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GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 802 A AIRFOIL (goe802a-il)
Reynolds number: 100,000
Max Cl/Cd: 60.98 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe802a-il-100000-n5.txt
Download as CSV file: xf-goe802a-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 A 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2565   0.11292   0.10817  -0.0324   1.0000   0.0374
  -9.250  -0.2638   0.11169   0.10702  -0.0304   1.0000   0.0380
  -9.000  -0.2727   0.11063   0.10604  -0.0282   0.9999   0.0385
  -8.750  -0.2575   0.10744   0.10284  -0.0334   0.9939   0.0393
  -8.500  -0.2443   0.10469   0.10009  -0.0390   0.9859   0.0396
  -8.250  -0.2272   0.10035   0.09574  -0.0425   0.9812   0.0401
  -8.000  -0.2115   0.09660   0.09200  -0.0447   0.9751   0.0413
  -7.750  -0.1905   0.09289   0.08827  -0.0498   0.9687   0.0430
  -7.500  -0.1693   0.08933   0.08469  -0.0557   0.9614   0.0445
  -7.250  -0.1429   0.08586   0.08118  -0.0640   0.9534   0.0455
  -7.000  -0.1152   0.08216   0.07742  -0.0718   0.9467   0.0458
  -6.750  -0.1020   0.07846   0.07373  -0.0723   0.9391   0.0465
  -6.500  -0.0787   0.07492   0.07014  -0.0762   0.9335   0.0478
  -6.250  -0.0540   0.07175   0.06691  -0.0810   0.9268   0.0502
  -6.000  -0.0194   0.06917   0.06416  -0.0895   0.9171   0.0518
  -5.750   0.0003   0.06517   0.06017  -0.0911   0.9125   0.0524
  -5.500   0.0196   0.06228   0.05724  -0.0929   0.9044   0.0535
  -5.250   0.0448   0.05942   0.05428  -0.0961   0.8969   0.0551
  -5.000   0.0798   0.05651   0.05119  -0.1011   0.8918   0.0572
  -4.750   0.1114   0.05465   0.04908  -0.1048   0.8822   0.0578
  -4.500   0.1302   0.05112   0.04558  -0.1056   0.8758   0.0589
  -4.250   0.1580   0.04858   0.04292  -0.1078   0.8699   0.0615
  -4.000   0.1867   0.04680   0.04092  -0.1096   0.8604   0.0635
  -3.500   0.2423   0.04213   0.03594  -0.1127   0.8457   0.0647
  -3.250   0.2693   0.03995   0.03364  -0.1138   0.8378   0.0660
  -3.000   0.2991   0.03805   0.03154  -0.1150   0.8308   0.0676
  -2.750   0.3267   0.03664   0.02990  -0.1155   0.8209   0.0689
  -2.500   0.3604   0.03548   0.02838  -0.1165   0.8142   0.0696
  -2.250   0.3826   0.03330   0.02619  -0.1166   0.8027   0.0711
  -2.000   0.4132   0.03180   0.02445  -0.1173   0.7950   0.0731
  -1.750   0.4394   0.03074   0.02317  -0.1171   0.7826   0.0739
  -1.500   0.4691   0.02956   0.02174  -0.1174   0.7735   0.0742
  -1.250   0.4960   0.02854   0.02052  -0.1172   0.7614   0.0742
  -1.000   0.5240   0.02749   0.01924  -0.1173   0.7507   0.0742
  -0.750   0.5519   0.02638   0.01794  -0.1173   0.7396   0.0736
  -0.250   0.6089   0.02435   0.01536  -0.1170   0.7179   0.0587
   0.000   0.6349   0.02370   0.01460  -0.1167   0.7047   0.0610
   0.250   0.6625   0.02307   0.01377  -0.1165   0.6929   0.0608
   0.500   0.6901   0.02247   0.01295  -0.1162   0.6811   0.0593
   0.750   0.7167   0.02203   0.01233  -0.1159   0.6683   0.0585
   1.000   0.7438   0.02157   0.01170  -0.1156   0.6568   0.0583
   1.250   0.7703   0.02115   0.01115  -0.1153   0.6443   0.0586
   1.500   0.7964   0.02080   0.01071  -0.1150   0.6315   0.0593
   1.750   0.8230   0.02060   0.01038  -0.1147   0.6198   0.0624
   2.000   0.8487   0.02044   0.01016  -0.1143   0.6072   0.0661
   2.250   0.8746   0.02028   0.00993  -0.1139   0.5958   0.0681
   2.500   0.9006   0.02016   0.00970  -0.1136   0.5849   0.0703
   2.750   0.9258   0.02008   0.00960  -0.1131   0.5728   0.0737
   3.000   0.9515   0.02011   0.00953  -0.1127   0.5621   0.0814
   3.250   0.9768   0.02017   0.00948  -0.1123   0.5504   0.0922
   3.750   1.0275   0.01855   0.00807  -0.1122   0.5305   0.1560
