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GOE 406 AIRFOIL (goe406-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 406 AIRFOIL (goe406-il)
Reynolds number: 200,000
Max Cl/Cd: 75.62 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe406-il-200000.txt
Download as CSV file: xf-goe406-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 406 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2644   0.11946   0.11597  -0.0341   1.0000   0.0381
 -10.000  -0.2664   0.11749   0.11406  -0.0331   1.0000   0.0387
  -9.750  -0.2731   0.11608   0.11273  -0.0313   1.0000   0.0391
  -9.500  -0.2622   0.11282   0.10949  -0.0346   0.9974   0.0402
  -9.250  -0.2449   0.10889   0.10554  -0.0421   0.9928   0.0414
  -9.000  -0.2352   0.10456   0.10122  -0.0525   0.9856   0.0421
  -8.750  -0.2076   0.10001   0.09665  -0.0529   0.9839   0.0427
  -8.500  -0.1871   0.09629   0.09293  -0.0561   0.9778   0.0435
  -8.250  -0.1656   0.09249   0.08911  -0.0610   0.9729   0.0446
  -8.000  -0.1483   0.08880   0.08543  -0.0657   0.9647   0.0459
  -7.750  -0.1307   0.08462   0.08123  -0.0754   0.9575   0.0480
  -7.500  -0.1280   0.08071   0.07723  -0.0873   0.9363   0.0486
  -7.250  -0.1089   0.07612   0.07268  -0.0875   0.9320   0.0491
  -7.000  -0.0845   0.07259   0.06914  -0.0887   0.9290   0.0499
  -6.750  -0.0686   0.06957   0.06610  -0.0906   0.9188   0.0507
  -6.500  -0.0426   0.06590   0.06238  -0.0957   0.9137   0.0532
  -6.250  -0.0195   0.06188   0.05791  -0.1079   0.8995   0.0565
  -6.000   0.0024   0.05744   0.05358  -0.1087   0.8945   0.0572
  -5.750   0.0244   0.05457   0.05070  -0.1097   0.8870   0.0581
  -5.500   0.0553   0.05149   0.04754  -0.1133   0.8820   0.0600
  -5.250   0.0753   0.04893   0.04485  -0.1148   0.8712   0.0626
  -5.000   0.0970   0.04590   0.04133  -0.1173   0.8612   0.0663
  -4.750   0.1201   0.04300   0.03845  -0.1183   0.8529   0.0674
  -4.500   0.1398   0.04104   0.03641  -0.1182   0.8434   0.0690
  -4.250   0.1635   0.03914   0.03433  -0.1187   0.8347   0.0724
  -4.000   0.1758   0.03765   0.03237  -0.1163   0.8246   0.0776
  -3.750   0.1983   0.03535   0.03008  -0.1166   0.8172   0.0793
  -3.500   0.2121   0.03405   0.02872  -0.1145   0.8076   0.0817
  -3.000   0.2454   0.03135   0.02548  -0.1104   0.7900   0.0913
  -2.750   0.2673   0.02976   0.02382  -0.1099   0.7827   0.0939
  -2.500   0.2822   0.02888   0.02285  -0.1074   0.7746   0.0989
  -2.250   0.3002   0.02765   0.02132  -0.1053   0.7679   0.1064
  -2.000   0.3199   0.02646   0.02009  -0.1040   0.7616   0.1105
  -1.750   0.3358   0.02578   0.01916  -0.1013   0.7543   0.1218
  -1.500   0.3591   0.02450   0.01785  -0.1007   0.7485   0.1275
  -1.250   0.3749   0.02368   0.01693  -0.0983   0.7413   0.1407
  -1.000   0.3940   0.02281   0.01598  -0.0966   0.7341   0.1583
  -0.750   0.4159   0.02196   0.01505  -0.0955   0.7280   0.1773
  -0.500   0.4549   0.01918   0.01119  -0.0928   0.7214   0.0718
  -0.250   0.4843   0.01847   0.01007  -0.0919   0.7149   0.0656
   0.000   0.5105   0.01756   0.00910  -0.0913   0.7079   0.0648
   0.250   0.5369   0.01689   0.00835  -0.0907   0.6999   0.0646
   0.500   0.5649   0.01643   0.00779  -0.0903   0.6927   0.0660
   0.750   0.5886   0.01581   0.00724  -0.0893   0.6836   0.0684
   1.000   0.6159   0.01538   0.00678  -0.0889   0.6761   0.0697
   1.250   0.6367   0.01507   0.00650  -0.0872   0.6665   0.0717
   1.500   0.6608   0.01478   0.00619  -0.0861   0.6580   0.0747
   1.750   0.6810   0.01447   0.00589  -0.0842   0.6477   0.0792
   2.000   0.7015   0.01428   0.00570  -0.0824   0.6370   0.0899
   2.250   0.9165   0.01248   0.00562  -0.1240   0.6083   1.0000
