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GOE 447 AIRFOIL (goe447-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 447 AIRFOIL (goe447-il)
Reynolds number: 200,000
Max Cl/Cd: 84.2 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe447-il-200000-n5.txt
Download as CSV file: xf-goe447-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.0691   0.09463   0.08995  -0.1120   0.8120   0.0435
  -9.000   0.0774   0.09219   0.08751  -0.1133   0.8068   0.0446
  -8.750   0.0831   0.08969   0.08499  -0.1155   0.8019   0.0458
  -8.500   0.0868   0.08719   0.08245  -0.1183   0.7976   0.0462
  -8.000   0.0961   0.08188   0.07715  -0.1238   0.7880   0.0464
  -7.750   0.1135   0.07924   0.07449  -0.1221   0.7847   0.0469
  -7.500   0.1271   0.07720   0.07241  -0.1221   0.7812   0.0478
  -7.250   0.1375   0.07515   0.07035  -0.1230   0.7774   0.0488
  -7.000   0.1452   0.07308   0.06830  -0.1244   0.7727   0.0498
  -6.750   0.1566   0.07054   0.06576  -0.1271   0.7683   0.0506
  -6.250   0.1821   0.06109   0.05614  -0.1396   0.7613   0.0403
  -6.000   0.1986   0.05877   0.05382  -0.1414   0.7573   0.0398
  -5.750   0.2177   0.05564   0.05065  -0.1454   0.7534   0.0397
  -5.500   0.2402   0.05181   0.04673  -0.1507   0.7500   0.0399
  -5.250   0.2635   0.04860   0.04341  -0.1546   0.7469   0.0396
  -5.000   0.2884   0.04518   0.03987  -0.1588   0.7438   0.0392
  -4.750   0.3142   0.04132   0.03590  -0.1631   0.7398   0.0388
  -4.500   0.3428   0.03668   0.03104  -0.1680   0.7362   0.0387
  -4.250   0.3754   0.02373   0.01682  -0.1771   0.7333   0.0401
  -4.000   0.4025   0.02060   0.01298  -0.1783   0.7303   0.0409
  -3.750   0.4299   0.01988   0.01209  -0.1785   0.7269   0.0415
  -3.500   0.4556   0.01925   0.01135  -0.1784   0.7222   0.0422
  -3.250   0.4825   0.01859   0.01052  -0.1784   0.7177   0.0430
  -3.000   0.5105   0.01790   0.00961  -0.1786   0.7140   0.0442
  -2.750   0.5387   0.01723   0.00872  -0.1787   0.7107   0.0456
  -2.500   0.5645   0.01693   0.00838  -0.1784   0.7059   0.0472
  -2.250   0.5913   0.01683   0.00825  -0.1783   0.7013   0.0491
  -2.000   0.6194   0.01647   0.00777  -0.1783   0.6974   0.0517
  -1.750   0.6472   0.01624   0.00748  -0.1784   0.6938   0.0540
  -1.500   0.6732   0.01613   0.00737  -0.1781   0.6895   0.0571
  -1.250   0.7001   0.01597   0.00717  -0.1779   0.6855   0.0614
  -1.000   0.7278   0.01587   0.00697  -0.1779   0.6821   0.0677
  -0.750   0.7563   0.01583   0.00690  -0.1781   0.6793   0.0734
  -0.500   0.7823   0.01577   0.00682  -0.1778   0.6754   0.0789
  -0.250   0.8081   0.01571   0.00679  -0.1775   0.6711   0.0836
   0.000   0.8349   0.01565   0.00668  -0.1774   0.6671   0.0890
   0.250   0.8627   0.01555   0.00660  -0.1775   0.6636   0.0965
   0.500   0.8889   0.01552   0.00656  -0.1773   0.6595   0.1020
   0.750   0.9140   0.01543   0.00653  -0.1769   0.6548   0.1056
   1.000   0.9404   0.01537   0.00648  -0.1767   0.6507   0.1082
   1.250   0.9681   0.01532   0.00639  -0.1768   0.6471   0.1110
   1.500   0.9937   0.01535   0.00643  -0.1764   0.6428   0.1143
   1.750   1.0185   0.01537   0.00650  -0.1759   0.6377   0.1183
   2.000   1.0446   0.01536   0.00650  -0.1757   0.6331   0.1234
   2.250   1.0721   0.01535   0.00646  -0.1757   0.6289   0.1307
   2.750   1.1199   0.01530   0.00683  -0.1746   0.6173   0.2539
