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GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 553 AIRFOIL (goe553-il)
Reynolds number: 100,000
Max Cl/Cd: 54.52 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe553-il-100000-n5.txt
Download as CSV file: xf-goe553-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 553 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  -0.2677   0.10802   0.10301  -0.0419   1.0000   0.0791
  -9.750  -0.2829   0.10508   0.10018  -0.0449   1.0000   0.0799
  -9.500  -0.2913   0.10204   0.09724  -0.0461   1.0000   0.0800
  -9.250  -0.2736   0.09888   0.09412  -0.0432   1.0000   0.0812
  -9.000  -0.2664   0.09669   0.09200  -0.0415   1.0000   0.0825
  -8.500  -0.2915   0.07823   0.07356  -0.0577   0.9762   0.0523
  -8.250  -0.2732   0.07421   0.06953  -0.0619   0.9607   0.0518
  -8.000  -0.2581   0.06810   0.06339  -0.0700   0.9426   0.0512
  -7.750  -0.2499   0.05810   0.05320  -0.0846   0.9194   0.0508
  -7.500  -0.2403   0.05046   0.04517  -0.0940   0.8988   0.0509
  -7.250  -0.2254   0.04482   0.03909  -0.0993   0.8800   0.0507
  -7.000  -0.2071   0.04037   0.03416  -0.1025   0.8620   0.0505
  -6.750  -0.1867   0.03673   0.03001  -0.1044   0.8447   0.0505
  -6.500  -0.1643   0.03380   0.02658  -0.1056   0.8284   0.0509
  -6.250  -0.1404   0.03135   0.02354  -0.1063   0.8129   0.0519
  -6.000  -0.1153   0.02941   0.02113  -0.1067   0.7986   0.0527
  -5.750  -0.0891   0.02783   0.01929  -0.1069   0.7856   0.0532
  -5.500  -0.0630   0.02647   0.01767  -0.1069   0.7728   0.0537
  -5.250  -0.0368   0.02528   0.01625  -0.1067   0.7607   0.0543
  -5.000  -0.0098   0.02422   0.01496  -0.1066   0.7501   0.0550
  -4.750   0.0168   0.02331   0.01386  -0.1064   0.7393   0.0559
  -4.500   0.0436   0.02255   0.01292  -0.1061   0.7294   0.0576
  -4.250   0.0706   0.02183   0.01200  -0.1058   0.7201   0.0593
  -4.000   0.0972   0.02118   0.01117  -0.1054   0.7107   0.0605
  -3.750   0.1236   0.02049   0.01044  -0.1050   0.7022   0.0616
  -3.500   0.1494   0.01995   0.00989  -0.1045   0.6934   0.0630
  -3.250   0.1757   0.01949   0.00938  -0.1041   0.6851   0.0647
  -3.000   0.2018   0.01912   0.00895  -0.1037   0.6769   0.0672
  -2.750   0.2280   0.01880   0.00854  -0.1032   0.6687   0.0705
  -2.500   0.2545   0.01850   0.00823  -0.1029   0.6612   0.0747
  -2.250   0.2809   0.01825   0.00790  -0.1025   0.6528   0.0794
  -2.000   0.3081   0.01800   0.00758  -0.1022   0.6461   0.0868
  -1.750   0.3343   0.01773   0.00735  -0.1019   0.6377   0.1033
  -1.500   0.3607   0.01720   0.00704  -0.1018   0.6306   0.1602
  -1.250   0.3848   0.01632   0.00704  -0.1017   0.6234   0.3845
  -1.000   0.4090   0.01621   0.00726  -0.1007   0.6158   0.5203
  -0.750   0.4342   0.01626   0.00736  -0.0997   0.6094   0.5862
  -0.500   0.4571   0.01633   0.00758  -0.0982   0.6013   0.6475
  -0.250   0.4804   0.01635   0.00765  -0.0967   0.5946   0.6943
   0.000   0.5048   0.01637   0.00770  -0.0956   0.5872   0.7245
   0.250   0.5300   0.01638   0.00769  -0.0947   0.5796   0.7483
   0.500   0.5562   0.01639   0.00763  -0.0941   0.5734   0.7711
   0.750   0.5811   0.01639   0.00768  -0.0933   0.5652   0.7925
   1.000   0.6074   0.01636   0.00761  -0.0927   0.5585   0.8173
   1.250   0.6340   0.01632   0.00764  -0.0922   0.5506   0.8528
   1.500   0.6748   0.01621   0.00756  -0.0946   0.5426   0.9871
   1.750   0.7025   0.01642   0.00765  -0.0948   0.5355   1.0000
   2.000   0.7298   0.01663   0.00776  -0.0949   0.5279   1.0000
   2.250   0.7576   0.01682   0.00780  -0.0949   0.5216   1.0000
   2.500   0.7837   0.01706   0.00801  -0.0947   0.5132   1.0000
   2.750   0.8109   0.01725   0.00807  -0.0945   0.5068   1.0000
