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GOE 592 AIRFOIL (goe592-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 592 AIRFOIL (goe592-il)
Reynolds number: 100,000
Max Cl/Cd: 45.94 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe592-il-100000-n5.txt
Download as CSV file: xf-goe592-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 592 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.0901   0.10041   0.09470  -0.1213   0.9031   0.0736
  -9.750   0.1017   0.09770   0.09197  -0.1233   0.8981   0.0753
  -9.500   0.1008   0.09566   0.08993  -0.1271   0.8918   0.0782
  -9.250   0.0941   0.09393   0.08822  -0.1282   0.8821   0.0786
  -9.000   0.1001   0.09086   0.08513  -0.1316   0.8772   0.0787
  -8.750   0.0981   0.08887   0.08318  -0.1304   0.8676   0.0788
  -8.500   0.1220   0.08542   0.07970  -0.1299   0.8642   0.0796
  -8.250   0.1376   0.08249   0.07674  -0.1312   0.8602   0.0802
  -8.000   0.1405   0.08080   0.07507  -0.1297   0.8518   0.0811
  -7.750   0.1489   0.07874   0.07300  -0.1299   0.8457   0.0834
  -7.500   0.1556   0.07621   0.07044  -0.1314   0.8406   0.0849
  -7.250   0.1262   0.07277   0.06701  -0.1300   0.8280   0.0690
  -6.750   0.1091   0.06487   0.05901  -0.1345   0.8109   0.0629
  -6.500   0.1232   0.06169   0.05574  -0.1368   0.8070   0.0626
  -6.250   0.1159   0.05865   0.05263  -0.1368   0.7969   0.0628
  -6.000   0.1328   0.05706   0.05103  -0.1368   0.7923   0.0639
  -5.750   0.1531   0.05425   0.04810  -0.1391   0.7890   0.0649
  -5.500   0.1505   0.05206   0.04584  -0.1376   0.7794   0.0650
  -5.250   0.1659   0.04801   0.04157  -0.1399   0.7745   0.0650
  -5.000   0.1893   0.04396   0.03721  -0.1428   0.7714   0.0654
  -4.750   0.1913   0.04219   0.03530  -0.1404   0.7624   0.0664
  -4.500   0.2110   0.03849   0.03117  -0.1416   0.7578   0.0685
  -4.250   0.2354   0.03369   0.02552  -0.1433   0.7548   0.0704
  -4.000   0.2510   0.03304   0.02483  -0.1417   0.7486   0.0712
  -3.750   0.2690   0.03246   0.02419  -0.1404   0.7426   0.0727
  -3.500   0.2977   0.03103   0.02247  -0.1409   0.7392   0.0755
  -3.250   0.3303   0.02885   0.01961  -0.1420   0.7367   0.0786
  -3.000   0.3417   0.02854   0.01929  -0.1395   0.7295   0.0800
  -2.750   0.3647   0.02809   0.01880  -0.1387   0.7244   0.0823
  -2.500   0.3963   0.02716   0.01761  -0.1394   0.7212   0.0859
  -2.250   0.4318   0.02606   0.01618  -0.1406   0.7188   0.0894
  -2.000   0.4405   0.02616   0.01632  -0.1374   0.7111   0.0915
  -1.750   0.4656   0.02574   0.01582  -0.1369   0.7063   0.0948
  -1.500   0.4987   0.02506   0.01490  -0.1376   0.7032   0.0988
  -1.250   0.5353   0.02436   0.01415  -0.1390   0.7008   0.1028
  -1.000   0.5405   0.02465   0.01447  -0.1352   0.6927   0.1050
  -0.750   0.5670   0.02435   0.01408  -0.1348   0.6882   0.1093
  -0.500   0.6010   0.02383   0.01347  -0.1357   0.6851   0.1138
  -0.250   0.6383   0.02329   0.01293  -0.1372   0.6826   0.1185
   0.000   0.6385   0.02381   0.01350  -0.1325   0.6740   0.1214
   0.250   0.6662   0.02360   0.01322  -0.1323   0.6698   0.1266
   0.500   0.7009   0.02315   0.01281  -0.1334   0.6668   0.1322
   0.750   0.7248   0.02313   0.01278  -0.1327   0.6621   0.1392
   1.000   0.7335   0.02346   0.01315  -0.1294   0.6550   0.1443
   1.250   0.7632   0.02326   0.01295  -0.1296   0.6511   0.1538
   1.500   0.8018   0.02289   0.01258  -0.1313   0.6482   0.1710
   1.750   0.8099   0.02331   0.01309  -0.1280   0.6414   0.1866
   2.000   0.8283   0.02341   0.01331  -0.1265   0.6358   0.2211
   2.250   0.8845   0.02169   0.01326  -0.1319   0.6327   1.0000
   2.500   0.9228   0.02157   0.01293  -0.1335   0.6297   1.0000
