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GOE 298 AIRFOIL (goe298-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 298 AIRFOIL (goe298-il)
Reynolds number: 500,000
Max Cl/Cd: 91.71 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe298-il-500000.txt
Download as CSV file: xf-goe298-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 298 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3853   0.13653   0.13397  -0.0075   1.0000   0.0483
 -11.750  -0.3759   0.13388   0.13133  -0.0085   1.0000   0.0489
 -11.500  -0.8012   0.03690   0.03367  -0.0835   1.0000   0.0502
 -11.250  -0.7681   0.03988   0.03683  -0.0804   1.0000   0.0505
 -11.000  -0.7392   0.04189   0.03894  -0.0783   1.0000   0.0509
 -10.750  -0.7092   0.04400   0.04112  -0.0761   1.0000   0.0513
 -10.500  -0.6772   0.04629   0.04349  -0.0738   0.9986   0.0516
 -10.250  -0.6355   0.04909   0.04636  -0.0720   0.9870   0.0520
 -10.000  -0.5939   0.05201   0.04932  -0.0698   0.9732   0.0522
  -9.750  -0.6407   0.02122   0.01639  -0.0954   0.9371   0.0566
  -9.500  -0.6170   0.02024   0.01512  -0.0950   0.9238   0.0576
  -9.250  -0.5932   0.01938   0.01419  -0.0945   0.9120   0.0585
  -9.000  -0.5675   0.01918   0.01397  -0.0939   0.9012   0.0593
  -8.750  -0.5407   0.01896   0.01372  -0.0935   0.8905   0.0603
  -8.500  -0.5145   0.01859   0.01322  -0.0931   0.8810   0.0615
  -8.250  -0.4878   0.01796   0.01241  -0.0929   0.8708   0.0629
  -8.000  -0.4616   0.01725   0.01156  -0.0927   0.8617   0.0641
  -7.750  -0.4337   0.01708   0.01141  -0.0925   0.8515   0.0651
  -7.500  -0.4058   0.01696   0.01126  -0.0922   0.8425   0.0661
  -7.250  -0.3777   0.01667   0.01090  -0.0920   0.8323   0.0674
  -7.000  -0.3499   0.01622   0.01027  -0.0919   0.8233   0.0690
  -6.750  -0.3219   0.01571   0.00965  -0.0918   0.8132   0.0704
  -6.500  -0.2934   0.01569   0.00964  -0.0916   0.8042   0.0715
  -6.250  -0.2646   0.01566   0.00961  -0.0915   0.7941   0.0727
  -6.000  -0.2361   0.01546   0.00929  -0.0913   0.7842   0.0742
  -5.750  -0.2075   0.01512   0.00878  -0.0912   0.7734   0.0759
  -5.500  -0.1792   0.01475   0.00833  -0.0911   0.7637   0.0774
  -5.250  -0.1503   0.01477   0.00836  -0.0910   0.7537   0.0786
  -5.000  -0.1214   0.01477   0.00830  -0.0909   0.7443   0.0800
  -4.750  -0.0924   0.01459   0.00804  -0.0908   0.7342   0.0817
  -4.500  -0.0634   0.01444   0.00771  -0.0907   0.7251   0.0836
  -4.250  -0.0345   0.01404   0.00730  -0.0908   0.7158   0.0852
  -4.000  -0.0057   0.01404   0.00727  -0.0906   0.7073   0.0866
  -3.750   0.0238   0.01391   0.00713  -0.0907   0.6985   0.0882
  -3.500   0.0529   0.01381   0.00693  -0.0906   0.6894   0.0902
  -3.250   0.0825   0.01375   0.00677  -0.0906   0.6798   0.0920
  -3.000   0.1112   0.01324   0.00623  -0.0906   0.6697   0.0940
  -2.750   0.1405   0.01311   0.00611  -0.0906   0.6602   0.0955
  -2.500   0.1697   0.01302   0.00597  -0.0906   0.6508   0.0975
  -2.250   0.1992   0.01291   0.00581  -0.0906   0.6420   0.0997
  -2.000   0.2286   0.01286   0.00567  -0.0906   0.6326   0.1013
  -1.750   0.2577   0.01236   0.00514  -0.0907   0.6242   0.1035
  -1.500   0.2869   0.01221   0.00501  -0.0907   0.6151   0.1055
  -1.250   0.3161   0.01212   0.00488  -0.0907   0.6071   0.1076
  -1.000   0.3455   0.01199   0.00473  -0.0907   0.5988   0.1096
  -0.750   0.3747   0.01196   0.00462  -0.0907   0.5913   0.1115
  -0.500   0.4041   0.01167   0.00431  -0.0908   0.5845   0.1136
  -0.250   0.4332   0.01145   0.00411  -0.0908   0.5777   0.1157
   0.000   0.4622   0.01139   0.00402  -0.0908   0.5711   0.1178
   0.250   0.4916   0.01130   0.00396  -0.0908   0.5641   0.1202
   0.500   0.5207   0.01126   0.00387  -0.0908   0.5569   0.1222
   0.750   0.5498   0.01125   0.00383  -0.0908   0.5509   0.1237
   1.000   0.5791   0.01105   0.00366  -0.0908   0.5442   0.1262
   1.250   0.6079   0.01097   0.00357  -0.0908   0.5355   0.1287
   1.500   0.6371   0.01091   0.00354  -0.0908   0.5267   0.1310
   1.750   0.6659   0.01093   0.00352  -0.0908   0.5167   0.1336
   2.000   0.6949   0.01091   0.00351  -0.0908   0.5070   0.1362
   2.250   0.7234   0.01097   0.00351  -0.0907   0.4950   0.1380
   2.500   0.7526   0.01087   0.00345  -0.0907   0.4803   0.1419
