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GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 549 AIRFOIL (goe549-il)
Reynolds number: 100,000
Max Cl/Cd: 52.81 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe549-il-100000-n5.txt
Download as CSV file: xf-goe549-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 549 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2562   0.10876   0.10400  -0.0463   1.0000   0.0672
  -9.750  -0.2576   0.10637   0.10170  -0.0457   1.0000   0.0678
  -9.500  -0.2739   0.09696   0.09232  -0.0523   0.9922   0.0438
  -9.250  -0.2597   0.09257   0.08792  -0.0562   0.9806   0.0435
  -9.000  -0.2462   0.08817   0.08351  -0.0604   0.9685   0.0430
  -8.750  -0.2354   0.08272   0.07807  -0.0664   0.9560   0.0430
  -8.500  -0.2228   0.07718   0.07251  -0.0729   0.9438   0.0426
  -8.250  -0.2120   0.07124   0.06655  -0.0800   0.9300   0.0420
  -8.000  -0.2089   0.06387   0.05913  -0.0893   0.9123   0.0412
  -7.750  -0.2129   0.05512   0.05015  -0.0987   0.8941   0.0401
  -7.500  -0.2174   0.04856   0.04322  -0.1030   0.8772   0.0395
  -7.250  -0.2149   0.04367   0.03790  -0.1046   0.8621   0.0393
  -7.000  -0.2063   0.03973   0.03349  -0.1051   0.8484   0.0395
  -6.750  -0.1925   0.03668   0.02999  -0.1051   0.8358   0.0406
  -6.500  -0.1779   0.03405   0.02685  -0.1044   0.8225   0.0422
  -6.250  -0.1608   0.03172   0.02398  -0.1036   0.8098   0.0433
  -6.000  -0.1407   0.02974   0.02150  -0.1028   0.7981   0.0439
  -5.750  -0.1185   0.02792   0.01936  -0.1023   0.7878   0.0452
  -5.500  -0.0960   0.02676   0.01807  -0.1018   0.7762   0.0470
  -5.250  -0.0723   0.02557   0.01664  -0.1012   0.7658   0.0483
  -5.000  -0.0468   0.02436   0.01516  -0.1007   0.7571   0.0492
  -4.750  -0.0225   0.02335   0.01395  -0.1001   0.7467   0.0501
  -4.500   0.0032   0.02249   0.01289  -0.0995   0.7383   0.0518
  -4.250   0.0287   0.02182   0.01200  -0.0990   0.7296   0.0537
  -4.000   0.0534   0.02099   0.01113  -0.0984   0.7217   0.0551
  -3.750   0.0782   0.02035   0.01043  -0.0978   0.7139   0.0564
  -3.500   0.1031   0.01982   0.00984  -0.0972   0.7068   0.0579
  -3.250   0.1280   0.01938   0.00929  -0.0966   0.6996   0.0597
  -3.000   0.1535   0.01900   0.00877  -0.0960   0.6932   0.0619
  -2.750   0.1785   0.01868   0.00837  -0.0955   0.6861   0.0652
  -2.500   0.2047   0.01834   0.00796  -0.0951   0.6806   0.0713
  -2.250   0.2296   0.01808   0.00768  -0.0946   0.6737   0.0795
  -2.000   0.2555   0.01775   0.00736  -0.0941   0.6678   0.0998
  -1.750   0.2803   0.01723   0.00706  -0.0937   0.6622   0.1656
  -1.500   0.3036   0.01666   0.00702  -0.0932   0.6557   0.3152
  -1.250   0.3285   0.01624   0.00702  -0.0927   0.6505   0.4444
  -1.000   0.3517   0.01605   0.00713  -0.0916   0.6444   0.5564
  -0.750   0.3752   0.01590   0.00718  -0.0904   0.6383   0.6423
  -0.500   0.4004   0.01565   0.00714  -0.0892   0.6334   0.7348
  -0.250   0.4612   0.01532   0.00718  -0.0948   0.6258   0.9259
   0.000   0.5147   0.01539   0.00701  -0.1001   0.6195   1.0000
   0.250   0.5374   0.01558   0.00704  -0.0993   0.6136   1.0000
   0.500   0.5604   0.01577   0.00709  -0.0985   0.6073   1.0000
   0.750   0.5858   0.01594   0.00707  -0.0980   0.6023   1.0000
   1.000   0.6082   0.01616   0.00722  -0.0971   0.5959   1.0000
   1.250   0.6324   0.01636   0.00730  -0.0965   0.5899   1.0000
   1.500   0.6583   0.01655   0.00734  -0.0961   0.5850   1.0000
   1.750   0.6803   0.01679   0.00756  -0.0952   0.5781   1.0000
   2.000   0.7053   0.01698   0.00765  -0.0946   0.5725   1.0000
