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GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 264 AIRFOIL (goe264-il)
Reynolds number: 200,000
Max Cl/Cd: 79.16 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe264-il-200000.txt
Download as CSV file: xf-goe264-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 264 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
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.3053   0.08824   0.08516  -0.0317   1.0000   0.0370
  -6.250  -0.3100   0.08418   0.08116  -0.0254   1.0000   0.0377
  -6.000  -0.3105   0.08179   0.07880  -0.0224   1.0000   0.0385
  -5.750  -0.3057   0.07946   0.07650  -0.0221   0.9996   0.0396
  -5.500  -0.2681   0.07485   0.07183  -0.0303   0.9952   0.0420
  -5.250  -0.1934   0.07059   0.06733  -0.0513   0.9888   0.0467
  -5.000  -0.1459   0.06385   0.06045  -0.0624   0.9847   0.0475
  -4.750  -0.1303   0.05933   0.05599  -0.0618   0.9804   0.0492
  -4.500  -0.0951   0.05571   0.05233  -0.0666   0.9750   0.0519
  -4.250  -0.0116   0.05246   0.04860  -0.0832   0.9715   0.0595
  -4.000   0.0149   0.04636   0.04255  -0.0869   0.9668   0.0614
  -3.750   0.0501   0.04333   0.03949  -0.0904   0.9614   0.0646
  -3.500   0.1176   0.03958   0.03526  -0.1010   0.9578   0.0740
  -3.250   0.1438   0.03664   0.03241  -0.1025   0.9501   0.0768
  -3.000   0.1987   0.03464   0.02992  -0.1085   0.9434   0.0876
  -2.750   0.2235   0.03157   0.02695  -0.1096   0.9324   0.0897
  -2.500   0.2523   0.02989   0.02520  -0.1103   0.9205   0.0951
  -2.250   0.2872   0.02789   0.02293  -0.1120   0.9078   0.1040
  -2.000   0.3134   0.02637   0.02135  -0.1119   0.8925   0.1086
  -1.750   0.3453   0.02479   0.01948  -0.1126   0.8762   0.1182
  -1.500   0.3711   0.02343   0.01802  -0.1122   0.8583   0.1229
  -1.250   0.4005   0.02219   0.01651  -0.1122   0.8399   0.1334
  -1.000   0.4425   0.01793   0.01129  -0.1132   0.8223   0.0891
  -0.750   0.4715   0.01655   0.00959  -0.1128   0.8004   0.0844
  -0.500   0.4999   0.01543   0.00814  -0.1125   0.7783   0.0837
  -0.250   0.5279   0.01470   0.00711  -0.1120   0.7544   0.0851
   0.000   0.5556   0.01414   0.00628  -0.1116   0.7308   0.0879
   0.250   0.5829   0.01359   0.00558  -0.1113   0.7079   0.0903
   0.500   0.6102   0.01330   0.00516  -0.1109   0.6854   0.0935
   0.750   0.6375   0.01312   0.00480  -0.1105   0.6652   0.0981
   1.000   0.6648   0.01295   0.00452  -0.1103   0.6463   0.1041
   1.250   0.6922   0.01299   0.00447  -0.1101   0.6278   0.1146
   1.500   0.7198   0.01291   0.00437  -0.1100   0.6107   0.1271
   1.750   0.7476   0.01283   0.00431  -0.1099   0.5946   0.1545
   2.000   0.7754   0.01274   0.00433  -0.1100   0.5788   0.2108
   2.250   0.8029   0.01267   0.00441  -0.1101   0.5635   0.2860
   2.500   0.8216   0.01147   0.00437  -0.1078   0.5499   1.0000
   2.750   0.8490   0.01171   0.00448  -0.1077   0.5357   1.0000
   3.000   0.8764   0.01196   0.00461  -0.1076   0.5223   1.0000
