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GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 614 AIRFOIL (goe614-il)
Reynolds number: 100,000
Max Cl/Cd: 43.45 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe614-il-100000-n5.txt
Download as CSV file: xf-goe614-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 614 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2370   0.07575   0.07019  -0.1089   0.9411   0.0470
 -11.000  -0.3048   0.06081   0.05492  -0.1214   0.9280   0.0464
 -10.750  -0.3349   0.05290   0.04670  -0.1296   0.9153   0.0461
 -10.500  -0.3523   0.04769   0.04118  -0.1350   0.9041   0.0460
 -10.250  -0.3599   0.04465   0.03786  -0.1354   0.8929   0.0460
 -10.000  -0.3612   0.04229   0.03525  -0.1347   0.8820   0.0461
  -9.750  -0.3474   0.03983   0.03251  -0.1358   0.8753   0.0463
  -9.500  -0.3383   0.03808   0.03052  -0.1349   0.8660   0.0466
  -9.250  -0.3200   0.03630   0.02848  -0.1352   0.8588   0.0469
  -9.000  -0.2899   0.03462   0.02673  -0.1369   0.8547   0.0476
  -8.750  -0.2812   0.03369   0.02575  -0.1345   0.8434   0.0481
  -8.500  -0.2525   0.03231   0.02427  -0.1356   0.8382   0.0489
  -8.250  -0.2380   0.03137   0.02324  -0.1341   0.8286   0.0496
  -8.000  -0.2125   0.03022   0.02195  -0.1343   0.8216   0.0504
  -7.750  -0.1882   0.02920   0.02080  -0.1342   0.8145   0.0510
  -7.500  -0.1695   0.02839   0.01989  -0.1330   0.8052   0.0515
  -7.250  -0.1374   0.02735   0.01868  -0.1342   0.7996   0.0523
  -6.750  -0.0956   0.02587   0.01703  -0.1324   0.7819   0.0538
  -6.500  -0.0795   0.02531   0.01641  -0.1306   0.7716   0.0546
  -6.250  -0.0520   0.02456   0.01553  -0.1308   0.7641   0.0560
  -6.000  -0.0324   0.02404   0.01491  -0.1295   0.7544   0.0574
  -5.750  -0.0064   0.02341   0.01418  -0.1293   0.7462   0.0593
  -5.500   0.0152   0.02286   0.01358  -0.1284   0.7370   0.0626
  -5.250   0.0398   0.02232   0.01299  -0.1279   0.7282   0.0672
  -5.000   0.0635   0.02182   0.01252  -0.1273   0.7195   0.0764
  -4.750   0.0874   0.02140   0.01205  -0.1265   0.7104   0.0946
  -4.500   0.1135   0.02102   0.01158  -0.1262   0.7021   0.1127
  -4.250   0.1359   0.02065   0.01126  -0.1253   0.6927   0.1321
  -4.000   0.1628   0.02037   0.01100  -0.1251   0.6846   0.1532
  -3.750   0.1858   0.02026   0.01087  -0.1241   0.6751   0.1715
  -3.500   0.2155   0.02013   0.01062  -0.1244   0.6680   0.1902
  -3.250   0.2368   0.02011   0.01054  -0.1231   0.6585   0.2050
  -3.000   0.2669   0.02001   0.01029  -0.1234   0.6513   0.2223
  -2.750   0.2871   0.01999   0.01029  -0.1219   0.6421   0.2344
  -2.500   0.3144   0.01991   0.01011  -0.1217   0.6348   0.2483
  -2.250   0.3386   0.01993   0.01002  -0.1210   0.6271   0.2624
  -2.000   0.3622   0.01992   0.01002  -0.1202   0.6196   0.2785
  -1.750   0.3914   0.01987   0.00990  -0.1203   0.6135   0.2965
  -1.500   0.4110   0.01994   0.00999  -0.1188   0.6054   0.3112
  -1.250   0.4371   0.01993   0.00990  -0.1184   0.5988   0.3254
  -1.000   0.4628   0.01994   0.00985  -0.1180   0.5926   0.3385
  -0.750   0.4845   0.02000   0.00994  -0.1168   0.5856   0.3518
  -0.500   0.5111   0.02002   0.00991  -0.1165   0.5800   0.3678
  -0.250   0.5371   0.02007   0.00991  -0.1162   0.5745   0.3841
   0.250   0.5835   0.02022   0.01008  -0.1144   0.5623   0.4228
   0.500   0.6115   0.02026   0.01010  -0.1144   0.5575   0.4469