   2.750   0.7812   0.01088   0.00346  -0.0907   0.4615   0.1461
   3.000   0.8092   0.01099   0.00347  -0.0906   0.4263   0.1507
   3.250   0.8345   0.01143   0.00359  -0.0902   0.3643   0.1563
   3.500   0.8609   0.01176   0.00382  -0.0899   0.3410   0.1661
   3.750   0.8881   0.01195   0.00404  -0.0898   0.3281   0.1943
   4.000   0.9130   0.01085   0.00447  -0.0899   0.3189   0.8039
   4.250   0.9328   0.01072   0.00457  -0.0876   0.3122   1.0000
   4.500   0.9605   0.01095   0.00475  -0.0874   0.3058   1.0000
   4.750   0.9875   0.01126   0.00498  -0.0872   0.2994   1.0000
   5.000   1.0150   0.01151   0.00520  -0.0870   0.2940   1.0000
   5.250   1.0427   0.01170   0.00539  -0.0869   0.2887   1.0000
   5.500   1.0697   0.01197   0.00561  -0.0866   0.2828   1.0000
   5.750   1.0962   0.01229   0.00587  -0.0863   0.2768   1.0000
   6.000   1.1240   0.01244   0.00604  -0.0862   0.2715   1.0000
   6.250   1.1508   0.01269   0.00626  -0.0859   0.2653   1.0000
   6.500   1.1767   0.01301   0.00653  -0.0856   0.2591   1.0000
   6.750   1.2041   0.01317   0.00672  -0.0854   0.2532   1.0000
   7.000   1.2302   0.01345   0.00696  -0.0851   0.2459   1.0000
   7.250   1.2564   0.01370   0.00720  -0.0848   0.2384   1.0000
   7.500   1.2820   0.01400   0.00745  -0.0844   0.2284   1.0000
   7.750   1.3075   0.01429   0.00771  -0.0840   0.2172   1.0000
   8.000   1.3317   0.01467   0.00802  -0.0834   0.2038   1.0000
   8.250   1.3546   0.01515   0.00840  -0.0827   0.1884   1.0000
   8.500   1.3764   0.01569   0.00884  -0.0819   0.1743   1.0000
   8.750   1.3974   0.01627   0.00934  -0.0809   0.1633   1.0000
   9.000   1.4178   0.01685   0.00987  -0.0798   0.1550   1.0000
   9.250   1.4383   0.01740   0.01039  -0.0788   0.1491   1.0000
   9.500   1.4580   0.01796   0.01094  -0.0776   0.1442   1.0000
   9.750   1.4747   0.01867   0.01161  -0.0761   0.1396   1.0000
  10.000   1.4944   0.01914   0.01212  -0.0749   0.1369   1.0000
  10.250   1.5110   0.01970   0.01271  -0.0732   0.1341   1.0000
  10.500   1.5244   0.02038   0.01339  -0.0712   0.1317   1.0000
  10.750   1.5362   0.02122   0.01424  -0.0691   0.1292   1.0000
  11.000   1.5484   0.02211   0.01515  -0.0673   0.1270   1.0000
  11.250   1.5645   0.02280   0.01591  -0.0660   0.1253   1.0000
  11.500   1.5796   0.02360   0.01677  -0.0647   0.1235   1.0000
  11.750   1.5932   0.02453   0.01773  -0.0635   0.1213   1.0000
  12.000   1.6051   0.02562   0.01884  -0.0621   0.1193   1.0000
  12.250   1.6147   0.02693   0.02016  -0.0607   0.1174   1.0000
  12.500   1.6241   0.02828   0.02155  -0.0594   0.1157   1.0000
  12.750   1.6386   0.02928   0.02264  -0.0585   0.1146   1.0000
  13.000   1.6518   0.03039   0.02382  -0.0576   0.1131   1.0000
  13.250   1.6641   0.03161   0.02510  -0.0567   0.1115   1.0000
  13.500   1.6748   0.03298   0.02653  -0.0558   0.1097   1.0000
  13.750   1.6830   0.03461   0.02818  -0.0549   0.1078   1.0000
  14.000   1.6881   0.03655   0.03014  -0.0540   0.1059   1.0000
  14.250   1.6976   0.03811   0.03179  -0.0532   0.1046   1.0000
  14.500   1.7091   0.03952   0.03329  -0.0527   0.1031   1.0000
  14.750   1.7191   0.04107   0.03493  -0.0521   0.1013   1.0000
  15.000   1.7270   0.04287   0.03678  -0.0516   0.0992   1.0000
  15.250   1.7309   0.04505   0.03899  -0.0510   0.0971   1.0000
  15.500   1.7341   0.04734   0.04133  -0.0505   0.0950   1.0000
  15.750   1.7449   0.04892   0.04302  -0.0502   0.0925   1.0000
  16.000   1.7515   0.05098   0.04515  -0.0499   0.0895   1.0000
  16.250   1.7515   0.05382   0.04801  -0.0497   0.0867   1.0000
  16.500   1.7602   0.05573   0.05002  -0.0496   0.0829   1.0000
  16.750   1.7607   0.05866   0.05297  -0.0496   0.0785   1.0000
  17.000   1.7628   0.06143   0.05579  -0.0497   0.0722   1.0000
  17.250   1.7575   0.06515   0.05952  -0.0500   0.0644   1.0000
  17.500   1.7454   0.06981   0.06419  -0.0505   0.0559   1.0000
  17.750   1.7292   0.07512   0.06951  -0.0513   0.0499   1.0000
  18.250   1.6964   0.08612   0.08065  -0.0535   0.0445   1.0000
  18.500   1.6791   0.09197   0.08660  -0.0549   0.0431   1.0000
  18.750   1.6601   0.09820   0.09294  -0.0567   0.0420   1.0000
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