   2.250   0.7297   0.01720   0.00780  -0.0940   0.5669   1.0000
   2.500   0.7526   0.01744   0.00801  -0.0932   0.5602   1.0000
   2.750   0.7784   0.01761   0.00809  -0.0928   0.5549   1.0000
   3.000   0.8008   0.01788   0.00836  -0.0919   0.5482   1.0000
   3.250   0.8249   0.01808   0.00853  -0.0913   0.5420   1.0000
   3.500   0.8497   0.01828   0.00868  -0.0907   0.5363   1.0000
   3.750   0.8717   0.01855   0.00897  -0.0898   0.5291   1.0000
   4.000   0.8972   0.01871   0.00908  -0.0893   0.5236   1.0000
   4.250   0.9186   0.01901   0.00942  -0.0883   0.5162   1.0000
   4.500   0.9427   0.01921   0.00960  -0.0876   0.5100   1.0000
   4.750   0.9654   0.01947   0.00989  -0.0868   0.5034   1.0000
   5.000   0.9879   0.01972   0.01015  -0.0860   0.4963   1.0000
   5.250   1.0118   0.01993   0.01035  -0.0853   0.4903   1.0000
   5.500   1.0328   0.02025   0.01075  -0.0842   0.4827   1.0000
   5.750   1.0576   0.02043   0.01088  -0.0837   0.4771   1.0000
   6.000   1.0770   0.02083   0.01137  -0.0825   0.4691   1.0000
   6.250   1.1006   0.02105   0.01158  -0.0818   0.4630   1.0000
   6.500   1.1205   0.02144   0.01206  -0.0806   0.4557   1.0000
   6.750   1.1427   0.02174   0.01237  -0.0797   0.4492   1.0000
   7.000   1.1633   0.02211   0.01280  -0.0787   0.4426   1.0000
   7.250   1.1836   0.02249   0.01322  -0.0776   0.4356   1.0000
   7.500   1.2057   0.02283   0.01360  -0.0767   0.4298   1.0000
   7.750   1.2236   0.02333   0.01420  -0.0753   0.4228   1.0000
   8.000   1.2463   0.02365   0.01452  -0.0746   0.4173   1.0000
   8.250   1.2622   0.02420   0.01519  -0.0730   0.4100   1.0000
   8.500   1.2819   0.02458   0.01561  -0.0718   0.4033   1.0000
   8.750   1.2978   0.02511   0.01624  -0.0701   0.3963   1.0000
   9.000   1.3145   0.02557   0.01675  -0.0686   0.3891   1.0000
   9.250   1.3296   0.02609   0.01734  -0.0668   0.3821   1.0000
   9.500   1.3424   0.02665   0.01801  -0.0647   0.3753   1.0000
   9.750   1.3600   0.02713   0.01851  -0.0633   0.3697   1.0000
  10.000   1.3682   0.02791   0.01946  -0.0608   0.3634   1.0000
  10.250   1.3836   0.02846   0.02005  -0.0592   0.3576   1.0000
  10.500   1.3914   0.02928   0.02099  -0.0567   0.3508   1.0000
  10.750   1.4005   0.03002   0.02183  -0.0545   0.3436   1.0000
  11.000   1.4074   0.03091   0.02282  -0.0522   0.3362   1.0000
  11.250   1.4124   0.03187   0.02385  -0.0499   0.3281   1.0000
  11.500   1.4128   0.03313   0.02522  -0.0474   0.3190   1.0000
  11.750   1.4174   0.03418   0.02627  -0.0453   0.3096   1.0000
  12.000   1.4118   0.03605   0.02831  -0.0429   0.3000   1.0000
  12.250   1.4099   0.03781   0.03015  -0.0410   0.2902   1.0000
  12.500   1.4081   0.03964   0.03201  -0.0393   0.2799   1.0000
  12.750   1.4005   0.04225   0.03479  -0.0378   0.2698   1.0000
  13.000   1.3933   0.04499   0.03762  -0.0367   0.2588   1.0000
  13.250   1.3858   0.04792   0.04062  -0.0358   0.2475   1.0000
  13.500   1.3776   0.05109   0.04385  -0.0352   0.2359   1.0000
  13.750   1.3670   0.05479   0.04765  -0.0349   0.2237   1.0000
  14.000   1.3564   0.05867   0.05162  -0.0348   0.2111   1.0000
  14.250   1.3456   0.06272   0.05573  -0.0349   0.1982   1.0000
  14.500   1.3339   0.06701   0.06007  -0.0352   0.1842   1.0000
  14.750   1.3216   0.07154   0.06462  -0.0357   0.1693   1.0000
  15.000   1.3076   0.07643   0.06949  -0.0364   0.1536   1.0000
  15.250   1.2926   0.08164   0.07467  -0.0374   0.1379   1.0000
  15.500   1.2769   0.08715   0.08015  -0.0386   0.1236   1.0000
  15.750   1.2614   0.09280   0.08578  -0.0401   0.1121   1.0000
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