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GOE 361 AIRFOIL (goe361-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 361 AIRFOIL (goe361-il)
Reynolds number: 50,000
Max Cl/Cd: 39.29 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe361-il-50000.txt
Download as CSV file: xf-goe361-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 361 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2921   0.10849   0.10175  -0.0228   1.0000   0.1096
  -8.000  -0.2976   0.10820   0.10159  -0.0236   1.0000   0.1123
  -7.750  -0.3085   0.10889   0.10246  -0.0245   1.0000   0.1132
  -7.500  -0.2867   0.10132   0.09486  -0.0223   1.0000   0.1192
  -7.250  -0.2877   0.09951   0.09315  -0.0217   1.0000   0.1237
  -7.000  -0.2937   0.09930   0.09310  -0.0233   1.0000   0.1269
  -6.750  -0.2953   0.09826   0.09220  -0.0261   1.0000   0.1285
  -6.500  -0.2839   0.09258   0.08652  -0.0213   1.0000   0.1339
  -6.250  -0.2831   0.09084   0.08488  -0.0220   1.0000   0.1394
  -6.000  -0.2833   0.09186   0.08598  -0.0293   1.0000   0.1424
  -5.750  -0.2791   0.08599   0.08021  -0.0219   1.0000   0.1469
  -5.500  -0.2765   0.08401   0.07831  -0.0221   1.0000   0.1534
  -5.250  -0.2724   0.08251   0.07688  -0.0258   1.0000   0.1580
  -5.000  -0.2710   0.07923   0.07369  -0.0216   1.0000   0.1641
  -4.750  -0.2632   0.07770   0.07219  -0.0260   1.0000   0.1726
  -4.500  -0.2625   0.07484   0.06942  -0.0223   1.0000   0.1807
  -4.250  -0.2563   0.07253   0.06715  -0.0234   1.0000   0.1902
  -3.750  -0.2345   0.06850   0.06312  -0.0281   1.0000   0.2167
  -3.000  -0.2082   0.06132   0.05601  -0.0280   1.0000   0.2624
  -2.750  -0.1934   0.05943   0.05411  -0.0298   1.0000   0.2901
  -2.500  -0.1903   0.05687   0.05165  -0.0267   1.0000   0.3103
  -2.250  -0.1816   0.05488   0.04970  -0.0258   1.0000   0.3511
  -1.500  -0.1683   0.04813   0.04330  -0.0124   0.9873   0.5431
  -1.250  -0.1546   0.04528   0.04055  -0.0077   0.9744   0.6172
  -1.000  -0.1360   0.04253   0.03787  -0.0047   0.9606   0.6775
  -0.750  -0.1058   0.03990   0.03526  -0.0054   0.9462   0.7232
  -0.500   0.2587   0.03736   0.02936  -0.0945   0.9237   0.2285
  -0.250   0.3216   0.03566   0.02685  -0.1002   0.9076   0.1849
   0.000   0.3766   0.03423   0.02491  -0.1044   0.8907   0.1704
   0.250   0.4307   0.03286   0.02320  -0.1084   0.8737   0.1691
   0.500   0.4893   0.03141   0.02140  -0.1125   0.8571   0.1661
   0.750   0.5494   0.02998   0.01958  -0.1162   0.8406   0.1672
   1.000   0.5944   0.02895   0.01837  -0.1175   0.8215   0.1731
   1.250   0.6353   0.02799   0.01742  -0.1182   0.8019   0.1894
   1.500   0.6773   0.02687   0.01649  -0.1190   0.7839   0.2356
   1.750   0.7172   0.02469   0.01536  -0.1188   0.7671   1.0000
   2.000   0.7453   0.02488   0.01516  -0.1175   0.7459   1.0000
   2.250   0.7757   0.02492   0.01495  -0.1165   0.7261   1.0000
   2.500   0.8068   0.02493   0.01473  -0.1155   0.7078   1.0000
   2.750   0.8305   0.02544   0.01511  -0.1142   0.6863   1.0000
   3.000   0.8573   0.02579   0.01533  -0.1130   0.6669   1.0000
   3.250   0.8847   0.02614   0.01554  -0.1119   0.6491   1.0000
