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GOE 366 AIRFOIL (goe366-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 366 AIRFOIL (goe366-il)
Reynolds number: 100,000
Max Cl/Cd: 51.73 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe366-il-100000.txt
Download as CSV file: xf-goe366-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 366 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.0892   0.10551   0.10095  -0.0720   0.9289   0.0623
  -7.000  -0.1007   0.10503   0.10051  -0.0722   0.9172   0.0628
  -6.750  -0.1014   0.10409   0.09957  -0.0783   0.9056   0.0632
  -6.500  -0.0827   0.09922   0.09472  -0.0776   0.9012   0.0640
  -6.250  -0.0551   0.09476   0.09026  -0.0790   0.8981   0.0656
  -6.000  -0.0538   0.09293   0.08844  -0.0783   0.8881   0.0668
  -5.750  -0.0314   0.08963   0.08511  -0.0829   0.8818   0.0692
  -5.500  -0.0231   0.08787   0.08332  -0.0867   0.8712   0.0716
  -5.250   0.0069   0.08417   0.07952  -0.0960   0.8640   0.0736
  -5.000   0.0366   0.07972   0.07509  -0.0968   0.8616   0.0761
  -4.750   0.0358   0.07827   0.07366  -0.0949   0.8489   0.0777
  -4.500   0.1026   0.07524   0.07018  -0.1128   0.8443   0.0843
  -3.750   0.1968   0.06523   0.05989  -0.1229   0.8260   0.0973
  -3.250   0.2369   0.05853   0.05334  -0.1226   0.8111   0.1042
  -3.000   0.2616   0.05736   0.05186  -0.1252   0.7982   0.1124
  -2.750   0.3008   0.05325   0.04781  -0.1281   0.7957   0.1191
  -2.500   0.3395   0.05045   0.04485  -0.1319   0.7898   0.1318
  -2.250   0.3698   0.04838   0.04263  -0.1337   0.7808   0.1472
  -2.000   0.4140   0.04518   0.03934  -0.1374   0.7777   0.1669
  -1.750   0.4345   0.04365   0.03774  -0.1371   0.7664   0.1844
  -1.500   0.4766   0.04090   0.03486  -0.1402   0.7620   0.2180
  -1.250   0.5184   0.03801   0.03191  -0.1431   0.7590   0.2699
  -0.500   0.5815   0.03266   0.02673  -0.1392   0.7292   0.4201
  -0.250   0.6248   0.03033   0.02428  -0.1412   0.7245   0.4681
   0.000   0.6480   0.02925   0.02315  -0.1405   0.7116   0.4846
   0.250   0.7375   0.02845   0.02096  -0.1512   0.7062   0.2990
   0.500   0.7740   0.02844   0.02017  -0.1500   0.6932   0.1735
   0.750   0.8104   0.02741   0.01868  -0.1499   0.6845   0.1355
   1.000   0.8417   0.02662   0.01760  -0.1493   0.6745   0.1190
   1.250   0.8689   0.02632   0.01702  -0.1483   0.6640   0.1093
   1.500   0.9022   0.02535   0.01592  -0.1486   0.6557   0.1041
   1.750   0.9249   0.02514   0.01562  -0.1473   0.6448   0.1013
   2.000   0.9595   0.02439   0.01474  -0.1478   0.6375   0.1028
   2.250   0.9787   0.02435   0.01473  -0.1461   0.6264   0.1035
   2.500   1.0124   0.02377   0.01399  -0.1465   0.6195   0.1038
   2.750   1.0321   0.02393   0.01414  -0.1450   0.6089   0.1051
   3.000   1.0638   0.02372   0.01374  -0.1453   0.6015   0.1086
   3.250   1.0868   0.02387   0.01383  -0.1444   0.5920   0.1151
   3.500   1.1178   0.02376   0.01367  -0.1447   0.5846   0.1408
   3.750   1.1361   0.02262   0.01405  -0.1428   0.5761   1.0000
   4.000   1.1700   0.02275   0.01380  -0.1435   0.5699   1.0000
   4.250   1.1874   0.02343   0.01443  -0.1419   0.5610   1.0000
   4.500   1.2209   0.02360   0.01432  -0.1427   0.5547   1.0000
   4.750   1.2381   0.02435   0.01508  -0.1412   0.5464   1.0000
   5.000   1.2669   0.02471   0.01528  -0.1414   0.5397   1.0000
   5.250   1.2908   0.02536   0.01587  -0.1410   0.5333   1.0000
   5.500   1.3107   0.02608   0.01660  -0.1399   0.5263   1.0000
   5.750   1.3439   0.02643   0.01677  -0.1409   0.5209   1.0000
   6.000   1.3582   0.02739   0.01783  -0.1391   0.5140   1.0000
   6.250   1.3804   0.02806   0.01851  -0.1384   0.5077   1.0000
   6.500   1.4147   0.02850   0.01878  -0.1397   0.5030   1.0000
   6.750   1.4239   0.02971   0.02017  -0.1372   0.4970   1.0000
   7.000   1.4426   0.03058   0.02110  -0.1361   0.4913   1.0000
   7.250   1.4742   0.03105   0.02148  -0.1369   0.4866   1.0000
   7.500   1.4872   0.03223   0.02278  -0.1351   0.4812   1.0000
   7.750   1.4973   0.03346   0.02415  -0.1328   0.4757   1.0000
   8.000   1.5222   0.03420   0.02491  -0.1327   0.4713   1.0000
   8.250   1.5591   0.03469   0.02530  -0.1345   0.4675   1.0000
   8.500   1.5458   0.03682   0.02775  -0.1289   0.4618   1.0000
   8.750   1.5567   0.03805   0.02909  -0.1269   0.4567   1.0000
   9.000   1.5923   0.03826   0.02926  -0.1283   0.4522   1.0000
   9.250   1.5987   0.03979   0.03092  -0.1257   0.4474   1.0000
   9.500   1.5807   0.04219   0.03355  -0.1199   0.4416   1.0000
   9.750   1.6191   0.04190   0.03321  -0.1213   0.4361   1.0000
  10.000   1.6445   0.04245   0.03380  -0.1212   0.4311   1.0000
  10.250   1.5727   0.04746   0.03913  -0.1092   0.4257   1.0000
  10.500   1.6047   0.04728   0.03899  -0.1096   0.4205   1.0000
  10.750   1.6871   0.04494   0.03650  -0.1163   0.4149   1.0000
  11.250   1.4448   0.06670   0.05887  -0.0920   0.4004   1.0000
  11.500   1.7088   0.04811   0.03996  -0.1090   0.3994   1.0000
  11.750   1.0575   0.12940   0.12188  -0.0985   0.3577   1.0000
  12.000   1.0860   0.12869   0.12119  -0.0974   0.3526   1.0000
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