   3.000   1.1456   0.01520   0.00691  -0.1743   0.6121   0.3527
   3.500   1.1894   0.01445   0.00718  -0.1720   0.5984   1.0000
   3.750   1.2117   0.01463   0.00734  -0.1710   0.5910   1.0000
   4.000   1.2345   0.01480   0.00746  -0.1702   0.5835   1.0000
   4.250   1.2564   0.01500   0.00762  -0.1691   0.5757   1.0000
   4.500   1.2775   0.01520   0.00777  -0.1679   0.5667   1.0000
   4.750   1.2978   0.01543   0.00799  -0.1666   0.5578   1.0000
   5.000   1.3185   0.01566   0.00817  -0.1654   0.5496   1.0000
   5.250   1.3380   0.01593   0.00844  -0.1640   0.5412   1.0000
   5.500   1.3564   0.01619   0.00866  -0.1624   0.5325   1.0000
   5.750   1.3725   0.01651   0.00898  -0.1604   0.5228   1.0000
   6.000   1.3894   0.01685   0.00927  -0.1585   0.5136   1.0000
   6.250   1.4056   0.01724   0.00964  -0.1566   0.5040   1.0000
   6.500   1.4218   0.01766   0.01004  -0.1548   0.4950   1.0000
   6.750   1.4375   0.01811   0.01046  -0.1529   0.4862   1.0000
   7.000   1.4531   0.01860   0.01094  -0.1511   0.4776   1.0000
   7.250   1.4680   0.01914   0.01143  -0.1491   0.4691   1.0000
   7.500   1.4824   0.01971   0.01202  -0.1472   0.4603   1.0000
   8.000   1.5109   0.02097   0.01325  -0.1435   0.4444   1.0000
   8.250   1.5256   0.02162   0.01389  -0.1418   0.4378   1.0000
   8.500   1.5404   0.02228   0.01459  -0.1402   0.4314   1.0000
   8.750   1.5540   0.02302   0.01535  -0.1385   0.4242   1.0000
   9.000   1.5674   0.02378   0.01611  -0.1367   0.4175   1.0000
   9.250   1.5803   0.02459   0.01699  -0.1350   0.4104   1.0000
   9.500   1.5927   0.02545   0.01786  -0.1333   0.4036   1.0000
   9.750   1.6048   0.02633   0.01882  -0.1316   0.3967   1.0000
  10.000   1.6148   0.02736   0.01988  -0.1297   0.3885   1.0000
  10.250   1.6235   0.02849   0.02106  -0.1277   0.3792   1.0000
  10.500   1.6289   0.02984   0.02241  -0.1255   0.3683   1.0000
  10.750   1.6340   0.03128   0.02393  -0.1233   0.3552   1.0000
  11.000   1.6368   0.03293   0.02560  -0.1211   0.3401   1.0000
  11.250   1.6376   0.03479   0.02745  -0.1187   0.3229   1.0000
  11.500   1.6354   0.03696   0.02958  -0.1163   0.3028   1.0000
  11.750   1.6306   0.03945   0.03199  -0.1138   0.2807   1.0000
  12.000   1.6235   0.04225   0.03471  -0.1113   0.2607   1.0000
  12.250   1.6168   0.04512   0.03752  -0.1090   0.2434   1.0000
  12.500   1.6113   0.04799   0.04034  -0.1069   0.2288   1.0000
  12.750   1.6077   0.05077   0.04310  -0.1051   0.2166   1.0000
  13.000   1.6073   0.05331   0.04565  -0.1036   0.2071   1.0000
  13.250   1.6055   0.05602   0.04837  -0.1021   0.1989   1.0000
  13.500   1.6059   0.05858   0.05097  -0.1008   0.1901   1.0000
  13.750   1.6038   0.06146   0.05386  -0.0995   0.1816   1.0000
  14.000   1.6019   0.06436   0.05680  -0.0984   0.1723   1.0000
  14.250   1.6019   0.06710   0.05958  -0.0974   0.1642   1.0000
  14.500   1.5991   0.07021   0.06272  -0.0964   0.1555   1.0000
  14.750   1.5982   0.07315   0.06571  -0.0955   0.1432   1.0000
  15.000   1.5911   0.07691   0.06943  -0.0947   0.1182   1.0000
  15.250   1.5666   0.08282   0.07507  -0.0936   0.0849   1.0000
  15.500   1.5515   0.08768   0.07985  -0.0929   0.0709   1.0000
  15.750   1.5396   0.09223   0.08438  -0.0924   0.0504   1.0000
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