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GOE 615 AIRFOIL (goe615-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 615 AIRFOIL (goe615-il)
Reynolds number: 100,000
Max Cl/Cd: 52.96 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe615-il-100000-n5.txt
Download as CSV file: xf-goe615-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 615 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1398   0.09335   0.08844  -0.0696   0.9491   0.0843
  -8.500  -0.1507   0.08880   0.08392  -0.0809   0.9356   0.0868
  -8.000  -0.1444   0.07147   0.06645  -0.0932   0.9174   0.0571
  -7.750  -0.1248   0.06774   0.06267  -0.0968   0.9115   0.0566
  -7.500  -0.1169   0.06371   0.05859  -0.1001   0.9003   0.0561
  -7.250  -0.1049   0.05785   0.05258  -0.1064   0.8922   0.0556
  -7.000  -0.1047   0.05139   0.04586  -0.1109   0.8798   0.0558
  -6.750  -0.1008   0.04608   0.04019  -0.1133   0.8690   0.0559
  -6.500  -0.0884   0.04158   0.03526  -0.1150   0.8607   0.0558
  -6.250  -0.0777   0.03829   0.03158  -0.1147   0.8506   0.0558
  -6.000  -0.0586   0.03520   0.02800  -0.1152   0.8433   0.0560
  -5.750  -0.0422   0.03289   0.02523  -0.1143   0.8342   0.0565
  -5.500  -0.0198   0.03086   0.02277  -0.1141   0.8266   0.0576
  -5.250   0.0036   0.02956   0.02135  -0.1138   0.8186   0.0587
  -5.000   0.0279   0.02827   0.01986  -0.1134   0.8101   0.0595
  -4.750   0.0535   0.02695   0.01827  -0.1130   0.8024   0.0602
  -4.500   0.0777   0.02582   0.01691  -0.1124   0.7933   0.0610
  -4.250   0.1053   0.02473   0.01558  -0.1122   0.7859   0.0619
  -4.000   0.1295   0.02390   0.01456  -0.1114   0.7767   0.0634
  -3.750   0.1589   0.02310   0.01346  -0.1114   0.7698   0.0655
  -3.500   0.1823   0.02236   0.01268  -0.1104   0.7601   0.0669
  -3.250   0.2120   0.02160   0.01186  -0.1106   0.7533   0.0684
  -3.000   0.2349   0.02111   0.01133  -0.1095   0.7430   0.0698
  -2.750   0.2642   0.02051   0.01064  -0.1094   0.7360   0.0719
  -2.500   0.2872   0.02018   0.01024  -0.1083   0.7260   0.0747
  -2.250   0.3158   0.01968   0.00971  -0.1083   0.7195   0.0780
  -2.000   0.3384   0.01941   0.00946  -0.1072   0.7102   0.0812
  -1.750   0.3662   0.01907   0.00902  -0.1069   0.7034   0.0852
  -1.500   0.3898   0.01883   0.00878  -0.1059   0.6947   0.0902
  -1.250   0.4167   0.01858   0.00847  -0.1055   0.6875   0.0990
  -1.000   0.4416   0.01831   0.00823  -0.1048   0.6797   0.1114
  -0.750   0.4667   0.01788   0.00804  -0.1042   0.6711   0.1522
  -0.500   0.4916   0.01750   0.00798  -0.1036   0.6617   0.2620
  -0.250   0.5185   0.01716   0.00785  -0.1032   0.6523   0.3546
   0.000   0.5401   0.01676   0.00789  -0.1020   0.6419   0.4890
   0.250   0.6211   0.01566   0.00778  -0.1116   0.6322   1.0000
   0.500   0.6429   0.01584   0.00781  -0.1104   0.6238   1.0000
   1.000   0.6900   0.01616   0.00782  -0.1084   0.6084   1.0000
   1.250   0.7151   0.01630   0.00779  -0.1077   0.6014   1.0000
   1.500   0.7372   0.01651   0.00790  -0.1065   0.5932   1.0000
   1.750   0.7615   0.01668   0.00793  -0.1056   0.5858   1.0000
   2.000   0.7847   0.01688   0.00804  -0.1047   0.5782   1.0000
   2.250   0.8078   0.01708   0.00814  -0.1036   0.5701   1.0000
   2.500   0.8318   0.01728   0.00823  -0.1028   0.5626   1.0000
   2.750   0.8538   0.01751   0.00841  -0.1016   0.5541   1.0000
   3.000   0.8782   0.01772   0.00850  -0.1008   0.5464   1.0000
   3.250   0.8991   0.01797   0.00873  -0.0995   0.5373   1.0000