   2.500   0.9362   0.01257   0.00562  -0.1221   0.5920   1.0000
   2.750   0.9548   0.01270   0.00565  -0.1200   0.5726   1.0000
   3.000   0.9725   0.01286   0.00569  -0.1178   0.5504   1.0000
   3.250   0.9893   0.01310   0.00576  -0.1154   0.5261   1.0000
   3.500   1.0053   0.01340   0.00588  -0.1128   0.5003   1.0000
   3.750   1.0213   0.01377   0.00605  -0.1104   0.4783   1.0000
   4.000   1.0384   0.01416   0.00629  -0.1082   0.4594   1.0000
   4.250   1.0562   0.01458   0.00656  -0.1063   0.4443   1.0000
   4.500   1.0750   0.01499   0.00684  -0.1045   0.4321   1.0000
   4.750   1.0948   0.01537   0.00716  -0.1030   0.4219   1.0000
   5.250   1.1359   0.01617   0.00782  -0.1004   0.4056   1.0000
   5.500   1.1576   0.01659   0.00815  -0.0993   0.3990   1.0000
   5.750   1.1791   0.01699   0.00853  -0.0982   0.3928   1.0000
   6.000   1.2003   0.01736   0.00892  -0.0971   0.3869   1.0000
   6.250   1.2240   0.01782   0.00929  -0.0965   0.3818   1.0000
   6.500   1.2460   0.01823   0.00973  -0.0956   0.3772   1.0000
   6.750   1.2677   0.01862   0.01017  -0.0945   0.3728   1.0000
   7.000   1.2906   0.01903   0.01059  -0.0938   0.3687   1.0000
   7.250   1.3171   0.01955   0.01104  -0.0939   0.3650   1.0000
   7.500   1.3389   0.02000   0.01157  -0.0929   0.3614   1.0000
   7.750   1.3575   0.02039   0.01206  -0.0913   0.3568   1.0000
   8.000   1.3774   0.02079   0.01246  -0.0901   0.3514   1.0000
   8.250   1.3994   0.02130   0.01294  -0.0893   0.3459   1.0000
   8.500   1.4128   0.02165   0.01344  -0.0867   0.3405   1.0000
   8.750   1.4304   0.02204   0.01384  -0.0850   0.3352   1.0000
   9.000   1.4533   0.02257   0.01433  -0.0845   0.3300   1.0000
   9.250   1.4639   0.02294   0.01487  -0.0814   0.3254   1.0000
   9.500   1.4767   0.02329   0.01528  -0.0788   0.3198   1.0000
   9.750   1.4985   0.02380   0.01572  -0.0781   0.3141   1.0000
  10.000   1.5029   0.02413   0.01625  -0.0739   0.3100   1.0000
  10.250   1.5085   0.02444   0.01666  -0.0699   0.3048   1.0000
  10.500   1.5210   0.02481   0.01701  -0.0674   0.2994   1.0000
  10.750   1.5244   0.02523   0.01757  -0.0633   0.2940   1.0000
  11.000   1.5278   0.02563   0.01810  -0.0594   0.2882   1.0000
  11.250   1.5376   0.02608   0.01853  -0.0567   0.2823   1.0000
  11.500   1.5371   0.02665   0.01930  -0.0525   0.2761   1.0000
  11.750   1.5379   0.02726   0.01999  -0.0487   0.2687   1.0000
  12.000   1.5387   0.02804   0.02090  -0.0452   0.2605   1.0000
  12.250   1.5374   0.02899   0.02190  -0.0417   0.2510   1.0000
  12.500   1.5359   0.03015   0.02322  -0.0386   0.2383   1.0000
  12.750   1.5308   0.03176   0.02488  -0.0356   0.2196   1.0000
  13.000   1.5209   0.03405   0.02712  -0.0327   0.1841   1.0000
  13.250   1.4964   0.03786   0.03060  -0.0295   0.1380   1.0000
  13.500   1.4704   0.04224   0.03477  -0.0267   0.1093   1.0000
  13.750   1.4494   0.04650   0.03894  -0.0247   0.0892   1.0000
  14.000   1.4318   0.05069   0.04310  -0.0232   0.0754   1.0000
  14.250   1.4159   0.05494   0.04736  -0.0222   0.0685   1.0000
  14.500   1.4036   0.05899   0.05149  -0.0216   0.0648   1.0000
  14.750   1.3871   0.06377   0.05633  -0.0213   0.0617   1.0000
  15.000   1.3721   0.06857   0.06122  -0.0213   0.0597   1.0000
  15.250   1.3609   0.07304   0.06583  -0.0215   0.0578   1.0000
  15.500   1.3482   0.07784   0.07075  -0.0219   0.0560   1.0000
  15.750   1.3336   0.08301   0.07601  -0.0225   0.0543   1.0000
  16.000   1.3215   0.08787   0.08092  -0.0232   0.0532   1.0000
  16.250   1.3095   0.09260   0.08567  -0.0237   0.0518   1.0000
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