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GOE 448 AIRFOIL (goe448-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 448 AIRFOIL (goe448-il)
Reynolds number: 500,000
Max Cl/Cd: 102.89 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe448-il-500000-n5.txt
Download as CSV file: xf-goe448-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 448 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.1684   0.10325   0.09957  -0.1301   0.7542   0.0131
 -10.750   0.1766   0.10044   0.09675  -0.1315   0.7503   0.0136
 -10.500   0.1767   0.09559   0.09190  -0.1336   0.7464   0.0149
 -10.250   0.1894   0.09401   0.09030  -0.1347   0.7422   0.0152
 -10.000   0.2015   0.09228   0.08853  -0.1359   0.7384   0.0155
  -9.750   0.2122   0.09011   0.08635  -0.1372   0.7347   0.0159
  -9.500   0.2217   0.08762   0.08386  -0.1387   0.7306   0.0164
  -9.000   0.2320   0.08080   0.07699  -0.1424   0.7227   0.0185
  -8.750   0.2459   0.07941   0.07559  -0.1435   0.7190   0.0188
  -8.500   0.2585   0.07765   0.07383  -0.1447   0.7152   0.0193
  -8.250   0.2689   0.07542   0.07159  -0.1462   0.7112   0.0199
  -8.000   0.2770   0.07277   0.06891  -0.1479   0.7073   0.0207
  -7.750   0.2756   0.06857   0.06471  -0.1505   0.7037   0.0223
  -7.500   0.2907   0.06732   0.06346  -0.1517   0.6998   0.0226
  -7.250   0.3065   0.06579   0.06192  -0.1535   0.6958   0.0231
  -7.000   0.3216   0.06369   0.05980  -0.1560   0.6921   0.0237
  -6.750   0.3368   0.06104   0.05710  -0.1594   0.6887   0.0245
  -5.750   0.4748   0.01546   0.00967  -0.2285   0.6752   0.0369
  -5.500   0.5027   0.01525   0.00939  -0.2287   0.6721   0.0377
  -5.250   0.5309   0.01506   0.00916  -0.2290   0.6688   0.0385
  -5.000   0.5588   0.01471   0.00871  -0.2293   0.6651   0.0395
  -4.750   0.5867   0.01412   0.00795  -0.2298   0.6614   0.0410
  -4.500   0.6145   0.01356   0.00718  -0.2302   0.6580   0.0428
  -4.250   0.6421   0.01379   0.00744  -0.2301   0.6548   0.0438
  -4.000   0.6698   0.01393   0.00760  -0.2301   0.6515   0.0447
  -3.750   0.6974   0.01387   0.00748  -0.2302   0.6479   0.0462
  -3.500   0.7251   0.01336   0.00677  -0.2305   0.6443   0.0490
  -3.250   0.7521   0.01357   0.00697  -0.2304   0.6409   0.0498
  -3.000   0.7794   0.01369   0.00707  -0.2304   0.6378   0.0510
  -2.750   0.8071   0.01346   0.00673  -0.2306   0.6345   0.0537
  -2.500   0.8344   0.01328   0.00644  -0.2306   0.6310   0.0557
  -2.250   0.8610   0.01343   0.00657  -0.2305   0.6274   0.0567
  -1.750   0.9148   0.01339   0.00638  -0.2305   0.6211   0.0602
  -1.500   0.9420   0.01327   0.00610  -0.2305   0.6177   0.0619
  -1.250   0.9684   0.01316   0.00599  -0.2305   0.6141   0.0628
  -1.000   0.9944   0.01319   0.00601  -0.2303   0.6106   0.0639
  -0.750   1.0204   0.01324   0.00602  -0.2302   0.6074   0.0655
  -0.500   1.0468   0.01321   0.00597  -0.2301   0.6041   0.0673
  -0.250   1.0727   0.01318   0.00586  -0.2299   0.6001   0.0685
   0.000   1.0978   0.01317   0.00576  -0.2296   0.5956   0.0691
   0.250   1.1224   0.01309   0.00561  -0.2292   0.5908   0.0697
   0.500   1.1471   0.01295   0.00549  -0.2288   0.5851   0.0705
   0.750   1.1709   0.01293   0.00546  -0.2283   0.5798   0.0714
   1.000   1.1946   0.01296   0.00545  -0.2277   0.5758   0.0721
   1.250   1.2197   0.01294   0.00544  -0.2275   0.5724   0.0727
   1.500   1.2441   0.01295   0.00545  -0.2270   0.5685   0.0733
