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GOE 447 AIRFOIL (goe447-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 447 AIRFOIL (goe447-il)
Reynolds number: 1,000,000
Max Cl/Cd: 161.26 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe447-il-1000000.txt
Download as CSV file: xf-goe447-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.0391   0.08752   0.08471  -0.1124   0.7674   0.0256
  -9.000   0.0458   0.08446   0.08161  -0.1144   0.7633   0.0256
  -8.750   0.0525   0.08102   0.07817  -0.1153   0.7598   0.0259
  -8.500   0.0650   0.07901   0.07617  -0.1160   0.7563   0.0260
  -8.250   0.0771   0.07703   0.07418  -0.1169   0.7524   0.0262
  -8.000   0.0886   0.07503   0.07216  -0.1180   0.7485   0.0264
  -7.750   0.0998   0.07296   0.07006  -0.1193   0.7442   0.0267
  -7.500   0.1107   0.07077   0.06789  -0.1209   0.7403   0.0272
  -7.250   0.1197   0.06851   0.06563  -0.1227   0.7358   0.0280
  -6.750   0.1461   0.05779   0.05482  -0.1388   0.7273   0.0301
  -6.500   0.1445   0.01692   0.01241  -0.1791   0.7252   0.0286
  -6.250   0.1701   0.01540   0.01061  -0.1796   0.7213   0.0288
  -6.000   0.1967   0.01446   0.00946  -0.1798   0.7174   0.0291
  -5.750   0.2239   0.01393   0.00875  -0.1800   0.7134   0.0295
  -5.500   0.2518   0.01350   0.00819  -0.1801   0.7100   0.0297
  -5.250   0.2787   0.01248   0.00699  -0.1803   0.7066   0.0300
  -5.000   0.3059   0.01167   0.00603  -0.1805   0.7029   0.0304
  -4.750   0.3335   0.01120   0.00547  -0.1806   0.6991   0.0308
  -4.500   0.3613   0.01088   0.00507  -0.1807   0.6952   0.0312
  -4.250   0.3897   0.01055   0.00471  -0.1809   0.6924   0.0316
  -4.000   0.4180   0.01027   0.00439  -0.1810   0.6889   0.0320
  -3.750   0.4462   0.01003   0.00409  -0.1811   0.6851   0.0325
  -3.500   0.4742   0.00983   0.00381  -0.1812   0.6810   0.0330
  -3.250   0.5025   0.00964   0.00358  -0.1813   0.6775   0.0335
  -3.000   0.5311   0.00946   0.00336  -0.1814   0.6742   0.0341
  -2.750   0.5594   0.00925   0.00312  -0.1816   0.6707   0.0348
  -2.500   0.5876   0.00905   0.00289  -0.1817   0.6675   0.0362
  -2.250   0.6157   0.00895   0.00276  -0.1818   0.6642   0.0373
  -2.000   0.6442   0.00885   0.00264  -0.1819   0.6612   0.0385
  -1.750   0.6728   0.00873   0.00252  -0.1821   0.6580   0.0399
  -1.500   0.7011   0.00861   0.00242  -0.1822   0.6545   0.0432
  -1.250   0.7292   0.00855   0.00238  -0.1823   0.6511   0.0491
  -1.000   0.7573   0.00861   0.00245  -0.1823   0.6476   0.0596
  -0.750   0.7858   0.00868   0.00256  -0.1825   0.6447   0.0659
  -0.500   0.8142   0.00870   0.00259  -0.1826   0.6416   0.0697
  -0.250   0.8424   0.00872   0.00264  -0.1828   0.6380   0.0731
   0.000   0.8700   0.00877   0.00267  -0.1828   0.6338   0.0758
   0.250   0.8975   0.00884   0.00271  -0.1828   0.6295   0.0775
   0.500   0.9255   0.00873   0.00261  -0.1829   0.6255   0.0802
   0.750   0.9532   0.00869   0.00259  -0.1829   0.6212   0.0827
   1.000   0.9802   0.00873   0.00261  -0.1829   0.6164   0.0854
   1.250   1.0076   0.00874   0.00263  -0.1829   0.6115   0.0877
   1.500   1.0350   0.00876   0.00265  -0.1829   0.6060   0.0893
   1.750   1.0618   0.00874   0.00261  -0.1827   0.6009   0.0922
   2.000   1.0888   0.00875   0.00262  -0.1827   0.5963   0.0947
   2.250   1.1163   0.00874   0.00264  -0.1827   0.5913   0.0970
   2.500   1.1428   0.00879   0.00268  -0.1826   0.5856   0.0993
   2.750   1.1690   0.00885   0.00273  -0.1824   0.5800   0.1018
   3.000   1.1956   0.00888   0.00278  -0.1822   0.5727   0.1078
