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GOE 447 AIRFOIL (goe447-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 447 AIRFOIL (goe447-il)
Reynolds number: 500,000
Max Cl/Cd: 129.36 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe447-il-500000.txt
Download as CSV file: xf-goe447-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 447 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.0605   0.09183   0.08851  -0.1104   0.8076   0.0323
  -9.000   0.0687   0.08917   0.08584  -0.1121   0.8027   0.0335
  -8.750   0.0617   0.08561   0.08224  -0.1190   0.7973   0.0344
  -8.500   0.0749   0.08259   0.07920  -0.1183   0.7936   0.0347
  -8.250   0.0891   0.08042   0.07703  -0.1181   0.7895   0.0350
  -8.000   0.1015   0.07839   0.07499  -0.1187   0.7853   0.0354
  -7.750   0.1128   0.07630   0.07287  -0.1198   0.7814   0.0359
  -7.500   0.1236   0.07406   0.07061  -0.1212   0.7775   0.0366
  -7.250   0.1331   0.07168   0.06825  -0.1230   0.7734   0.0376
  -7.000   0.1438   0.06600   0.06254  -0.1378   0.7683   0.0396
  -6.750   0.1556   0.06364   0.06015  -0.1368   0.7649   0.0399
  -6.500   0.1716   0.06181   0.05828  -0.1369   0.7613   0.0402
  -6.250   0.1886   0.05985   0.05633  -0.1382   0.7574   0.0407
  -6.000   0.2072   0.05770   0.05417  -0.1405   0.7532   0.0414
  -5.750   0.2278   0.05529   0.05171  -0.1437   0.7493   0.0427
  -5.500   0.2619   0.04856   0.04480  -0.1572   0.7454   0.0458
  -5.250   0.2809   0.04697   0.04322  -0.1576   0.7417   0.0462
  -5.000   0.3022   0.04529   0.04152  -0.1587   0.7377   0.0468
  -4.750   0.3263   0.04330   0.03948  -0.1609   0.7340   0.0478
  -4.500   0.3654   0.01783   0.01211  -0.1809   0.7316   0.0394
  -4.250   0.3923   0.01605   0.00990  -0.1814   0.7282   0.0396
  -4.000   0.4184   0.01456   0.00816  -0.1815   0.7246   0.0401
  -3.750   0.4457   0.01388   0.00737  -0.1816   0.7208   0.0407
  -3.500   0.4736   0.01343   0.00684  -0.1817   0.7174   0.0414
  -3.250   0.5019   0.01310   0.00641  -0.1819   0.7141   0.0424
  -3.000   0.5301   0.01280   0.00600  -0.1820   0.7106   0.0436
  -2.750   0.5576   0.01242   0.00556  -0.1819   0.7066   0.0448
  -2.500   0.5854   0.01199   0.00506  -0.1819   0.7027   0.0459
  -2.250   0.6135   0.01177   0.00482  -0.1820   0.6994   0.0475
  -2.000   0.6423   0.01167   0.00466  -0.1822   0.6963   0.0495
  -1.750   0.6703   0.01151   0.00447  -0.1822   0.6932   0.0518
  -1.500   0.6981   0.01142   0.00443  -0.1823   0.6898   0.0552
  -1.250   0.7262   0.01137   0.00437  -0.1823   0.6864   0.0603
  -1.000   0.7547   0.01147   0.00446  -0.1824   0.6832   0.0666
  -0.750   0.7834   0.01149   0.00446  -0.1826   0.6799   0.0734
  -0.500   0.8109   0.01145   0.00441  -0.1826   0.6765   0.0795
  -0.250   0.8381   0.01138   0.00438  -0.1826   0.6726   0.0843
   0.000   0.8658   0.01138   0.00437  -0.1826   0.6689   0.0885
   0.250   0.8937   0.01122   0.00418  -0.1827   0.6655   0.0928
   0.500   0.9218   0.01119   0.00415  -0.1829   0.6621   0.0968
   0.750   0.9485   0.01116   0.00416  -0.1828   0.6582   0.1010
   1.000   0.9755   0.01107   0.00408  -0.1827   0.6539   0.1048
   1.250   1.0028   0.01097   0.00399  -0.1827   0.6495   0.1091
   1.500   1.0301   0.01096   0.00396  -0.1826   0.6450   0.1115
   1.750   1.0562   0.01092   0.00396  -0.1824   0.6399   0.1141
   2.000   1.0829   0.01090   0.00393  -0.1822   0.6350   0.1168
   2.250   1.1100   0.01092   0.00392  -0.1821   0.6298   0.1224
   2.500   1.1353   0.01088   0.00397  -0.1817   0.6239   0.1318
   2.750   1.1613   0.01074   0.00408  -0.1816   0.6182   0.2366