   2.750   0.9188   0.02241   0.01377  -0.1282   0.6217   1.0000
   3.000   0.9413   0.02264   0.01390  -0.1272   0.6166   1.0000
   3.250   0.9780   0.02255   0.01367  -0.1286   0.6131   1.0000
   3.500   0.9892   0.02307   0.01415  -0.1258   0.6070   1.0000
   3.750   0.9983   0.02366   0.01472  -0.1228   0.6004   1.0000
   4.000   1.0309   0.02364   0.01460  -0.1235   0.5964   1.0000
   4.250   1.0683   0.02352   0.01438  -0.1249   0.5928   1.0000
   4.500   1.0548   0.02476   0.01569  -0.1185   0.5838   1.0000
   4.750   1.0839   0.02480   0.01566  -0.1187   0.5792   1.0000
   5.000   1.1247   0.02452   0.01529  -0.1206   0.5759   1.0000
   5.250   1.1088   0.02597   0.01684  -0.1141   0.5665   1.0000
   5.500   1.1368   0.02601   0.01682  -0.1141   0.5616   1.0000
   5.750   1.1780   0.02564   0.01637  -0.1159   0.5580   1.0000
   6.000   1.1596   0.02731   0.01815  -0.1095   0.5481   1.0000
   6.250   1.1903   0.02719   0.01798  -0.1098   0.5432   1.0000
   6.500   1.2023   0.02784   0.01866  -0.1076   0.5366   1.0000
   6.750   1.2092   0.02871   0.01956  -0.1049   0.5289   1.0000
   7.000   1.2443   0.02838   0.01917  -0.1057   0.5244   1.0000
   7.250   1.2362   0.02999   0.02087  -0.1013   0.5155   1.0000
   7.500   1.2587   0.03020   0.02109  -0.1006   0.5097   1.0000
   7.750   1.2899   0.03003   0.02089  -0.1009   0.5051   1.0000
   8.000   1.2780   0.03199   0.02296  -0.0965   0.4956   1.0000
   8.250   1.3093   0.03170   0.02264  -0.0967   0.4905   1.0000
   8.500   1.3042   0.03342   0.02446  -0.0932   0.4814   1.0000
   8.750   1.3266   0.03357   0.02459  -0.0925   0.4746   1.0000
   9.000   1.3314   0.03477   0.02585  -0.0901   0.4661   1.0000
   9.250   1.3472   0.03526   0.02634  -0.0888   0.4577   1.0000
   9.500   1.3516   0.03656   0.02769  -0.0865   0.4486   1.0000
   9.750   1.3674   0.03707   0.02820  -0.0853   0.4401   1.0000
  10.000   1.3696   0.03863   0.02982  -0.0831   0.4309   1.0000
  10.250   1.3869   0.03905   0.03024  -0.0820   0.4225   1.0000
  10.500   1.3842   0.04106   0.03234  -0.0796   0.4124   1.0000
  10.750   1.4064   0.04109   0.03232  -0.0789   0.4040   1.0000
  11.000   1.3972   0.04376   0.03510  -0.0763   0.3930   1.0000
  11.250   1.4100   0.04459   0.03593  -0.0751   0.3836   1.0000
  11.500   1.4114   0.04644   0.03781  -0.0733   0.3724   1.0000
  11.750   1.4107   0.04864   0.04009  -0.0717   0.3618   1.0000
  12.000   1.4250   0.04938   0.04079  -0.0707   0.3526   1.0000
  12.250   1.4193   0.05225   0.04378  -0.0691   0.3421   1.0000
  12.500   1.4256   0.05391   0.04546  -0.0680   0.3327   1.0000
  12.750   1.4285   0.05596   0.04755  -0.0668   0.3224   1.0000
  13.000   1.4278   0.05851   0.05018  -0.0657   0.3123   1.0000
  13.250   1.4338   0.06026   0.05192  -0.0648   0.3021   1.0000
  13.500   1.4313   0.06312   0.05486  -0.0639   0.2913   1.0000
  13.750   1.4313   0.06574   0.05752  -0.0631   0.2807   1.0000
  14.000   1.4342   0.06797   0.05974  -0.0623   0.2698   1.0000
  14.250   1.4309   0.07109   0.06291  -0.0617   0.2582   1.0000
  14.500   1.4281   0.07421   0.06609  -0.0611   0.2465   1.0000
  14.750   1.4262   0.07723   0.06911  -0.0607   0.2347   1.0000
  15.000   1.4237   0.08037   0.07222  -0.0603   0.2224   1.0000
  15.250   1.4183   0.08404   0.07592  -0.0602   0.2098   1.0000
  15.500   1.4131   0.08773   0.07963  -0.0601   0.1973   1.0000
  15.750   1.4082   0.09142   0.08333  -0.0602   0.1853   1.0000
  16.000   1.4039   0.09506   0.08696  -0.0603   0.1742   1.0000
  16.250   1.3999   0.09872   0.09059  -0.0606   0.1641   1.0000
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