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GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 549 AIRFOIL (goe549-il)
Reynolds number: 200,000
Max Cl/Cd: 74.37 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe549-il-200000.txt
Download as CSV file: xf-goe549-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2522   0.09732   0.09417  -0.0482   0.9938   0.0574
  -9.000  -0.2324   0.09315   0.08999  -0.0533   0.9868   0.0595
  -8.750  -0.2336   0.08521   0.08207  -0.0720   0.9727   0.0642
  -8.500  -0.2187   0.07963   0.07651  -0.0748   0.9640   0.0654
  -8.250  -0.1856   0.07751   0.07436  -0.0745   0.9596   0.0672
  -8.000  -0.1602   0.07386   0.07069  -0.0793   0.9488   0.0705
  -7.750  -0.1828   0.06029   0.05667  -0.1089   0.9179   0.0767
  -7.500  -0.1430   0.05830   0.05494  -0.1058   0.9102   0.0785
  -7.250  -0.1191   0.05679   0.05339  -0.1055   0.8946   0.0811
  -7.000  -0.1133   0.05316   0.04959  -0.1084   0.8734   0.0854
  -6.750  -0.1283   0.04717   0.04309  -0.1122   0.8525   0.0916
  -6.500  -0.1093   0.04542   0.04138  -0.1109   0.8371   0.0938
  -6.250  -0.0950   0.04365   0.03948  -0.1103   0.8217   0.0983
  -6.000  -0.0918   0.04010   0.03548  -0.1106   0.8070   0.1074
  -5.750  -0.0907   0.02938   0.02344  -0.1089   0.7956   0.0668
  -5.500  -0.0719   0.02567   0.01918  -0.1074   0.7854   0.0587
  -5.250  -0.0514   0.02316   0.01612  -0.1060   0.7752   0.0572
  -5.000  -0.0278   0.02212   0.01488  -0.1053   0.7650   0.0593
  -4.750  -0.0027   0.02081   0.01323  -0.1046   0.7573   0.0599
  -4.500   0.0218   0.01984   0.01206  -0.1038   0.7476   0.0613
  -4.250   0.0480   0.01892   0.01090  -0.1032   0.7404   0.0623
  -4.000   0.0736   0.01804   0.00987  -0.1026   0.7320   0.0626
  -3.750   0.1003   0.01731   0.00897  -0.1021   0.7256   0.0632
  -3.500   0.1258   0.01673   0.00833  -0.1015   0.7177   0.0639
  -3.250   0.1515   0.01603   0.00754  -0.1010   0.7117   0.0657
  -3.000   0.1761   0.01551   0.00704  -0.1004   0.7046   0.0678
  -2.750   0.2017   0.01512   0.00661  -0.0999   0.6982   0.0696
  -2.500   0.2274   0.01483   0.00626  -0.0993   0.6922   0.0721
  -2.250   0.2531   0.01459   0.00595  -0.0988   0.6855   0.0752
  -2.000   0.2798   0.01434   0.00562  -0.0985   0.6802   0.0814
  -1.750   0.3047   0.01410   0.00545  -0.0978   0.6733   0.0969
  -1.500   0.3266   0.01317   0.00524  -0.0971   0.6675   0.2871
  -1.250   0.3479   0.01265   0.00532  -0.0960   0.6619   0.4632
  -1.000   0.3701   0.01245   0.00544  -0.0948   0.6555   0.5754
  -0.750   0.3948   0.01236   0.00546  -0.0938   0.6503   0.6451
  -0.500   0.4173   0.01224   0.00556  -0.0925   0.6444   0.7126
  -0.250   0.4424   0.01201   0.00561  -0.0913   0.6385   0.8059
   0.000   0.5323   0.01191   0.00555  -0.1035   0.6319   0.9821
   0.250   0.5706   0.01203   0.00558  -0.1059   0.6252   1.0000
   0.500   0.5951   0.01220   0.00559  -0.1053   0.6198   1.0000
   0.750   0.6188   0.01240   0.00569  -0.1046   0.6143   1.0000
   1.000   0.6421   0.01256   0.00578  -0.1038   0.6080   1.0000
   1.250   0.6679   0.01275   0.00582  -0.1034   0.6029   1.0000
   1.500   0.6910   0.01294   0.00598  -0.1025   0.5969   1.0000
   1.750   0.7152   0.01310   0.00608  -0.1018   0.5907   1.0000
   2.000   0.7420   0.01330   0.00614  -0.1015   0.5858   1.0000
   2.250   0.7641   0.01347   0.00634  -0.1005   0.5790   1.0000
   2.500   0.7893   0.01362   0.00641  -0.1000   0.5732   1.0000
   2.750   0.8148   0.01381   0.00653  -0.0995   0.5677   1.0000