   3.000   0.8366   0.01751   0.00830  -0.0942   0.4987   1.0000
   3.250   0.8630   0.01772   0.00842  -0.0940   0.4917   1.0000
   3.500   0.8887   0.01798   0.00863  -0.0936   0.4843   1.0000
   3.750   0.9144   0.01821   0.00881  -0.0932   0.4766   1.0000
   4.000   0.9398   0.01846   0.00900  -0.0928   0.4691   1.0000
   4.250   0.9647   0.01872   0.00923  -0.0923   0.4611   1.0000
   4.500   0.9903   0.01899   0.00943  -0.0919   0.4546   1.0000
   4.750   1.0146   0.01931   0.00977  -0.0914   0.4469   1.0000
   5.000   1.0401   0.01957   0.00994  -0.0910   0.4406   1.0000
   5.250   1.0635   0.01993   0.01035  -0.0903   0.4325   1.0000
   5.500   1.0880   0.02022   0.01059  -0.0898   0.4256   1.0000
   5.750   1.1113   0.02059   0.01097  -0.0891   0.4181   1.0000
   6.000   1.1347   0.02093   0.01132  -0.0885   0.4109   1.0000
   6.250   1.1585   0.02129   0.01167  -0.0879   0.4047   1.0000
   6.500   1.1811   0.02172   0.01216  -0.0871   0.3982   1.0000
   6.750   1.2048   0.02210   0.01254  -0.0865   0.3927   1.0000
   7.000   1.2272   0.02255   0.01304  -0.0858   0.3868   1.0000
   7.250   1.2489   0.02301   0.01357  -0.0850   0.3805   1.0000
   7.500   1.2721   0.02341   0.01396  -0.0843   0.3751   1.0000
   7.750   1.2924   0.02394   0.01460  -0.0833   0.3688   1.0000
   8.000   1.3129   0.02442   0.01515  -0.0824   0.3625   1.0000
   8.250   1.3350   0.02486   0.01558  -0.0816   0.3570   1.0000
   8.500   1.3521   0.02546   0.01634  -0.0802   0.3498   1.0000
   8.750   1.3714   0.02595   0.01687  -0.0790   0.3435   1.0000
   9.000   1.3892   0.02654   0.01753  -0.0777   0.3371   1.0000
   9.250   1.4049   0.02716   0.01827  -0.0762   0.3301   1.0000
   9.500   1.4233   0.02767   0.01876  -0.0749   0.3239   1.0000
   9.750   1.4334   0.02843   0.01970  -0.0727   0.3160   1.0000
  10.000   1.4458   0.02899   0.02025  -0.0706   0.3088   1.0000
  10.250   1.4513   0.02986   0.02128  -0.0678   0.3003   1.0000
  10.500   1.4603   0.03059   0.02200  -0.0656   0.2927   1.0000
  10.750   1.4641   0.03167   0.02324  -0.0630   0.2843   1.0000
  11.000   1.4713   0.03263   0.02421  -0.0609   0.2773   1.0000
  11.250   1.4750   0.03394   0.02568  -0.0589   0.2699   1.0000
  11.500   1.4802   0.03520   0.02700  -0.0570   0.2634   1.0000
  11.750   1.4832   0.03674   0.02866  -0.0554   0.2566   1.0000
  12.000   1.4851   0.03839   0.03039  -0.0538   0.2496   1.0000
  12.250   1.4855   0.04030   0.03240  -0.0524   0.2426   1.0000
  12.500   1.4853   0.04237   0.03455  -0.0513   0.2358   1.0000
  12.750   1.4856   0.04455   0.03682  -0.0504   0.2297   1.0000
  13.000   1.4845   0.04701   0.03941  -0.0497   0.2238   1.0000
  13.250   1.4850   0.04930   0.04173  -0.0490   0.2184   1.0000
  13.500   1.4798   0.05243   0.04503  -0.0488   0.2120   1.0000
  13.750   1.4772   0.05521   0.04785  -0.0485   0.2060   1.0000
  14.000   1.4709   0.05867   0.05144  -0.0485   0.2001   1.0000
  14.250   1.4658   0.06202   0.05487  -0.0487   0.1942   1.0000
  14.500   1.4618   0.06531   0.05822  -0.0488   0.1888   1.0000
  14.750   1.4529   0.06945   0.06250  -0.0495   0.1830   1.0000
  15.000   1.4510   0.07254   0.06559  -0.0497   0.1770   1.0000
  15.250   1.4389   0.07747   0.07071  -0.0509   0.1712   1.0000
  15.500   1.4313   0.08172   0.07503  -0.0519   0.1649   1.0000
  15.750   1.4233   0.08618   0.07957  -0.0530   0.1586   1.0000
  16.000   1.4094   0.09181   0.08536  -0.0549   0.1518   1.0000
  16.250   1.4011   0.09652   0.09011  -0.0563   0.1448   1.0000
  16.500   1.3836   0.10315   0.09694  -0.0589   0.1371   1.0000
  16.750   1.3700   0.10916   0.10307  -0.0613   0.1291   1.0000
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