   3.250   0.9036   0.01223   0.00477  -0.1074   0.5096   1.0000
   3.500   0.9307   0.01250   0.00496  -0.1073   0.4977   1.0000
   3.750   0.9578   0.01279   0.00516  -0.1072   0.4862   1.0000
   4.000   0.9849   0.01306   0.00540  -0.1071   0.4746   1.0000
   4.250   1.0119   0.01336   0.00567  -0.1069   0.4639   1.0000
   4.500   1.0387   0.01369   0.00596  -0.1068   0.4540   1.0000
   4.750   1.0655   0.01399   0.00625  -0.1066   0.4441   1.0000
   5.000   1.0924   0.01432   0.00660  -0.1065   0.4350   1.0000
   5.250   1.1191   0.01470   0.00694  -0.1064   0.4275   1.0000
   5.500   1.1459   0.01502   0.00738  -0.1063   0.4194   1.0000
   5.750   1.1719   0.01532   0.00768  -0.1060   0.4088   1.0000
   6.000   1.1965   0.01544   0.00783  -0.1055   0.3909   1.0000
   6.250   1.2211   0.01560   0.00801  -0.1049   0.3732   1.0000
   6.500   1.2461   0.01584   0.00832  -0.1045   0.3586   1.0000
   6.750   1.2701   0.01610   0.00858  -0.1039   0.3396   1.0000
   7.000   1.2934   0.01634   0.00887  -0.1032   0.3085   1.0000
   7.250   1.2977   0.01908   0.01033  -0.1005   0.1003   1.0000
   7.500   1.3071   0.02154   0.01244  -0.0980   0.0467   1.0000
   7.750   1.3235   0.02285   0.01395  -0.0963   0.0409   1.0000
   8.000   1.3373   0.02425   0.01549  -0.0943   0.0374   1.0000
   8.250   1.3429   0.02633   0.01766  -0.0913   0.0347   1.0000
   8.500   1.3543   0.02773   0.01917  -0.0889   0.0328   1.0000
   8.750   1.3649   0.02912   0.02066  -0.0865   0.0310   1.0000
   9.000   1.3725   0.03071   0.02234  -0.0837   0.0299   1.0000
   9.250   1.3782   0.03234   0.02404  -0.0807   0.0289   1.0000
   9.500   1.3851   0.03412   0.02590  -0.0779   0.0281   1.0000
   9.750   1.3950   0.03606   0.02787  -0.0756   0.0274   1.0000
  10.000   1.4105   0.03843   0.03025  -0.0741   0.0264   1.0000
  10.250   1.4366   0.04182   0.03375  -0.0741   0.0251   1.0000
  10.500   1.4506   0.04377   0.03591  -0.0723   0.0246   1.0000
  10.750   1.4696   0.04660   0.03897  -0.0713   0.0244   1.0000
  11.000   1.4870   0.05009   0.04276  -0.0702   0.0245   1.0000
  11.250   1.5033   0.05494   0.04789  -0.0695   0.0250   1.0000
  11.500   1.5239   0.05833   0.05146  -0.0687   0.0260   1.0000
  11.750   1.5028   0.05949   0.05318  -0.0621   0.0279   1.0000
  12.000   1.4878   0.06675   0.06102  -0.0585   0.0323   1.0000
  12.250   1.3771   0.05874   0.05282  -0.0441   0.0267   1.0000
  12.500   1.3411   0.06330   0.05783  -0.0407   0.0279   1.0000
  12.750   1.3083   0.06940   0.06435  -0.0387   0.0294   1.0000
  13.000   1.2828   0.07518   0.07040  -0.0377   0.0305   1.0000
  13.250   1.2571   0.08075   0.07619  -0.0374   0.0312   1.0000
  13.500   1.2301   0.08621   0.08185  -0.0377   0.0316   1.0000
  13.750   1.2011   0.09148   0.08731  -0.0384   0.0319   1.0000
  14.000   1.1664   0.09605   0.09206  -0.0392   0.0318   1.0000
  14.250   1.1351   0.10116   0.09734  -0.0410   0.0319   1.0000
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