   3.000   1.1874   0.01061   0.00424  -0.1815   0.6129   0.3838
   3.250   1.2086   0.00964   0.00443  -0.1802   0.6070   1.0000
   3.500   1.2339   0.00976   0.00449  -0.1798   0.6008   1.0000
   3.750   1.2587   0.00988   0.00458  -0.1793   0.5941   1.0000
   4.000   1.2828   0.01000   0.00467  -0.1787   0.5863   1.0000
   4.250   1.3068   0.01014   0.00478  -0.1780   0.5790   1.0000
   4.500   1.3302   0.01029   0.00490  -0.1773   0.5705   1.0000
   4.750   1.3531   0.01046   0.00504  -0.1765   0.5619   1.0000
   5.000   1.3748   0.01065   0.00520  -0.1754   0.5519   1.0000
   5.250   1.3964   0.01084   0.00538  -0.1743   0.5415   1.0000
   5.500   1.4164   0.01109   0.00558  -0.1730   0.5308   1.0000
   5.750   1.4346   0.01138   0.00580  -0.1712   0.5187   1.0000
   6.000   1.4516   0.01166   0.00606  -0.1693   0.5067   1.0000
   6.250   1.4679   0.01199   0.00636  -0.1673   0.4958   1.0000
   6.500   1.4827   0.01241   0.00671  -0.1650   0.4846   1.0000
   6.750   1.4979   0.01284   0.00709  -0.1629   0.4732   1.0000
   7.000   1.5140   0.01327   0.00751  -0.1610   0.4635   1.0000
   7.250   1.5290   0.01377   0.00796  -0.1590   0.4553   1.0000
   7.500   1.5473   0.01417   0.00837  -0.1576   0.4486   1.0000
   7.750   1.5630   0.01468   0.00886  -0.1558   0.4413   1.0000
   8.000   1.5788   0.01519   0.00938  -0.1540   0.4334   1.0000
   8.250   1.5925   0.01581   0.00997  -0.1520   0.4247   1.0000
   8.500   1.6076   0.01638   0.01056  -0.1503   0.4166   1.0000
   8.750   1.6209   0.01707   0.01123  -0.1484   0.4083   1.0000
   9.000   1.6356   0.01770   0.01190  -0.1467   0.4002   1.0000
   9.250   1.6468   0.01854   0.01272  -0.1446   0.3908   1.0000
   9.500   1.6618   0.01922   0.01344  -0.1431   0.3824   1.0000
   9.750   1.6722   0.02017   0.01437  -0.1411   0.3734   1.0000
  10.000   1.6853   0.02101   0.01526  -0.1395   0.3623   1.0000
  10.250   1.6949   0.02208   0.01633  -0.1375   0.3498   1.0000
  10.500   1.7019   0.02338   0.01760  -0.1353   0.3338   1.0000
  10.750   1.7043   0.02503   0.01918  -0.1327   0.3129   1.0000
  11.000   1.7007   0.02717   0.02120  -0.1296   0.2859   1.0000
  11.250   1.6922   0.02977   0.02364  -0.1262   0.2578   1.0000
  11.500   1.6838   0.03246   0.02621  -0.1230   0.2346   1.0000
  11.750   1.6808   0.03483   0.02851  -0.1204   0.2178   1.0000
  12.250   1.6808   0.03923   0.03284  -0.1162   0.1941   1.0000
  12.500   1.6826   0.04136   0.03497  -0.1144   0.1842   1.0000
  12.750   1.6822   0.04374   0.03733  -0.1125   0.1745   1.0000
  13.000   1.6818   0.04617   0.03974  -0.1108   0.1630   1.0000
  13.250   1.6811   0.04869   0.04224  -0.1091   0.1496   1.0000
  13.500   1.6748   0.05182   0.04527  -0.1072   0.1253   1.0000
  13.750   1.6477   0.05713   0.05027  -0.1043   0.0827   1.0000
  14.000   1.6281   0.06187   0.05493  -0.1021   0.0596   1.0000
  14.250   1.6088   0.06676   0.05969  -0.1002   0.0377   1.0000
  14.500   1.6006   0.07052   0.06345  -0.0989   0.0316   1.0000
  14.750   1.5970   0.07382   0.06681  -0.0979   0.0288   1.0000
  15.000   1.5945   0.07708   0.07014  -0.0971   0.0271   1.0000
  15.250   1.5895   0.08068   0.07382  -0.0963   0.0257   1.0000
  15.500   1.5860   0.08414   0.07736  -0.0957   0.0246   1.0000
  15.750   1.5845   0.08738   0.08069  -0.0952   0.0238   1.0000
  16.000   1.5813   0.09088   0.08429  -0.0948   0.0230   1.0000
  16.250   1.5774   0.09453   0.08802  -0.0945   0.0223   1.0000
  16.500   1.5711   0.09855   0.09212  -0.0944   0.0217   1.0000
  16.750   1.5617   0.10307   0.09673  -0.0943   0.0212   1.0000
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