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GOE 411 AIRFOIL (goe411-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 411 AIRFOIL (goe411-il)
Reynolds number: 100,000
Max Cl/Cd: 40.75 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe411-il-100000.txt
Download as CSV file: xf-goe411-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 411 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6285   0.10352   0.09861  -0.0379   1.0000   0.0841
 -12.000  -0.6646   0.09045   0.08557  -0.0452   1.0000   0.0747
 -11.750  -0.6939   0.08304   0.07818  -0.0498   1.0000   0.0750
 -11.500  -0.7234   0.07705   0.07212  -0.0527   1.0000   0.0753
 -11.250  -0.7552   0.07211   0.06707  -0.0537   1.0000   0.0753
 -11.000  -0.7864   0.06828   0.06310  -0.0525   1.0000   0.0750
 -10.750  -0.8217   0.06530   0.05994  -0.0488   1.0000   0.0745
 -10.500  -0.8556   0.06341   0.05785  -0.0428   1.0000   0.0740
 -10.250  -0.8575   0.05824   0.05248  -0.0401   1.0000   0.0651
 -10.000  -0.8915   0.05541   0.04918  -0.0330   1.0000   0.0621
  -9.750  -0.8960   0.05283   0.04623  -0.0284   1.0000   0.0577
  -9.500  -0.8975   0.04885   0.04201  -0.0249   1.0000   0.0548
  -9.250  -0.9061   0.04578   0.03840  -0.0195   1.0000   0.0515
  -9.000  -0.9110   0.04528   0.03726  -0.0132   1.0000   0.0488
  -8.750  -0.8999   0.04245   0.03415  -0.0106   1.0000   0.0482
  -8.500  -0.8891   0.03984   0.03125  -0.0078   1.0000   0.0481
  -8.250  -0.8737   0.03731   0.02843  -0.0056   1.0000   0.0480
  -8.000  -0.8500   0.03453   0.02547  -0.0048   1.0000   0.0474
  -7.750  -0.8218   0.03202   0.02282  -0.0044   1.0000   0.0467
  -7.500  -0.7951   0.03002   0.02075  -0.0038   1.0000   0.0464
  -7.250  -0.7742   0.02843   0.01914  -0.0023   1.0000   0.0465
  -7.000  -0.7606   0.02714   0.01783   0.0003   1.0000   0.0470
  -6.750  -0.7518   0.02603   0.01667   0.0038   1.0000   0.0477
  -6.500  -0.7448   0.02507   0.01564   0.0076   1.0000   0.0488
  -6.250  -0.7420   0.02388   0.01442   0.0118   1.0000   0.0521
  -6.000  -0.7336   0.02305   0.01347   0.0153   1.0000   0.0554
  -5.750  -0.7234   0.02230   0.01258   0.0186   1.0000   0.0584
  -5.500  -0.7137   0.02143   0.01165   0.0220   1.0000   0.0638
  -5.250  -0.7037   0.02053   0.01078   0.0253   1.0000   0.0776
  -5.000  -0.7041   0.01874   0.00997   0.0298   1.0000   0.2150
  -4.750  -0.6999   0.01764   0.00957   0.0338   1.0000   0.3264
  -4.500  -0.6928   0.01705   0.00943   0.0377   1.0000   0.4158
  -4.250  -0.6831   0.01674   0.00934   0.0412   1.0000   0.4779
  -4.000  -0.6710   0.01656   0.00921   0.0443   1.0000   0.5233
  -3.750  -0.6592   0.01640   0.00916   0.0475   1.0000   0.5679
  -3.500  -0.6475   0.01625   0.00917   0.0509   1.0000   0.6141
  -3.250  -0.6319   0.01613   0.00917   0.0535   1.0000   0.6500
  -3.000  -0.6187   0.01616   0.00940   0.0569   1.0000   0.6972
  -2.750  -0.6025   0.01626   0.00959   0.0596   1.0000   0.7361
  -2.500  -0.5823   0.01631   0.00965   0.0610   1.0000   0.7637
  -2.250  -0.5597   0.01642   0.00977   0.0619   1.0000   0.7920
  -2.000  -0.5324   0.01667   0.01002   0.0620   1.0000   0.8213
  -1.750  -0.4982   0.01711   0.01045   0.0606   1.0000   0.8499
  -1.500  -0.4378   0.01805   0.01128   0.0541   0.9947   0.8758
  -1.250  -0.3699   0.01919   0.01230   0.0466   0.9874   0.8999
  -1.000  -0.2903   0.02043   0.01338   0.0368   0.9825   0.9144
