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GOE 364 AIRFOIL (goe364-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 364 AIRFOIL (goe364-il)
Reynolds number: 200,000
Max Cl/Cd: 76.37 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe364-il-200000.txt
Download as CSV file: xf-goe364-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 364 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.0891   0.09064   0.08761  -0.0518   0.9775   0.0356
  -8.750  -0.0728   0.08617   0.08314  -0.0562   0.9729   0.0369
  -8.500  -0.0627   0.08227   0.07923  -0.0624   0.9658   0.0381
  -8.250  -0.0558   0.07830   0.07525  -0.0720   0.9580   0.0385
  -8.000  -0.0280   0.07237   0.06932  -0.0713   0.9563   0.0392
  -7.750  -0.0099   0.06857   0.06551  -0.0729   0.9462   0.0403
  -7.500   0.0078   0.06463   0.06156  -0.0766   0.9373   0.0423
  -7.250  -0.0804   0.07796   0.07479  -0.0731   0.9480   0.0394
  -7.000  -0.0523   0.07419   0.07101  -0.0771   0.9426   0.0410
  -6.750  -0.0289   0.07050   0.06728  -0.0828   0.9297   0.0429
  -6.500   0.0096   0.06563   0.06214  -0.1023   0.9107   0.0455
  -6.250   0.0218   0.06161   0.05818  -0.1004   0.8992   0.0461
  -6.000   0.0402   0.05883   0.05539  -0.1000   0.8883   0.0472
  -5.750   0.0619   0.05601   0.05248  -0.1023   0.8767   0.0489
  -5.500   0.0853   0.05301   0.04933  -0.1063   0.8632   0.0523
  -5.250   0.1071   0.04918   0.04525  -0.1106   0.8496   0.0550
  -5.000   0.1230   0.04709   0.04314  -0.1098   0.8381   0.0565
  -4.750   0.1439   0.04490   0.04082  -0.1106   0.8277   0.0590
  -4.500   0.1720   0.04181   0.03725  -0.1141   0.8163   0.0649
  -4.250   0.1883   0.03960   0.03507  -0.1133   0.8061   0.0662
  -4.000   0.2092   0.03785   0.03322  -0.1132   0.7974   0.0689
  -3.750   0.2349   0.03579   0.03075  -0.1140   0.7870   0.0771
  -3.500   0.2542   0.03389   0.02886  -0.1135   0.7786   0.0795
  -3.250   0.2764   0.03252   0.02737  -0.1131   0.7685   0.0851
  -3.000   0.3005   0.03058   0.02510  -0.1130   0.7597   0.0920
  -2.750   0.3222   0.02918   0.02365  -0.1124   0.7503   0.0963
  -2.500   0.3468   0.02781   0.02196  -0.1119   0.7413   0.1067
  -2.250   0.3697   0.02657   0.02068  -0.1114   0.7325   0.1134
  -2.000   0.3927   0.02529   0.01922  -0.1107   0.7231   0.1247
  -1.750   0.4177   0.02424   0.01793  -0.1102   0.7146   0.1387
  -1.500   0.4406   0.02332   0.01688  -0.1093   0.7043   0.1542
  -1.250   0.4647   0.02228   0.01571  -0.1087   0.6954   0.1713
  -1.000   0.4873   0.02128   0.01468  -0.1078   0.6848   0.1900
  -0.750   0.5112   0.02051   0.01382  -0.1070   0.6751   0.2122
  -0.500   0.5551   0.01750   0.00943  -0.1048   0.6670   0.0736
  -0.250   0.5808   0.01665   0.00844  -0.1038   0.6559   0.0710
   0.000   0.6073   0.01601   0.00759  -0.1030   0.6454   0.0694
   0.250   0.6325   0.01550   0.00699  -0.1020   0.6335   0.0691
   0.500   0.6573   0.01517   0.00661  -0.1011   0.6215   0.0708
   0.750   0.6825   0.01489   0.00626  -0.1003   0.6106   0.0729
   1.000   0.7073   0.01461   0.00591  -0.0993   0.5995   0.0740
   1.250   0.7311   0.01441   0.00570  -0.0983   0.5878   0.0755
   1.500   0.7555   0.01420   0.00546  -0.0974   0.5780   0.0789
   1.750   0.7803   0.01413   0.00534  -0.0966   0.5684   0.0854
   2.000   0.8049   0.01408   0.00530  -0.0957   0.5589   0.1027
   2.250   0.8699   0.01237   0.00532  -0.1038   0.5487   1.0000
   2.500   0.8937   0.01254   0.00540  -0.1029   0.5392   1.0000
   2.750   0.9182   0.01275   0.00546  -0.1021   0.5311   1.0000
   3.000   0.9420   0.01293   0.00556  -0.1012   0.5220   1.0000
   3.250   0.9662   0.01314   0.00568  -0.1004   0.5138   1.0000
   3.500   0.9901   0.01335   0.00581  -0.0995   0.5055   1.0000
   3.750   1.0142   0.01358   0.00598  -0.0988   0.4977   1.0000
   4.000   1.0380   0.01381   0.00614  -0.0979   0.4897   1.0000
   4.250   1.0618   0.01406   0.00634  -0.0971   0.4817   1.0000