   1.750   1.2666   0.01299   0.00548  -0.2262   0.5644   0.0738
   2.000   1.2877   0.01306   0.00553  -0.2252   0.5604   0.0744
   2.250   1.3102   0.01311   0.00559  -0.2244   0.5568   0.0749
   2.500   1.3326   0.01318   0.00568  -0.2236   0.5529   0.0755
   2.750   1.3545   0.01330   0.00580  -0.2227   0.5486   0.0762
   3.000   1.3756   0.01349   0.00597  -0.2218   0.5441   0.0770
   3.250   1.3982   0.01364   0.00614  -0.2211   0.5392   0.0775
   3.500   1.4196   0.01382   0.00634  -0.2202   0.5336   0.0778
   3.750   1.4400   0.01404   0.00654  -0.2192   0.5284   0.0786
   4.000   1.4621   0.01421   0.00675  -0.2185   0.5239   0.0794
   4.250   1.4836   0.01442   0.00700  -0.2178   0.5190   0.0802
   4.500   1.5034   0.01471   0.00729  -0.2167   0.5140   0.0811
   4.750   1.5230   0.01501   0.00760  -0.2156   0.5093   0.0819
   5.000   1.5432   0.01530   0.00792  -0.2147   0.5037   0.0829
   5.250   1.5611   0.01569   0.00831  -0.2133   0.4978   0.0839
   5.500   1.5794   0.01607   0.00871  -0.2121   0.4926   0.0849
   5.750   1.5985   0.01644   0.00911  -0.2111   0.4870   0.0864
   6.250   1.6322   0.01741   0.01010  -0.2083   0.4753   0.0907
   6.500   1.6470   0.01801   0.01071  -0.2066   0.4671   0.0939
   6.750   1.6596   0.01873   0.01145  -0.2047   0.4569   0.0986
   7.000   1.6692   0.01964   0.01243  -0.2024   0.4447   0.1749
   7.250   1.6765   0.02072   0.01350  -0.1999   0.4313   0.2032
   7.500   1.6869   0.02169   0.01453  -0.1979   0.4189   0.2562
   8.000   1.7023   0.02333   0.01706  -0.1934   0.3949   1.0000
   8.250   1.7068   0.02480   0.01848  -0.1908   0.3825   1.0000
   8.500   1.7107   0.02637   0.02000  -0.1883   0.3691   1.0000
   8.750   1.7156   0.02794   0.02153  -0.1859   0.3566   1.0000
   9.000   1.7193   0.02963   0.02319  -0.1835   0.3451   1.0000
   9.250   1.7209   0.03154   0.02507  -0.1810   0.3330   1.0000
   9.500   1.7196   0.03375   0.02721  -0.1783   0.3182   1.0000
   9.750   1.7188   0.03597   0.02938  -0.1757   0.3037   1.0000
  10.000   1.7182   0.03824   0.03161  -0.1733   0.2890   1.0000
  10.250   1.7154   0.04077   0.03408  -0.1707   0.2727   1.0000
  10.500   1.7065   0.04392   0.03712  -0.1678   0.2483   1.0000
  10.750   1.6798   0.04879   0.04175  -0.1635   0.2036   1.0000
  11.000   1.6555   0.05364   0.04641  -0.1597   0.1697   1.0000
  11.250   1.6457   0.05718   0.04988  -0.1573   0.1525   1.0000
  11.500   1.6390   0.06051   0.05317  -0.1552   0.1373   1.0000
  11.750   1.6197   0.06525   0.05775  -0.1524   0.1031   1.0000
  12.000   1.5909   0.07117   0.06347  -0.1494   0.0634   1.0000
  12.250   1.5659   0.07692   0.06909  -0.1468   0.0227   1.0000
  12.500   1.5632   0.08019   0.07239  -0.1456   0.0171   1.0000
  12.750   1.5665   0.08274   0.07501  -0.1447   0.0155   1.0000
  13.000   1.5685   0.08547   0.07781  -0.1438   0.0145   1.0000
  13.250   1.5705   0.08820   0.08061  -0.1429   0.0136   1.0000
  13.500   1.5714   0.09112   0.08360  -0.1421   0.0129   1.0000
  13.750   1.5748   0.09370   0.08626  -0.1414   0.0124   1.0000
  14.000   1.5766   0.09654   0.08918  -0.1408   0.0119   1.0000
  14.250   1.5787   0.09932   0.09204  -0.1402   0.0113   1.0000
  14.500   1.5791   0.10235   0.09514  -0.1396   0.0108   1.0000
  14.750   1.5790   0.10542   0.09829  -0.1391   0.0104   1.0000
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