  -0.750  -0.2143   0.02115   0.01400   0.0271   0.9753   0.9223
  -0.500  -0.1395   0.02171   0.01447   0.0175   0.9690   0.9320
  -0.250  -0.0732   0.02197   0.01469   0.0094   0.9593   0.9430
   0.000  -0.0001   0.02207   0.01477   0.0000   0.9510   0.9509
   0.250   0.0732   0.02197   0.01469  -0.0094   0.9430   0.9593
   0.500   0.1397   0.02171   0.01447  -0.0175   0.9319   0.9690
   0.750   0.2145   0.02114   0.01400  -0.0271   0.9222   0.9752
   1.000   0.2906   0.02043   0.01338  -0.0368   0.9144   0.9826
   1.500   0.4380   0.01805   0.01127  -0.0542   0.8759   0.9947
   1.750   0.4983   0.01711   0.01042  -0.0606   0.8498   1.0000
   2.000   0.5325   0.01666   0.01002  -0.0620   0.8211   1.0000
   2.250   0.5598   0.01642   0.00977  -0.0620   0.7921   1.0000
   2.500   0.5824   0.01630   0.00965  -0.0610   0.7637   1.0000
   2.750   0.6025   0.01625   0.00961  -0.0596   0.7359   1.0000
   3.000   0.6189   0.01616   0.00940  -0.0569   0.6976   1.0000
   3.250   0.6317   0.01613   0.00916  -0.0534   0.6487   1.0000
   3.500   0.6479   0.01625   0.00917  -0.0509   0.6151   1.0000
   3.750   0.6587   0.01640   0.00915  -0.0474   0.5657   1.0000
   4.000   0.6709   0.01656   0.00921  -0.0443   0.5225   1.0000
   4.250   0.6825   0.01675   0.00932  -0.0411   0.4747   1.0000
   4.500   0.6929   0.01705   0.00943  -0.0377   0.4157   1.0000
   4.750   0.6993   0.01767   0.00957  -0.0337   0.3211   1.0000
   5.000   0.7037   0.01877   0.00997  -0.0297   0.2113   1.0000
   5.250   0.7042   0.02048   0.01075  -0.0254   0.0790   1.0000
   5.500   0.7135   0.02146   0.01168  -0.0219   0.0635   1.0000
   5.750   0.7233   0.02231   0.01259  -0.0186   0.0582   1.0000
   6.000   0.7334   0.02307   0.01349  -0.0153   0.0544   1.0000
   6.250   0.7419   0.02389   0.01444  -0.0118   0.0518   1.0000
   6.500   0.7448   0.02507   0.01564  -0.0076   0.0488   1.0000
   6.750   0.7518   0.02603   0.01668  -0.0038   0.0476   1.0000
   7.000   0.7606   0.02714   0.01783  -0.0003   0.0470   1.0000
   7.250   0.7743   0.02841   0.01912   0.0023   0.0466   1.0000
   7.500   0.7950   0.03001   0.02075   0.0038   0.0464   1.0000
   7.750   0.8221   0.03206   0.02287   0.0044   0.0467   1.0000
   8.000   0.8497   0.03448   0.02542   0.0048   0.0474   1.0000
   8.250   0.8724   0.03716   0.02829   0.0059   0.0478   1.0000
   8.500   0.8862   0.03940   0.03086   0.0084   0.0477   1.0000
   8.750   0.8989   0.04230   0.03402   0.0108   0.0481   1.0000
   9.000   0.9106   0.04555   0.03753   0.0132   0.0487   1.0000
   9.250   0.9074   0.04571   0.03830   0.0193   0.0513   1.0000
   9.500   0.8973   0.04891   0.04206   0.0250   0.0548   1.0000
   9.750   0.8965   0.05274   0.04614   0.0283   0.0577   1.0000
  10.000   0.8935   0.05537   0.04912   0.0327   0.0620   1.0000
  10.250   0.8557   0.05842   0.05268   0.0403   0.0654   1.0000
  10.500   0.8344   0.06140   0.05583   0.0453   0.0677   1.0000
  10.750   0.8194   0.06532   0.05997   0.0490   0.0746   1.0000
  11.000   0.7886   0.06816   0.06297   0.0524   0.0750   1.0000
  11.250   0.7550   0.07216   0.06712   0.0537   0.0753   1.0000
  11.500   0.7253   0.07693   0.07200   0.0527   0.0753   1.0000
  11.750   0.6962   0.08281   0.07794   0.0499   0.0750   1.0000
  12.000   0.6625   0.09093   0.08606   0.0447   0.0748   1.0000
  12.250   0.6079   0.10806   0.10310   0.0330   0.0826   1.0000
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