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GOE 288 AIRFOIL (goe288-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 288 AIRFOIL (goe288-il)
Reynolds number: 100,000
Max Cl/Cd: 43.72 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe288-il-100000.txt
Download as CSV file: xf-goe288-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 288 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1402   0.10159   0.09703  -0.0724   0.9566   0.1644
  -8.500  -0.0882   0.09700   0.09238  -0.0737   0.9532   0.1681
  -8.250  -0.2031   0.06773   0.06298  -0.1044   0.9245   0.1083
  -8.000  -0.1835   0.06257   0.05775  -0.1092   0.9136   0.1068
  -7.750  -0.2302   0.04253   0.03655  -0.1302   0.8924   0.0998
  -7.500  -0.2033   0.03798   0.03144  -0.1346   0.8843   0.1005
  -7.250  -0.1815   0.03548   0.02858  -0.1357   0.8713   0.1020
  -7.000  -0.1488   0.03286   0.02551  -0.1380   0.8646   0.1048
  -6.750  -0.1261   0.03114   0.02323  -0.1383   0.8514   0.1081
  -6.500  -0.0960   0.02975   0.02190  -0.1389   0.8435   0.1120
  -6.250  -0.0700   0.02863   0.02059  -0.1389   0.8324   0.1166
  -6.000  -0.0403   0.02718   0.01891  -0.1393   0.8248   0.1224
  -5.750  -0.0147   0.02649   0.01818  -0.1392   0.8146   0.1303
  -5.500   0.0158   0.02548   0.01714  -0.1395   0.8086   0.1421
  -5.250   0.0397   0.02485   0.01653  -0.1393   0.7982   0.1572
  -5.000   0.0695   0.02402   0.01559  -0.1395   0.7915   0.1803
  -4.750   0.0949   0.02377   0.01549  -0.1393   0.7831   0.2006
  -4.500   0.1227   0.02366   0.01542  -0.1393   0.7757   0.2208
  -4.250   0.1533   0.02357   0.01529  -0.1394   0.7706   0.2411
  -4.000   0.1771   0.02395   0.01574  -0.1390   0.7616   0.2592
  -3.750   0.2061   0.02417   0.01592  -0.1389   0.7552   0.2799
  -3.500   0.2341   0.02443   0.01617  -0.1386   0.7489   0.2988
  -3.250   0.2595   0.02464   0.01643  -0.1379   0.7400   0.3146
  -3.000   0.2903   0.02448   0.01617  -0.1376   0.7334   0.3332
  -2.750   0.3142   0.02465   0.01638  -0.1368   0.7232   0.3501
  -2.500   0.3438   0.02452   0.01614  -0.1364   0.7160   0.3699
  -2.250   0.3694   0.02467   0.01629  -0.1359   0.7084   0.3882
  -2.000   0.3961   0.02472   0.01631  -0.1354   0.7011   0.4061
  -1.750   0.4260   0.02461   0.01609  -0.1353   0.6958   0.4240
  -1.500   0.4500   0.02483   0.01632  -0.1348   0.6880   0.4397
  -1.250   0.4778   0.02482   0.01622  -0.1346   0.6811   0.4559
  -1.000   0.5085   0.02470   0.01597  -0.1346   0.6760   0.4714
  -0.750   0.5302   0.02496   0.01635  -0.1337   0.6674   0.4834
  -0.500   0.5590   0.02486   0.01617  -0.1336   0.6608   0.4976
  -0.250   0.5882   0.02487   0.01606  -0.1336   0.6549   0.5124
   0.000   0.6109   0.02507   0.01636  -0.1328   0.6463   0.5247
   0.250   0.6408   0.02490   0.01611  -0.1327   0.6401   0.5391
   0.500   0.6658   0.02508   0.01629  -0.1323   0.6322   0.5530
   0.750   0.6927   0.02507   0.01626  -0.1320   0.6242   0.5659
   1.000   0.7249   0.02482   0.01588  -0.1322   0.6186   0.5779
   1.250   0.7460   0.02517   0.01632  -0.1315   0.6084   0.5895
   1.500   0.7765   0.02496   0.01604  -0.1315   0.6018   0.6021
   1.750   0.8000   0.02517   0.01631  -0.1308   0.5927   0.6145
   2.000   0.8286   0.02505   0.01615  -0.1307   0.5845   0.6298
   2.250   0.8553   0.02511   0.01619  -0.1303   0.5762   0.6463
   2.500   0.8812   0.02507   0.01620  -0.1298   0.5668   0.6657
   2.750   0.9100   0.02491   0.01605  -0.1296   0.5595   0.6915
   3.000   0.9308   0.02496   0.01633  -0.1283   0.5491   0.7286
   3.250   0.9585   0.02414   0.01583  -0.1270   0.5432   1.0000
   3.500   0.9817   0.02477   0.01640  -0.1270   0.5315   1.0000
   3.750   1.0173   0.02473   0.01602  -0.1281   0.5250   1.0000
   4.000   1.0364   0.02538   0.01671  -0.1270   0.5138   1.0000
   4.250   1.0692   0.02538   0.01646  -0.1275   0.5074   1.0000
   4.500   1.0880   0.02612   0.01724  -0.1264   0.4976   1.0000
   4.750   1.1172   0.02630   0.01728  -0.1265   0.4910   1.0000
   5.000   1.1408   0.02689   0.01783  -0.1259   0.4838   1.0000
   5.250   1.1632   0.02742   0.01835  -0.1252   0.4762   1.0000
   5.500   1.1959   0.02749   0.01822  -0.1258   0.4712   1.0000
   5.750   1.2107   0.02849   0.01935  -0.1241   0.4633   1.0000
   6.000   1.2358   0.02889   0.01971  -0.1238   0.4574   1.0000
   6.250   1.2691   0.02903   0.01967  -0.1245   0.4533   1.0000
   6.500   1.2798   0.03034   0.02117  -0.1224   0.4467   1.0000
   6.750   1.3010   0.03107   0.02193  -0.1217   0.4415   1.0000
   7.000   1.3308   0.03137   0.02214  -0.1219   0.4376   1.0000
   7.250   1.3531   0.03219   0.02296  -0.1214   0.4333   1.0000
   7.500   1.3605   0.03365   0.02461  -0.1190   0.4276   1.0000
   7.750   1.3830   0.03430   0.02527  -0.1184   0.4233   1.0000
   8.000   1.4140   0.03461   0.02550  -0.1189   0.4200   1.0000
   8.250   1.4321   0.03577   0.02672  -0.1179   0.4166   1.0000
   8.500   1.4259   0.03811   0.02933  -0.1141   0.4119   1.0000
   8.750   1.4337   0.03971   0.03105  -0.1121   0.4082   1.0000
   9.000   1.4560   0.04053   0.03189  -0.1116   0.4052   1.0000
   9.250   1.4913   0.04075   0.03204  -0.1126   0.4026   1.0000
   9.500   1.4779   0.04361   0.03512  -0.1083   0.3990   1.0000
   9.750   1.1868   0.07315   0.06535  -0.0934   0.3845   1.0000
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