   3.000   0.8378   0.01395   0.00669  -0.0986   0.5607   1.0000
   3.250   0.8643   0.01409   0.00674  -0.0983   0.5553   1.0000
   3.500   0.8874   0.01426   0.00694  -0.0974   0.5486   1.0000
   3.750   0.9123   0.01438   0.00702  -0.0968   0.5420   1.0000
   4.000   0.9378   0.01453   0.00713  -0.0964   0.5362   1.0000
   4.250   0.9608   0.01468   0.00731  -0.0955   0.5289   1.0000
   4.500   0.9876   0.01479   0.00734  -0.0952   0.5233   1.0000
   4.750   1.0094   0.01496   0.00758  -0.0942   0.5153   1.0000
   5.000   1.0351   0.01507   0.00762  -0.0937   0.5090   1.0000
   5.250   1.0578   0.01526   0.00788  -0.0928   0.5016   1.0000
   5.500   1.0826   0.01539   0.00797  -0.0923   0.4947   1.0000
   5.750   1.1057   0.01559   0.00820  -0.0915   0.4873   1.0000
   6.000   1.1297   0.01575   0.00834  -0.0908   0.4801   1.0000
   6.250   1.1532   0.01598   0.00860  -0.0901   0.4731   1.0000
   6.500   1.1763   0.01618   0.00882  -0.0893   0.4656   1.0000
   6.750   1.1990   0.01640   0.00904  -0.0884   0.4577   1.0000
   7.000   1.2211   0.01656   0.00919  -0.0874   0.4490   1.0000
   7.250   1.2418   0.01679   0.00947  -0.0862   0.4399   1.0000
   7.500   1.2651   0.01701   0.00961  -0.0855   0.4320   1.0000
   7.750   1.2837   0.01728   0.00998  -0.0840   0.4230   1.0000
   8.000   1.3067   0.01757   0.01022  -0.0833   0.4157   1.0000
   8.250   1.3244   0.01786   0.01062  -0.0816   0.4068   1.0000
   8.500   1.3463   0.01820   0.01093  -0.0808   0.3998   1.0000
   8.750   1.3636   0.01853   0.01136  -0.0791   0.3916   1.0000
   9.000   1.3835   0.01889   0.01171  -0.0779   0.3840   1.0000
   9.250   1.3990   0.01924   0.01214  -0.0760   0.3756   1.0000
   9.500   1.4150   0.01961   0.01253  -0.0742   0.3670   1.0000
   9.750   1.4295   0.01999   0.01296  -0.0722   0.3588   1.0000
  10.000   1.4432   0.02042   0.01344  -0.0700   0.3514   1.0000
  10.250   1.4554   0.02086   0.01396  -0.0676   0.3445   1.0000
  10.500   1.4687   0.02135   0.01449  -0.0655   0.3380   1.0000
  10.750   1.4775   0.02187   0.01511  -0.0628   0.3305   1.0000
  11.000   1.4882   0.02244   0.01570  -0.0604   0.3232   1.0000
  11.250   1.4943   0.02309   0.01646  -0.0576   0.3147   1.0000
  11.500   1.5005   0.02383   0.01727  -0.0550   0.3060   1.0000
  11.750   1.5050   0.02470   0.01817  -0.0524   0.2966   1.0000
  12.000   1.5090   0.02568   0.01928  -0.0499   0.2869   1.0000
  12.250   1.5124   0.02681   0.02046  -0.0476   0.2776   1.0000
  12.500   1.5138   0.02814   0.02185  -0.0454   0.2669   1.0000
  12.750   1.5147   0.02964   0.02345  -0.0433   0.2553   1.0000
  13.000   1.5128   0.03145   0.02533  -0.0414   0.2419   1.0000
  13.250   1.5084   0.03362   0.02754  -0.0396   0.2268   1.0000
  13.500   1.5009   0.03622   0.03015  -0.0380   0.2099   1.0000
  13.750   1.4892   0.03942   0.03332  -0.0366   0.1886   1.0000
  14.000   1.4714   0.04345   0.03726  -0.0355   0.1646   1.0000
  14.500   1.4268   0.05326   0.04683  -0.0344   0.1172   1.0000
  14.750   1.4052   0.05847   0.05197  -0.0344   0.1027   1.0000
  15.000   1.3852   0.06371   0.05718  -0.0346   0.0922   1.0000
  15.250   1.3677   0.06889   0.06238  -0.0350   0.0833   1.0000
  15.500   1.3489   0.07444   0.06795  -0.0357   0.0755   1.0000
  15.750   1.3337   0.07969   0.07325  -0.0366   0.0673   1.0000
  16.000   1.3222   0.08461   0.07823  -0.0374   0.0609   1.0000
  16.250   1.3096   0.08980   0.08341  -0.0386   0.0559   1.0000
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