   0.00854   0.00343  -0.1343   0.5292   1.0000
   4.500   1.0833   0.00872   0.00358  -0.1338   0.5169   1.0000
   4.750   1.1086   0.00892   0.00375  -0.1332   0.5044   1.0000
   5.000   1.1337   0.00912   0.00394  -0.1326   0.4913   1.0000
   5.250   1.1583   0.00934   0.00413  -0.1319   0.4752   1.0000
   5.500   1.1817   0.00961   0.00433  -0.1310   0.4508   1.0000
   5.750   1.2033   0.00999   0.00457  -0.1298   0.4178   1.0000
   6.000   1.2225   0.01054   0.00490  -0.1282   0.3707   1.0000
   6.250   1.2394   0.01130   0.00534  -0.1264   0.3144   1.0000
   6.500   1.2576   0.01199   0.00581  -0.1248   0.2757   1.0000
   6.750   1.2774   0.01256   0.00625  -0.1234   0.2513   1.0000
   7.250   1.3186   0.01354   0.00709  -0.1210   0.2190   1.0000
   7.750   1.3595   0.01446   0.00794  -0.1185   0.1895   1.0000
   8.000   1.3795   0.01492   0.00836  -0.1172   0.1729   1.0000
   8.250   1.3975   0.01550   0.00884  -0.1156   0.1490   1.0000
   8.500   1.4088   0.01646   0.00953  -0.1130   0.1078   1.0000
   8.750   1.4125   0.01774   0.01052  -0.1091   0.0688   1.0000
   9.000   1.4190   0.01885   0.01149  -0.1057   0.0483   1.0000
   9.250   1.4284   0.01980   0.01241  -0.1028   0.0378   1.0000
   9.500   1.4370   0.02081   0.01340  -0.0999   0.0318   1.0000
   9.750   1.4487   0.02164   0.01428  -0.0975   0.0287   1.0000
  10.000   1.4551   0.02284   0.01550  -0.0945   0.0260   1.0000
  10.250   1.4675   0.02365   0.01638  -0.0924   0.0245   1.0000
  10.500   1.4775   0.02465   0.01744  -0.0902   0.0230   1.0000
  10.750   1.4835   0.02595   0.01880  -0.0876   0.0218   1.0000
  11.000   1.4858   0.02759   0.02052  -0.0848   0.0208   1.0000
  11.250   1.4940   0.02885   0.02187  -0.0828   0.0202   1.0000
  11.500   1.5010   0.03026   0.02336  -0.0808   0.0195   1.0000
  11.750   1.5069   0.03182   0.02500  -0.0789   0.0189   1.0000
  12.000   1.5118   0.03352   0.02678  -0.0771   0.0182   1.0000
  12.250   1.5148   0.03546   0.02879  -0.0754   0.0177   1.0000
  12.500   1.5117   0.03809   0.03149  -0.0735   0.0172   1.0000
  12.750   1.5079   0.04092   0.03444  -0.0719   0.0167   1.0000
  13.000   1.5133   0.04293   0.03655  -0.0708   0.0164   1.0000
  13.250   1.5174   0.04514   0.03886  -0.0699   0.0160   1.0000
  13.500   1.5195   0.04763   0.04146  -0.0690   0.0156   1.0000
  13.750   1.5211   0.05026   0.04419  -0.0683   0.0152   1.0000
  14.000   1.5224   0.05304   0.04707  -0.0678   0.0149   1.0000
  14.250   1.5229   0.05596   0.05009  -0.0674   0.0146   1.0000
  14.500   1.5233   0.05901   0.05322  -0.0672   0.0143   1.0000
  14.750   1.5229   0.06225   0.05654  -0.0672   0.0141   1.0000
  15.000   1.5214   0.06570   0.06007  -0.0672   0.0138   1.0000
  15.250   1.5182   0.06945   0.06390  -0.0671   0.0135   1.0000
  15.500   1.5154   0.07326   0.06783  -0.0669   0.0133   1.0000
  15.750   1.5154   0.07683   0.07153  -0.0674   0.0131   1.0000
  16.000   1.5144   0.08060   0.07545  -0.0682   0.0130   1.0000
  16.250   1.5127   0.08458   0.07958  -0.0691   0.0128   1.0000
  16.500   1.5103   0.08875   0.08389  -0.0702   0.0126   1.0000
  16.750   1.5073   0.09312   0.08841  -0.0715   0.0124   1.0000
  17.000   1.5035   0.09768   0.09311  -0.0730   0.0122   1.0000
  17.250   1.4993   0.10238   0.09795  -0.0748   0.0120   1.0000
  17.500   1.4947   0.10725   0.10294  -0.0767   0.0118   1.0000
  17.750   1.4899   0.11224   0.10806  -0.0788   0.0117   1.0000
  18.000   1.4841   0.11749   0.11345  -0.0812   0.0116   1.0000
  18.250   1.4774   0.12298   0.11908  -0.0839   0.0114   1.0000
  18.500   1.4704   0.12864   0.12488  -0.0869   0.0113   1.0000
  18.750   1.4630   0.13448   0.13086  -0.0901   0.0113   1.0000
  19.000   1.4551   0.14052   0.13703  -0.0936   0.0112   1.0000
  19.250   1.4469   0.14675   0.14339  -0.0974   0.0111   1.0000
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