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GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 408 AIRFOIL (goe408-il)
Reynolds number: 200,000
Max Cl/Cd: 78.35 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe408-il-200000.txt
Download as CSV file: xf-goe408-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 408 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4066   0.10956   0.10606  -0.0243   1.0000   0.0351
  -8.500  -0.4106   0.10703   0.10359  -0.0249   1.0000   0.0351
  -8.250  -0.4179   0.10470   0.10130  -0.0252   1.0000   0.0352
  -8.000  -0.4094   0.09835   0.09497  -0.0232   1.0000   0.0357
  -7.750  -0.3988   0.09431   0.09093  -0.0212   1.0000   0.0362
  -7.500  -0.4001   0.09163   0.08830  -0.0200   1.0000   0.0365
  -7.250  -0.4011   0.08898   0.08568  -0.0186   1.0000   0.0372
  -7.000  -0.4008   0.08622   0.08296  -0.0182   1.0000   0.0381
  -6.750  -0.4000   0.08338   0.08015  -0.0184   1.0000   0.0385
  -6.500  -0.3988   0.08043   0.07723  -0.0187   1.0000   0.0394
  -6.250  -0.3966   0.07754   0.07437  -0.0193   1.0000   0.0412
  -6.000  -0.3921   0.07470   0.07152  -0.0209   1.0000   0.0428
  -5.750  -0.3795   0.07252   0.06916  -0.0260   1.0000   0.0442
  -5.500  -0.3735   0.06977   0.06631  -0.0260   1.0000   0.0444
  -5.250  -0.3684   0.06711   0.06356  -0.0249   1.0000   0.0445
  -5.000  -0.3621   0.06063   0.05715  -0.0254   0.9979   0.0453
  -4.750  -0.3361   0.05671   0.05323  -0.0280   0.9932   0.0466
  -4.500  -0.3034   0.05312   0.04954  -0.0320   0.9871   0.0489
  -4.250  -0.2477   0.05080   0.04656  -0.0386   0.9780   0.0558
  -4.000  -0.2258   0.04417   0.03994  -0.0413   0.9724   0.0574
  -3.750  -0.1972   0.04120   0.03696  -0.0433   0.9647   0.0602
  -3.500  -0.1602   0.03848   0.03359  -0.0449   0.9547   0.0696
  -3.250  -0.1332   0.03520   0.03047  -0.0469   0.9490   0.0734
  -3.000  -0.1012   0.03294   0.02773  -0.0474   0.9393   0.0840
  -2.750  -0.0758   0.03057   0.02542  -0.0480   0.9301   0.0887
  -2.500  -0.0413   0.02837   0.02296  -0.0495   0.9248   0.1013
  -2.250  -0.0134   0.02668   0.02099  -0.0493   0.9146   0.1135
  -2.000   0.0199   0.02486   0.01900  -0.0505   0.9094   0.1281
  -1.750   0.0486   0.02319   0.01723  -0.0507   0.9002   0.1434
  -1.500   0.0839   0.02152   0.01543  -0.0522   0.8940   0.1606
  -1.000   0.1726   0.01733   0.01005  -0.0546   0.8792   0.0934
  -0.750   0.2171   0.01581   0.00830  -0.0576   0.8694   0.0887
  -0.500   0.2657   0.01487   0.00720  -0.0617   0.8581   0.0900
  -0.250   0.3192   0.01396   0.00615  -0.0669   0.8456   0.0899
   0.000   0.3666   0.01330   0.00538  -0.0709   0.8306   0.0906
   0.250   0.4077   0.01285   0.00485  -0.0736   0.8139   0.0924
   0.500   0.4436   0.01255   0.00448  -0.0751   0.7969   0.0947
   0.750   0.4754   0.01227   0.00418  -0.0758   0.7799   0.0993
   1.000   0.5041   0.01211   0.00399  -0.0759   0.7635   0.1041
   1.250   0.5311   0.01203   0.00384  -0.0755   0.7475   0.1094
   1.500   0.5566   0.01195   0.00372  -0.0748   0.7319   0.1177
   1.750   0.7445   0.01038   0.00396  -0.1116   0.7043   1.0000
   2.000   0.7673   0.01058   0.00403  -0.1103   0.6853   1.0000
   2.250   0.7875   0.01074   0.00410  -0.1084   0.6636   1.0000
   2.500   0.8084   0.01092   0.00416  -0.1067   0.6427   1.0000
   2.750   0.8289   0.01109   0.00424  -0.1049   0.6224   1.0000
   3.000   0.8502   0.01127   0.00437  -0.1033   0.6041   1.0000