   3.250   1.2207   0.00895   0.00286  -0.1818   0.5646   0.1273
   3.500   1.2468   0.00881   0.00306  -0.1818   0.5559   0.3011
   3.750   1.2709   0.00820   0.00338  -0.1817   0.5472   0.7833
   4.000   1.2917   0.00801   0.00351  -0.1802   0.5367   1.0000
   4.250   1.3155   0.00820   0.00364  -0.1795   0.5242   1.0000
   4.500   1.3378   0.00844   0.00381  -0.1786   0.5095   1.0000
   4.750   1.3591   0.00872   0.00400  -0.1775   0.4946   1.0000
   5.000   1.3792   0.00903   0.00424  -0.1762   0.4793   1.0000
   5.250   1.3984   0.00937   0.00449  -0.1747   0.4648   1.0000
   5.500   1.4156   0.00971   0.00476  -0.1727   0.4525   1.0000
   5.750   1.4343   0.01002   0.00502  -0.1712   0.4426   1.0000
   6.000   1.4534   0.01033   0.00530  -0.1697   0.4343   1.0000
   6.250   1.4723   0.01065   0.00559  -0.1682   0.4262   1.0000
   6.500   1.4917   0.01097   0.00589  -0.1669   0.4196   1.0000
   6.750   1.5124   0.01124   0.00616  -0.1658   0.4139   1.0000
   7.250   1.5498   0.01196   0.00685  -0.1630   0.3992   1.0000
   7.500   1.5672   0.01238   0.00724  -0.1615   0.3920   1.0000
   7.750   1.5863   0.01274   0.00761  -0.1602   0.3854   1.0000
   8.000   1.6033   0.01320   0.00805  -0.1587   0.3764   1.0000
   8.250   1.6210   0.01365   0.00849  -0.1573   0.3683   1.0000
   8.500   1.6359   0.01424   0.00904  -0.1555   0.3579   1.0000
   8.750   1.6521   0.01479   0.00958  -0.1540   0.3462   1.0000
   9.000   1.6642   0.01556   0.01030  -0.1519   0.3305   1.0000
   9.250   1.6705   0.01668   0.01130  -0.1490   0.3072   1.0000
   9.500   1.6682   0.01838   0.01280  -0.1451   0.2723   1.0000
   9.750   1.6631   0.02036   0.01459  -0.1411   0.2399   1.0000
  10.000   1.6623   0.02217   0.01629  -0.1379   0.2173   1.0000
  10.250   1.6663   0.02374   0.01779  -0.1354   0.2018   1.0000
  10.500   1.6714   0.02524   0.01924  -0.1331   0.1899   1.0000
  10.750   1.6794   0.02659   0.02058  -0.1313   0.1809   1.0000
  11.000   1.6865   0.02805   0.02201  -0.1294   0.1724   1.0000
  11.250   1.6933   0.02953   0.02348  -0.1275   0.1643   1.0000
  11.500   1.7017   0.03094   0.02490  -0.1259   0.1573   1.0000
  11.750   1.7066   0.03265   0.02658  -0.1240   0.1483   1.0000
  12.000   1.7118   0.03436   0.02826  -0.1222   0.1364   1.0000
  12.250   1.6996   0.03755   0.03125  -0.1190   0.1029   1.0000
  12.500   1.6798   0.04159   0.03513  -0.1154   0.0755   1.0000
  12.750   1.6687   0.04499   0.03847  -0.1128   0.0567   1.0000
  13.000   1.6498   0.04925   0.04258  -0.1098   0.0308   1.0000
  13.250   1.6475   0.05204   0.04537  -0.1082   0.0249   1.0000
  13.500   1.6502   0.05439   0.04775  -0.1069   0.0226   1.0000
  13.750   1.6511   0.05693   0.05034  -0.1056   0.0208   1.0000
  14.000   1.6560   0.05908   0.05255  -0.1046   0.0198   1.0000
  14.250   1.6581   0.06158   0.05510  -0.1036   0.0189   1.0000
  14.500   1.6593   0.06420   0.05777  -0.1025   0.0180   1.0000
  14.750   1.6590   0.06703   0.06067  -0.1015   0.0173   1.0000
  15.000   1.6622   0.06949   0.06319  -0.1007   0.0168   1.0000
  15.250   1.6644   0.07206   0.06583  -0.0999   0.0164   1.0000
  15.500   1.6654   0.07483   0.06866  -0.0992   0.0159   1.0000
  15.750   1.6660   0.07765   0.07154  -0.0985   0.0155   1.0000
  16.000   1.6638   0.08088   0.07484  -0.0979   0.0150   1.0000
  16.250   1.6592   0.08443   0.07847  -0.0972   0.0146   1.0000
  16.500   1.6550   0.08794   0.08207  -0.0967   0.0142   1.0000
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