   3.500   0.9234   0.01819   0.00884  -0.0987   0.5294   1.0000
   3.750   0.9433   0.01846   0.00910  -0.0972   0.5197   1.0000
   4.000   0.9663   0.01870   0.00926  -0.0962   0.5110   1.0000
   4.250   0.9857   0.01898   0.00953  -0.0946   0.5009   1.0000
   4.500   1.0066   0.01924   0.00975  -0.0933   0.4911   1.0000
   4.750   1.0262   0.01951   0.01000  -0.0918   0.4806   1.0000
   5.000   1.0443   0.01981   0.01032  -0.0900   0.4693   1.0000
   5.250   1.0634   0.02009   0.01055  -0.0884   0.4586   1.0000
   5.500   1.0803   0.02040   0.01085  -0.0865   0.4463   1.0000
   5.750   1.0961   0.02073   0.01120  -0.0844   0.4333   1.0000
   6.000   1.1112   0.02107   0.01151  -0.0822   0.4198   1.0000
   6.250   1.1255   0.02143   0.01183  -0.0799   0.4063   1.0000
   6.500   1.1379   0.02181   0.01215  -0.0772   0.3930   1.0000
   7.000   1.1608   0.02277   0.01295  -0.0719   0.3672   1.0000
   7.250   1.1728   0.02333   0.01345  -0.0695   0.3558   1.0000
   7.500   1.1849   0.02395   0.01398  -0.0672   0.3456   1.0000
   7.750   1.1977   0.02459   0.01460  -0.0651   0.3363   1.0000
   8.000   1.2105   0.02527   0.01523  -0.0631   0.3278   1.0000
   8.250   1.2222   0.02600   0.01593  -0.0611   0.3188   1.0000
   8.500   1.2345   0.02675   0.01668  -0.0591   0.3107   1.0000
   8.750   1.2458   0.02755   0.01748  -0.0572   0.3026   1.0000
   9.000   1.2585   0.02835   0.01825  -0.0555   0.2960   1.0000
   9.250   1.2712   0.02916   0.01914  -0.0539   0.2897   1.0000
   9.500   1.2838   0.03000   0.01999  -0.0523   0.2840   1.0000
   9.750   1.2966   0.03086   0.02088  -0.0508   0.2786   1.0000
  10.000   1.3079   0.03180   0.02192  -0.0493   0.2727   1.0000
  10.250   1.3193   0.03274   0.02288  -0.0478   0.2675   1.0000
  10.500   1.3305   0.03374   0.02393  -0.0463   0.2622   1.0000
  10.750   1.3408   0.03481   0.02513  -0.0449   0.2570   1.0000
  11.000   1.3499   0.03594   0.02631  -0.0435   0.2518   1.0000
  11.250   1.3590   0.03711   0.02750  -0.0421   0.2466   1.0000
  11.500   1.3654   0.03849   0.02903  -0.0407   0.2407   1.0000
  11.750   1.3728   0.03984   0.03046  -0.0394   0.2357   1.0000
  12.000   1.3801   0.04122   0.03187  -0.0382   0.2310   1.0000
  12.250   1.3856   0.04284   0.03366  -0.0370   0.2257   1.0000
  12.500   1.3909   0.04447   0.03538  -0.0359   0.2209   1.0000
  12.750   1.3961   0.04610   0.03702  -0.0349   0.2164   1.0000
  13.000   1.3975   0.04823   0.03936  -0.0340   0.2102   1.0000
  13.250   1.3985   0.05039   0.04161  -0.0332   0.2045   1.0000
  13.500   1.3995   0.05262   0.04393  -0.0325   0.1991   1.0000
  13.750   1.4002   0.05507   0.04653  -0.0319   0.1938   1.0000
  14.000   1.3999   0.05762   0.04917  -0.0315   0.1886   1.0000
  14.250   1.3991   0.06036   0.05203  -0.0312   0.1835   1.0000
  14.500   1.3963   0.06345   0.05529  -0.0312   0.1778   1.0000
  14.750   1.3926   0.06662   0.05851  -0.0312   0.1724   1.0000
  15.000   1.3867   0.07038   0.06246  -0.0316   0.1660   1.0000
  15.250   1.3796   0.07426   0.06642  -0.0320   0.1598   1.0000
  15.500   1.3711   0.07853   0.07084  -0.0327   0.1534   1.0000
  15.750   1.3603   0.08319   0.07558  -0.0337   0.1466   1.0000
  16.000   1.3479   0.08827   0.08078  -0.0349   0.1396   1.0000
  16.250   1.3338   0.09367   0.08623  -0.0364   0.1327   1.0000
  16.500   1.3194   0.09933   0.09201  -0.0381   0.1257   1.0000
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