   3.250   0.8719   0.01145   0.00449  -0.1019   0.5868   1.0000
   3.500   0.8937   0.01165   0.00463  -0.1005   0.5704   1.0000
   3.750   0.9155   0.01185   0.00479  -0.0990   0.5542   1.0000
   4.000   0.9373   0.01207   0.00498  -0.0976   0.5384   1.0000
   4.250   0.9589   0.01230   0.00517  -0.0962   0.5226   1.0000
   4.500   0.9800   0.01253   0.00537  -0.0947   0.5061   1.0000
   4.750   1.0005   0.01277   0.00560  -0.0931   0.4879   1.0000
   5.000   1.0209   0.01303   0.00585  -0.0914   0.4700   1.0000
   5.250   1.0408   0.01331   0.00610  -0.0897   0.4516   1.0000
   5.500   1.0605   0.01362   0.00637  -0.0879   0.4333   1.0000
   5.750   1.0794   0.01391   0.00667  -0.0860   0.4121   1.0000
   6.000   1.0974   0.01424   0.00696  -0.0840   0.3899   1.0000
   6.250   1.1159   0.01457   0.00733  -0.0820   0.3679   1.0000
   6.500   1.1330   0.01496   0.00768  -0.0798   0.3437   1.0000
   6.750   1.1488   0.01539   0.00805  -0.0774   0.3120   1.0000
   7.000   1.1636   0.01591   0.00846  -0.0749   0.2774   1.0000
   7.250   1.1770   0.01656   0.00897  -0.0722   0.2433   1.0000
   7.500   1.1914   0.01721   0.00952  -0.0697   0.2154   1.0000
   7.750   1.2059   0.01787   0.01011  -0.0673   0.1908   1.0000
   8.000   1.2190   0.01862   0.01077  -0.0647   0.1638   1.0000
   8.250   1.2294   0.01957   0.01156  -0.0617   0.1272   1.0000
   8.500   1.2293   0.02130   0.01276  -0.0569   0.0662   1.0000
   8.750   1.2261   0.02294   0.01434  -0.0513   0.0531   1.0000
   9.000   1.2290   0.02412   0.01566  -0.0469   0.0465   1.0000
   9.250   1.2245   0.02575   0.01732  -0.0414   0.0428   1.0000
   9.500   1.2294   0.02696   0.01866  -0.0376   0.0396   1.0000
   9.750   1.2357   0.02811   0.01989  -0.0343   0.0364   1.0000
  10.000   1.2390   0.02955   0.02136  -0.0308   0.0342   1.0000
  10.250   1.2401   0.03187   0.02368  -0.0273   0.0324   1.0000
  10.500   1.2500   0.03316   0.02512  -0.0248   0.0309   1.0000
  10.750   1.2608   0.03473   0.02681  -0.0226   0.0298   1.0000
  11.000   1.2719   0.03645   0.02867  -0.0205   0.0284   1.0000
  11.250   1.2815   0.03810   0.03044  -0.0184   0.0274   1.0000
  11.500   1.2890   0.03982   0.03223  -0.0164   0.0260   1.0000
  11.750   1.3018   0.04233   0.03480  -0.0151   0.0251   1.0000
  12.000   1.3110   0.04593   0.03864  -0.0135   0.0242   1.0000
  12.250   1.3116   0.04811   0.04108  -0.0110   0.0239   1.0000
  12.500   1.3087   0.05076   0.04402  -0.0083   0.0236   1.0000
  12.750   1.3045   0.05368   0.04719  -0.0061   0.0234   1.0000
  13.000   1.2983   0.05697   0.05073  -0.0042   0.0235   1.0000
  13.250   1.2887   0.06056   0.05457  -0.0027   0.0235   1.0000
  13.500   1.2737   0.06453   0.05881  -0.0015   0.0234   1.0000
  13.750   1.2604   0.06877   0.06329  -0.0010   0.0235   1.0000
  14.000   1.2436   0.07348   0.06824  -0.0012   0.0236   1.0000
  14.250   1.2254   0.07859   0.07357  -0.0021   0.0236   1.0000
  14.500   1.2090   0.08423   0.07937  -0.0031   0.0240   1.0000
  14.750   1.1872   0.09028   0.08563  -0.0054   0.0239   1.0000
  15.000   1.1666   0.09686   0.09235  -0.0080   0.0241   1.0000
  15.250   1.1468   0.10417   0.09982  -0.0105   0.0244   1.0000
  15.500   1.1339   0.10961   0.10540  -0.0138   0.0246   1.0000
  15.750   1.1151   0.11678   0.11274  -0.0183   0.0248   1.0000
  16.000   1.0937   0.12535   0.12150  -0.0243   0.0251   1.0000
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