   3.500   0.9086   0.02683   0.01614  -0.1108   0.6305   1.0000
   3.750   0.9317   0.02759   0.01686  -0.1096   0.6122   1.0000
   4.000   0.9556   0.02835   0.01761  -0.1086   0.5956   1.0000
   4.250   0.9792   0.02919   0.01843  -0.1077   0.5804   1.0000
   4.500   1.0022   0.03018   0.01944  -0.1069   0.5667   1.0000
   4.750   1.0254   0.03124   0.02052  -0.1062   0.5548   1.0000
   5.000   1.0516   0.03203   0.02130  -0.1055   0.5446   1.0000
   5.250   1.0696   0.03362   0.02309  -0.1048   0.5330   1.0000
   5.500   1.0880   0.03525   0.02487  -0.1041   0.5230   1.0000
   5.750   1.1144   0.03615   0.02581  -0.1035   0.5157   1.0000
   6.000   1.1238   0.03891   0.02885  -0.1029   0.5072   1.0000
   6.250   1.1477   0.04024   0.03034  -0.1025   0.5015   1.0000
   6.500   1.1504   0.04382   0.03420  -0.1018   0.4944   1.0000
   6.750   1.1668   0.04593   0.03648  -0.1013   0.4884   1.0000
   7.000   1.1717   0.04940   0.04015  -0.1007   0.4832   1.0000
   7.250   1.1390   0.05703   0.04795  -0.1006   0.4789   1.0000
   7.500   1.0837   0.06689   0.05774  -0.1013   0.4772   1.0000
   7.750   1.0345   0.07615   0.06686  -0.1030   0.4787   1.0000
   8.000   1.0165   0.08231   0.07303  -0.1042   0.4814   1.0000
   8.250   1.0167   0.08703   0.07784  -0.1053   0.4844   1.0000
   8.500   1.3586   0.03890   0.03033  -0.0865   0.3642   1.0000
   8.750   1.3719   0.03569   0.02703  -0.0816   0.3208   1.0000
   9.000   1.3711   0.03490   0.02629  -0.0766   0.2789   1.0000
   9.250   1.3650   0.03566   0.02707  -0.0720   0.2274   1.0000
   9.500   1.3571   0.03768   0.02881  -0.0681   0.1506   1.0000
   9.750   1.3429   0.04062   0.03120  -0.0644   0.1257   1.0000
  10.000   1.3306   0.04393   0.03431  -0.0616   0.1148   1.0000
  10.250   1.3196   0.04745   0.03779  -0.0596   0.1079   1.0000
  10.500   1.3106   0.05106   0.04141  -0.0583   0.1027   1.0000
  10.750   1.3041   0.05466   0.04509  -0.0573   0.0976   1.0000
  11.000   1.2971   0.05844   0.04884  -0.0566   0.0936   1.0000
  11.250   1.2977   0.06161   0.05220  -0.0556   0.0893   1.0000
  11.500   1.3034   0.06429   0.05499  -0.0542   0.0855   1.0000
  11.750   1.3455   0.06447   0.05495  -0.0496   0.0804   1.0000
  12.000   1.3742   0.06669   0.05756  -0.0476   0.0783   1.0000
  12.250   1.3859   0.07004   0.06126  -0.0465   0.0764   1.0000
  12.500   1.3897   0.07386   0.06540  -0.0458   0.0750   1.0000
  12.750   1.3876   0.07814   0.06998  -0.0454   0.0741   1.0000
  13.000   1.3782   0.08301   0.07518  -0.0458   0.0740   1.0000
  13.250   1.3623   0.08860   0.08108  -0.0470   0.0743   1.0000
  13.500   1.3415   0.09500   0.08778  -0.0493   0.0750   1.0000
  13.750   1.3176   0.10226   0.09530  -0.0528   0.0758   1.0000
  14.000   1.2921   0.11041   0.10369  -0.0572   0.0769   1.0000
  14.250   1.2668   0.11930   0.11275  -0.0624   0.0782   1.0000
  14.500   1.2453   0.12836   0.12193  -0.0676   0.0794   1.0000
  14.750   1.2291   0.13711   0.13075  -0.0723   0.0804   1.0000
  15.000   1.1485   0.16632   0.15988  -0.0938   0.0919   1.0000
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