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GOE 447 AIRFOIL (goe447-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 447 AIRFOIL (goe447-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.35 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe447-il-1000000-n5.txt
Download as CSV file: xf-goe447-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.0140   0.08956   0.08652  -0.1079   0.7330   0.0176
  -9.250  -0.1511   0.02244   0.01841  -0.1747   0.7257   0.0223
  -9.000  -0.1278   0.02005   0.01574  -0.1763   0.7220   0.0224
  -8.750  -0.1054   0.01783   0.01322  -0.1774   0.7182   0.0227
  -8.500  -0.0801   0.01678   0.01202  -0.1778   0.7146   0.0229
  -8.250  -0.0540   0.01604   0.01115  -0.1781   0.7113   0.0231
  -8.000  -0.0271   0.01535   0.01036  -0.1784   0.7084   0.0232
  -7.750  -0.0001   0.01476   0.00967  -0.1786   0.7052   0.0234
  -7.500   0.0271   0.01422   0.00902  -0.1788   0.7018   0.0236
  -7.250   0.0543   0.01373   0.00843  -0.1790   0.6984   0.0237
  -7.000   0.0815   0.01329   0.00788  -0.1791   0.6948   0.0239
  -6.750   0.1093   0.01286   0.00737  -0.1793   0.6911   0.0241
  -6.500   0.1370   0.01246   0.00688  -0.1795   0.6864   0.0243
  -6.250   0.1645   0.01212   0.00643  -0.1795   0.6816   0.0245
  -6.000   0.1922   0.01179   0.00601  -0.1796   0.6776   0.0247
  -5.750   0.2204   0.01147   0.00563  -0.1798   0.6742   0.0249
  -5.500   0.2486   0.01118   0.00527  -0.1800   0.6710   0.0251
  -5.250   0.2767   0.01092   0.00494  -0.1801   0.6673   0.0254
  -5.000   0.3045   0.01071   0.00464  -0.1801   0.6633   0.0256
  -4.750   0.3328   0.01049   0.00437  -0.1803   0.6597   0.0258
  -4.500   0.3613   0.01029   0.00412  -0.1804   0.6561   0.0260
  -4.250   0.3896   0.01012   0.00390  -0.1806   0.6526   0.0261
  -4.000   0.4176   0.00995   0.00368  -0.1806   0.6488   0.0263
  -3.750   0.4455   0.00973   0.00340  -0.1807   0.6454   0.0268
  -3.500   0.4741   0.00954   0.00320  -0.1809   0.6422   0.0273
  -3.250   0.5025   0.00941   0.00304  -0.1811   0.6380   0.0279
  -3.000   0.5304   0.00931   0.00291  -0.1811   0.6333   0.0284
  -2.750   0.5582   0.00923   0.00279  -0.1811   0.6291   0.0289
  -2.500   0.5868   0.00913   0.00267  -0.1813   0.6262   0.0293
  -2.250   0.6153   0.00904   0.00257  -0.1815   0.6231   0.0298
  -2.000   0.6436   0.00897   0.00248  -0.1816   0.6198   0.0303
  -1.750   0.6716   0.00891   0.00240  -0.1816   0.6164   0.0310
  -1.250   0.7278   0.00880   0.00227  -0.1818   0.6102   0.0335
  -1.000   0.7561   0.00875   0.00222  -0.1820   0.6066   0.0352
  -0.750   0.7840   0.00870   0.00219  -0.1820   0.6024   0.0394
  -0.500   0.8114   0.00868   0.00221  -0.1820   0.5981   0.0530
  -0.250   0.8392   0.00870   0.00225  -0.1821   0.5940   0.0602
   0.000   0.8670   0.00873   0.00230  -0.1821   0.5883   0.0640
   0.250   0.8936   0.00881   0.00233  -0.1819   0.5810   0.0665
   0.500   0.9210   0.00884   0.00236  -0.1819   0.5741   0.0683
   0.750   0.9478   0.00889   0.00240  -0.1818   0.5670   0.0708
   1.000   0.9747   0.00893   0.00244  -0.1817   0.5615   0.0724
   1.250   1.0018   0.00898   0.00248  -0.1816   0.5547   0.0742
   1.500   1.0277   0.00908   0.00254  -0.1814   0.5473   0.0759
   1.750   1.0542   0.00915   0.00260  -0.1812   0.5385   0.0767
   2.000   1.0794   0.00924   0.00265  -0.1808   0.5280   0.0784
   2.250   1.1036   0.00938   0.00275  -0.1802   0.5137   0.0808
   2.500   1.1264   0.00959   0.00289  -0.1794   0.4946   0.0825
   2.750   1.1483   0.00985   0.00305  -0.1783   0.4755   0.0840
   3.000   1.1706   0.01008   0.00322  -0.1774   0.4613   0.0855
   3.250   1.1930   0.01031   0.00339  -0.1765   0.4495   0.0867
   3.750   1.2388   0.01068   0.00372  -0.1749   0.4329   0.0919
   4.000   1.2616   0.01085   0.00389  -0.1741   0.4251   0.0972
   4.250   1.2825   0.01105   0.00410  -0.1729   0.4176   0.1139
