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GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 377 AIRFOIL (goe377-il)
Reynolds number: 100,000
Max Cl/Cd: 58.13 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe377-il-100000-n5.txt
Download as CSV file: xf-goe377-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 377 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3553   0.09268   0.08801  -0.0258   1.0000   0.0350
  -7.250  -0.3617   0.09087   0.08630  -0.0257   1.0000   0.0357
  -7.000  -0.3640   0.08878   0.08429  -0.0272   1.0000   0.0362
  -6.750  -0.3641   0.08636   0.08192  -0.0281   1.0000   0.0364
  -6.500  -0.3630   0.08387   0.07947  -0.0297   1.0000   0.0366
  -6.250  -0.3602   0.08117   0.07679  -0.0302   1.0000   0.0367
  -6.000  -0.3558   0.07832   0.07394  -0.0309   1.0000   0.0368
  -5.750  -0.3500   0.07531   0.07091  -0.0314   1.0000   0.0368
  -5.250  -0.3392   0.06651   0.06204  -0.0309   1.0000   0.0261
  -5.000  -0.3165   0.06191   0.05737  -0.0343   0.9961   0.0256
  -4.250  -0.2097   0.04662   0.04133  -0.0502   0.9792   0.0263
  -4.000  -0.1786   0.04203   0.03647  -0.0532   0.9730   0.0261
  -3.750  -0.1430   0.03734   0.03131  -0.0562   0.9679   0.0264
  -3.500  -0.1176   0.03537   0.02929  -0.0579   0.9611   0.0296
  -3.250  -0.0828   0.03206   0.02556  -0.0599   0.9560   0.0323
  -3.000  -0.0508   0.02857   0.02149  -0.0608   0.9501   0.0336
  -2.750  -0.0176   0.02564   0.01785  -0.0615   0.9445   0.0384
  -2.500   0.0180   0.02385   0.01576  -0.0632   0.9406   0.0424
  -2.250   0.0479   0.02261   0.01392  -0.0630   0.9332   0.0492
  -2.000   0.0827   0.02089   0.01196  -0.0645   0.9287   0.0535
  -1.750   0.1150   0.02007   0.01092  -0.0652   0.9224   0.0600
  -1.500   0.1495   0.01917   0.00970  -0.0662   0.9166   0.0628
  -1.250   0.1867   0.01817   0.00856  -0.0678   0.9122   0.0639
  -1.000   0.2148   0.01739   0.00779  -0.0677   0.9036   0.0661
  -0.750   0.2508   0.01671   0.00708  -0.0692   0.8986   0.0702
  -0.500   0.2785   0.01630   0.00658  -0.0689   0.8887   0.0757
  -0.250   0.3106   0.01584   0.00609  -0.0695   0.8801   0.0847
   0.000   0.3473   0.01531   0.00558  -0.0709   0.8709   0.1103
   0.500   0.4489   0.01264   0.00492  -0.0800   0.8465   1.0000
   0.750   0.4775   0.01259   0.00471  -0.0798   0.8316   1.0000
   1.000   0.5057   0.01256   0.00455  -0.0794   0.8161   1.0000
   1.250   0.5322   0.01256   0.00444  -0.0788   0.7987   1.0000
   1.500   0.5588   0.01257   0.00437  -0.0782   0.7808   1.0000
   1.750   0.5859   0.01258   0.00429  -0.0776   0.7623   1.0000
   2.000   0.6130   0.01261   0.00423  -0.0771   0.7432   1.0000
   2.250   0.6387   0.01269   0.00426  -0.0764   0.7222   1.0000
   2.500   0.6651   0.01278   0.00427  -0.0757   0.7014   1.0000
   2.750   0.6900   0.01292   0.00434  -0.0749   0.6784   1.0000
   3.000   0.7150   0.01308   0.00445  -0.0740   0.6552   1.0000
   3.250   0.7394   0.01328   0.00458  -0.0731   0.6311   1.0000
   3.500   0.7633   0.01350   0.00475  -0.0721   0.6064   1.0000
   3.750   0.7870   0.01376   0.00495  -0.0711   0.5814   1.0000
   4.000   0.8102   0.01406   0.00521  -0.0700   0.5561   1.0000
   4.250   0.8331   0.01438   0.00549  -0.0689   0.5308   1.0000
   4.500   0.8556   0.01472   0.00581  -0.0678   0.5050   1.0000
   4.750   0.8776   0.01510   0.00615  -0.0666   0.4775   1.0000
   5.000   0.8989   0.01552   0.00655  -0.0653   0.4481   1.0000
   5.250   0.9201   0.01595   0.00695  -0.0640   0.4200   1.0000
   5.500   0.9414   0.01640   0.00740  -0.0628   0.3961   1.0000
   5.750   0.9628   0.01688   0.00790  -0.0616   0.3748   1.0000
   6.000   0.9841   0.01738   0.00848  -0.0604   0.3551   1.0000
   6.250   1.0020   0.01798   0.00899  -0.0587   0.3194   1.0000
   6.500   1.0176   0.01873   0.00951  -0.0568   0.2708   1.0000
   6.750   1.0352   0.01943   0.01013  -0.0552   0.2284   1.0000
   7.000   1.0493   0.02056   0.01088  -0.0532   0.1464   1.0000
   7.250   1.0536   0.02305   0.01251  -0.0502   0.0440   1.0000
   7.500   1.0674   0.02449   0.01397  -0.0480   0.0291   1.0000
   7.750   1.0810   0.02589   0.01553  -0.0458   0.0247   1.0000
   8.000   1.0940   0.02722   0.01708  -0.0436   0.0222   1.0000
   8.250   1.1054   0.02858   0.01867  -0.0412   0.0198   1.0000
   8.500   1.1145   0.03004   0.02033  -0.0385   0.0186   1.0000
   8.750   1.1210   0.03166   0.02215  -0.0356   0.0177   1.0000
   9.000   1.1256   0.03336   0.02400  -0.0324   0.0170   1.0000
   9.250   1.1304   0.03518   0.02596  -0.0294   0.0165   1.0000
   9.500   1.1360   0.03744   0.02833  -0.0267   0.0156   1.0000
   9.750   1.1464   0.04095   0.03203  -0.0250   0.0144   1.0000
  10.000   1.1563   0.04297   0.03427  -0.0230   0.0139   1.0000
  10.250   1.1649   0.04535   0.03694  -0.0209   0.0136   1.0000
  10.500   1.1704   0.04813   0.04001  -0.0188   0.0134   1.0000
  10.750   1.1717   0.05108   0.04326  -0.0166   0.0132   1.0000
  11.000   1.1693   0.05410   0.04667  -0.0145   0.0132   1.0000
  11.250   1.1632   0.05737   0.05024  -0.0125   0.0131   1.0000
  11.500   1.1540   0.06090   0.05406  -0.0111   0.0131   1.0000
  11.750   1.1428   0.06470   0.05812  -0.0102   0.0131   1.0000
  12.000   1.1290   0.06896   0.06264  -0.0101   0.0131   1.0000
  12.250   1.1156   0.07344   0.06735  -0.0108   0.0132   1.0000
  12.500   1.0985   0.07886   0.07300  -0.0125   0.0132   1.0000
  12.750   1.0827   0.08446   0.07879  -0.0150   0.0133   1.0000
  13.000   1.0661   0.09072   0.08524  -0.0183   0.0133   1.0000
  13.250   1.0484   0.09775   0.09245  -0.0224   0.0134   1.0000
  13.500   1.0315   0.10522   0.10006  -0.0270   0.0135   1.0000
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