   4.000   1.0493   0.01747   0.00831  -0.1112   0.5212   1.0000
   4.250   1.0738   0.01780   0.00856  -0.1107   0.5106   1.0000
   4.500   1.0984   0.01814   0.00882  -0.1103   0.5009   1.0000
   4.750   1.1226   0.01849   0.00914  -0.1099   0.4909   1.0000
   5.000   1.1465   0.01884   0.00944  -0.1094   0.4806   1.0000
   5.250   1.1698   0.01919   0.00971  -0.1087   0.4689   1.0000
   5.500   1.1922   0.01955   0.01008  -0.1080   0.4558   1.0000
   5.750   1.2146   0.01992   0.01038  -0.1072   0.4440   1.0000
   6.000   1.2369   0.02030   0.01075  -0.1065   0.4326   1.0000
   6.250   1.2594   0.02070   0.01115  -0.1058   0.4229   1.0000
   6.500   1.2815   0.02111   0.01158  -0.1050   0.4132   1.0000
   6.750   1.3034   0.02154   0.01203  -0.1043   0.4039   1.0000
   7.000   1.3248   0.02198   0.01248  -0.1035   0.3944   1.0000
   7.250   1.3459   0.02244   0.01297  -0.1026   0.3853   1.0000
   7.500   1.3666   0.02292   0.01351  -0.1017   0.3762   1.0000
   7.750   1.3870   0.02342   0.01403  -0.1007   0.3677   1.0000
   8.000   1.4060   0.02393   0.01460  -0.0996   0.3574   1.0000
   8.250   1.4240   0.02447   0.01518  -0.0983   0.3466   1.0000
   8.500   1.4405   0.02504   0.01575  -0.0967   0.3352   1.0000
   8.750   1.4562   0.02565   0.01647  -0.0952   0.3230   1.0000
   9.000   1.4709   0.02630   0.01712  -0.0934   0.3121   1.0000
   9.250   1.4843   0.02698   0.01788  -0.0915   0.3000   1.0000
   9.500   1.4954   0.02771   0.01868  -0.0893   0.2884   1.0000
   9.750   1.5040   0.02854   0.01950  -0.0867   0.2765   1.0000
  10.000   1.5126   0.02944   0.02052  -0.0843   0.2629   1.0000
  10.250   1.5206   0.03044   0.02159  -0.0821   0.2500   1.0000
  10.500   1.5274   0.03158   0.02275  -0.0798   0.2383   1.0000
  10.750   1.5329   0.03285   0.02405  -0.0776   0.2258   1.0000
  11.000   1.5379   0.03425   0.02549  -0.0755   0.2133   1.0000
  11.250   1.5407   0.03587   0.02711  -0.0733   0.2019   1.0000
  11.500   1.5414   0.03772   0.02896  -0.0713   0.1910   1.0000
  11.750   1.5434   0.03960   0.03089  -0.0695   0.1808   1.0000
  12.250   1.5443   0.04386   0.03525  -0.0663   0.1645   1.0000
  12.500   1.5424   0.04633   0.03774  -0.0648   0.1576   1.0000
  12.750   1.5428   0.04870   0.04022  -0.0637   0.1509   1.0000
  13.000   1.5418   0.05130   0.04292  -0.0627   0.1443   1.0000
  13.250   1.5369   0.05433   0.04600  -0.0618   0.1388   1.0000
  13.500   1.5372   0.05700   0.04884  -0.0612   0.1329   1.0000
  13.750   1.5346   0.06005   0.05203  -0.0607   0.1275   1.0000
  14.000   1.5293   0.06350   0.05554  -0.0604   0.1231   1.0000
  14.250   1.5268   0.06675   0.05893  -0.0602   0.1190   1.0000
  14.500   1.5250   0.07005   0.06241  -0.0603   0.1147   1.0000
  14.750   1.5206   0.07375   0.06625  -0.0605   0.1107   1.0000
  15.000   1.5139   0.07783   0.07043  -0.0610   0.1071   1.0000
  15.250   1.5088   0.08181   0.07453  -0.0615   0.1035   1.0000
  15.500   1.5036   0.08597   0.07890  -0.0623   0.0989   1.0000
  15.750   1.4947   0.09074   0.08379  -0.0634   0.0943   1.0000
  16.000   1.4843   0.09581   0.08892  -0.0648   0.0905   1.0000
  16.250   1.4782   0.10034   0.09365  -0.0660   0.0862   1.0000
  16.500   1.4698   0.10530   0.09875  -0.0675   0.0823   1.0000
  16.750   1.4598   0.11059   0.10414  -0.0693   0.0790   1.0000
  17.000   1.4515   0.11565   0.10933  -0.0710   0.0759   1.0000
  17.250   1.4439   0.12072   0.11455  -0.0729   0.0725   1.0000
  17.500   1.4347   0.12615   0.12009  -0.0752   0.0691   1.0000
  17.750   1.4243   0.13189   0.12588  -0.0778   0.0659   1.0000
  18.000   1.4156   0.13743   0.13156  -0.0803   0.0619   1.0000
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