   4.500   1.3049   0.01105   0.00434  -0.1721   0.4125   0.2499
   4.750   1.3252   0.01119   0.00456  -0.1709   0.4074   0.2932
   5.000   1.3453   0.01140   0.00484  -0.1696   0.4008   0.3528
   5.500   1.3861   0.01097   0.00555  -0.1674   0.3872   1.0000
   5.750   1.4074   0.01122   0.00579  -0.1664   0.3825   1.0000
   6.000   1.4287   0.01148   0.00603  -0.1655   0.3765   1.0000
   6.250   1.4470   0.01186   0.00637  -0.1640   0.3687   1.0000
   6.500   1.4674   0.01216   0.00666  -0.1629   0.3610   1.0000
   6.750   1.4849   0.01259   0.00705  -0.1613   0.3522   1.0000
   7.000   1.5049   0.01292   0.00738  -0.1602   0.3456   1.0000
   7.250   1.5204   0.01347   0.00787  -0.1584   0.3331   1.0000
   7.500   1.5322   0.01421   0.00851  -0.1561   0.3119   1.0000
   7.750   1.5384   0.01526   0.00941  -0.1530   0.2850   1.0000
   8.000   1.5413   0.01657   0.01056  -0.1496   0.2558   1.0000
   8.250   1.5418   0.01809   0.01193  -0.1460   0.2266   1.0000
   8.500   1.5458   0.01950   0.01322  -0.1431   0.2043   1.0000
   8.750   1.5548   0.02065   0.01431  -0.1409   0.1913   1.0000
   9.000   1.5654   0.02173   0.01536  -0.1391   0.1818   1.0000
   9.250   1.5763   0.02283   0.01643  -0.1373   0.1736   1.0000
   9.500   1.5878   0.02390   0.01750  -0.1357   0.1666   1.0000
   9.750   1.6001   0.02493   0.01852  -0.1343   0.1613   1.0000
  10.000   1.6110   0.02607   0.01966  -0.1327   0.1563   1.0000
  10.250   1.6241   0.02708   0.02068  -0.1314   0.1521   1.0000
  10.500   1.6356   0.02823   0.02185  -0.1300   0.1468   1.0000
  10.750   1.6435   0.02964   0.02324  -0.1283   0.1391   1.0000
  11.000   1.6511   0.03112   0.02469  -0.1266   0.1291   1.0000
  11.500   1.6344   0.03679   0.03009  -0.1205   0.0777   1.0000
  11.750   1.6376   0.03879   0.03209  -0.1187   0.0703   1.0000
  12.000   1.6391   0.04098   0.03427  -0.1169   0.0606   1.0000
  12.250   1.6230   0.04484   0.03798  -0.1138   0.0325   1.0000
  12.500   1.6230   0.04730   0.04043  -0.1121   0.0246   1.0000
  12.750   1.6267   0.04947   0.04263  -0.1108   0.0211   1.0000
  13.000   1.6317   0.05153   0.04471  -0.1096   0.0188   1.0000
  13.250   1.6370   0.05361   0.04683  -0.1085   0.0174   1.0000
  13.500   1.6419   0.05572   0.04898  -0.1074   0.0162   1.0000
  13.750   1.6468   0.05788   0.05118  -0.1064   0.0154   1.0000
  14.000   1.6523   0.05996   0.05331  -0.1055   0.0147   1.0000
  14.250   1.6562   0.06228   0.05568  -0.1046   0.0140   1.0000
  14.500   1.6599   0.06462   0.05806  -0.1037   0.0133   1.0000
  14.750   1.6620   0.06718   0.06068  -0.1028   0.0127   1.0000
  15.000   1.6665   0.06947   0.06302  -0.1020   0.0123   1.0000
  15.250   1.6694   0.07196   0.06558  -0.1013   0.0120   1.0000
  15.500   1.6724   0.07446   0.06814  -0.1006   0.0116   1.0000
  15.750   1.6740   0.07717   0.07090  -0.0999   0.0112   1.0000
  16.000   1.6755   0.07991   0.07370  -0.0993   0.0109   1.0000
  16.250   1.6759   0.08281   0.07666  -0.0988   0.0106   1.0000
  16.500   1.6750   0.08588   0.07979  -0.0983   0.0103   1.0000
  16.750   1.6747   0.08886   0.08284  -0.0978   0.0100   1.0000
  17.000   1.6747   0.09189   0.08594  -0.0975   0.0098   1.0000
  17.250   1.6753   0.09483   0.08895  -0.0972   0.0096   1.0000
  17.500   1.6744   0.09801   0.09221  -0.0971   0.0094   1.0000
  17.750   1.6739   0.10115   0.09542  -0.0970   0.0092   1.0000
  18.000   1.6728   0.10438   0.09871  -0.0969   0.0090   1.0000
  18.250   1.6708   0.10775   0.10216  -0.0970   0.0088   1.0000
  18.500   1.6692   0.11106   0.10553  -0.0971   0.0085   1.0000
  18.750   1.6666   0.11457   0.10911  -0.0974   0.0083   1.0000
  19.000   1.6635   0.11817   0.11278  -0.0978   0.0082   1.0000
  19.250   1.6606   0.12176   0.11643  -0.0983   0.0080   1.0000
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