   4.500   1.0852   0.01430   0.00653  -0.0962   0.4732   1.0000
   4.750   1.1083   0.01456   0.00676  -0.0953   0.4646   1.0000
   5.000   1.1316   0.01483   0.00695  -0.0945   0.4561   1.0000
   5.250   1.1540   0.01511   0.00724  -0.0934   0.4472   1.0000
   5.500   1.1775   0.01543   0.00746  -0.0927   0.4387   1.0000
   5.750   1.1983   0.01569   0.00777  -0.0914   0.4287   1.0000
   6.000   1.2204   0.01602   0.00804  -0.0903   0.4192   1.0000
   6.250   1.2409   0.01631   0.00834  -0.0890   0.4088   1.0000
   6.500   1.2611   0.01663   0.00867  -0.0877   0.3981   1.0000
   6.750   1.2816   0.01699   0.00896  -0.0864   0.3877   1.0000
   7.000   1.3000   0.01729   0.00928  -0.0848   0.3762   1.0000
   7.250   1.3182   0.01763   0.00966  -0.0831   0.3646   1.0000
   7.500   1.3362   0.01800   0.00999  -0.0815   0.3538   1.0000
   7.750   1.3533   0.01837   0.01031  -0.0797   0.3429   1.0000
   8.000   1.3693   0.01872   0.01072  -0.0778   0.3317   1.0000
   8.250   1.3858   0.01916   0.01114  -0.0759   0.3221   1.0000
   8.500   1.4017   0.01961   0.01156  -0.0741   0.3135   1.0000
   8.750   1.4176   0.02008   0.01208  -0.0722   0.3053   1.0000
   9.000   1.4323   0.02059   0.01254  -0.0702   0.2982   1.0000
   9.250   1.4464   0.02111   0.01312  -0.0681   0.2910   1.0000
   9.500   1.4602   0.02166   0.01366  -0.0660   0.2842   1.0000
   9.750   1.4748   0.02227   0.01429  -0.0641   0.2779   1.0000
  10.000   1.4885   0.02287   0.01494  -0.0622   0.2718   1.0000
  10.250   1.5057   0.02359   0.01559  -0.0609   0.2661   1.0000
  10.500   1.5169   0.02424   0.01638  -0.0587   0.2603   1.0000
  10.750   1.5303   0.02495   0.01710  -0.0569   0.2545   1.0000
  11.000   1.5436   0.02574   0.01793  -0.0552   0.2486   1.0000
  11.250   1.5519   0.02652   0.01881  -0.0529   0.2422   1.0000
  11.500   1.5649   0.02740   0.01962  -0.0513   0.2357   1.0000
  11.750   1.5695   0.02832   0.02072  -0.0488   0.2295   1.0000
  12.000   1.5785   0.02928   0.02166  -0.0469   0.2233   1.0000
  12.250   1.5845   0.03039   0.02289  -0.0449   0.2174   1.0000
  12.500   1.5893   0.03155   0.02415  -0.0429   0.2114   1.0000
  12.750   1.5968   0.03276   0.02534  -0.0413   0.2053   1.0000
  13.000   1.5981   0.03421   0.02698  -0.0394   0.1995   1.0000
  13.250   1.6025   0.03563   0.02843  -0.0379   0.1939   1.0000
  13.500   1.6052   0.03726   0.03018  -0.0365   0.1883   1.0000
  13.750   1.6062   0.03905   0.03211  -0.0352   0.1826   1.0000
  14.000   1.6104   0.04071   0.03373  -0.0341   0.1776   1.0000
  14.250   1.6093   0.04286   0.03611  -0.0331   0.1720   1.0000
  14.500   1.6088   0.04506   0.03839  -0.0323   0.1666   1.0000
  14.750   1.6088   0.04730   0.04069  -0.0316   0.1618   1.0000
  15.000   1.6075   0.04982   0.04339  -0.0311   0.1563   1.0000
  15.250   1.6060   0.05240   0.04601  -0.0307   0.1518   1.0000
  15.500   1.6045   0.05513   0.04887  -0.0305   0.1470   1.0000
  15.750   1.6021   0.05806   0.05194  -0.0305   0.1422   1.0000
  16.000   1.5967   0.06135   0.05522  -0.0306   0.1375   1.0000
  16.250   1.5929   0.06473   0.05880  -0.0310   0.1323   1.0000
  16.500   1.5866   0.06847   0.06262  -0.0315   0.1274   1.0000
  16.750   1.5805   0.07222   0.06644  -0.0321   0.1233   1.0000
  17.000   1.5736   0.07632   0.07071  -0.0331   0.1178   1.0000
  17.250   1.5637   0.08084   0.07527  -0.0342   0.1133   1.0000
  17.500   1.5558   0.08529   0.07988  -0.0354   0.1081   1.0000
  17.750   1.5432   0.09047   0.08513  -0.0370   0.1027   1.0000
  18.000   1.5305   0.09584   0.09062  -0.0388   0.0967   1.0000
  18.250   1.5163   0.10150   0.09636  -0.0408   0.0912   1.0000
  18.500   1.5025   0.10722   0.10220  -0.0429   0.0854   1.0000
  18.750   1.4839   0.11383   0.10886  -0.0456   0.0792   1.0000
  19.000   1.4663   0.12047   0.11561  -0.0484   0.0714   1.0000
  19.250   1.4481   0.12730   0.12251  -0.0515   0.0647   1.0000
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