   0.750   0.6309   0.02041   0.01034  -0.1129   0.5515   0.4698
   1.000   0.6552   0.02051   0.01047  -0.1123   0.5463   0.4951
   1.250   0.6836   0.02058   0.01050  -0.1124   0.5418   0.5234
   1.500   0.7066   0.02070   0.01069  -0.1115   0.5368   0.5529
   1.750   0.7265   0.02084   0.01093  -0.1101   0.5313   0.5867
   2.000   0.7505   0.02088   0.01108  -0.1094   0.5266   0.6302
   2.250   0.7787   0.02081   0.01117  -0.1092   0.5227   0.6988
   2.500   0.8446   0.02083   0.01164  -0.1169   0.5166   1.0000
   2.750   0.8636   0.02115   0.01187  -0.1155   0.5115   1.0000
   3.000   0.8876   0.02141   0.01199  -0.1149   0.5071   1.0000
   3.250   0.9165   0.02164   0.01204  -0.1152   0.5032   1.0000
   3.500   0.9261   0.02206   0.01248  -0.1121   0.4974   1.0000
   3.750   0.9431   0.02234   0.01269  -0.1102   0.4913   1.0000
   4.000   0.9688   0.02249   0.01267  -0.1099   0.4858   1.0000
   4.250   0.9756   0.02289   0.01307  -0.1063   0.4794   1.0000
   4.500   0.9888   0.02320   0.01334  -0.1038   0.4733   1.0000
   4.750   1.0117   0.02340   0.01341  -0.1030   0.4682   1.0000
   5.000   1.0236   0.02382   0.01382  -0.1004   0.4630   1.0000
   5.250   1.0340   0.02427   0.01429  -0.0976   0.4574   1.0000
   5.500   1.0524   0.02459   0.01455  -0.0962   0.4526   1.0000
   5.750   1.0785   0.02482   0.01465  -0.0960   0.4487   1.0000
   6.000   1.0830   0.02548   0.01540  -0.0925   0.4435   1.0000
   6.250   1.0949   0.02602   0.01596  -0.0903   0.4387   1.0000
   6.500   1.1129   0.02640   0.01630  -0.0889   0.4343   1.0000
   6.750   1.1367   0.02665   0.01644  -0.0884   0.4302   1.0000
   7.000   1.1375   0.02753   0.01745  -0.0848   0.4247   1.0000
   7.250   1.1475   0.02816   0.01810  -0.0825   0.4193   1.0000
   7.500   1.1659   0.02854   0.01842  -0.0813   0.4149   1.0000
   7.750   1.1780   0.02917   0.01906  -0.0794   0.4102   1.0000
   8.000   1.1803   0.03020   0.02019  -0.0764   0.4047   1.0000
   8.250   1.1918   0.03089   0.02089  -0.0746   0.3998   1.0000
   8.500   1.2127   0.03121   0.02115  -0.0739   0.3958   1.0000
   8.750   1.2118   0.03255   0.02259  -0.0709   0.3905   1.0000
   9.000   1.2153   0.03375   0.02388  -0.0686   0.3853   1.0000
   9.250   1.2283   0.03446   0.02458  -0.0672   0.3807   1.0000
   9.500   1.2429   0.03516   0.02527  -0.0660   0.3766   1.0000
   9.750   1.2346   0.03723   0.02749  -0.0630   0.3708   1.0000
  10.000   1.2401   0.03853   0.02884  -0.0613   0.3659   1.0000
  10.250   1.2577   0.03906   0.02935  -0.0605   0.3621   1.0000
  10.500   1.2489   0.04148   0.03189  -0.0581   0.3564   1.0000
  10.750   1.2450   0.04369   0.03420  -0.0562   0.3510   1.0000
  11.000   1.2574   0.04465   0.03516  -0.0553   0.3469   1.0000
  11.250   1.2596   0.04651   0.03707  -0.0539   0.3422   1.0000
  11.500   1.2396   0.05043   0.04116  -0.0519   0.3353   1.0000
  11.750   1.2503   0.05164   0.04238  -0.0511   0.3310   1.0000
  12.000   1.2520   0.05378   0.04457  -0.0502   0.3264   1.0000
  12.250   1.2224   0.05935   0.05031  -0.0489   0.3189   1.0000
  12.500   1.2360   0.06036   0.05133  -0.0484   0.3151   1.0000
  12.750   1.2603   0.06023   0.05117  -0.0479   0.3129   1.0000
  13.000   1.1942   0.07071   0.06191  -0.0474   0.3025   1.0000
  13.250   1.2097   0.07159   0.06281  -0.0470   0.2997   1.0000
  13.500   1.2328   0.07151   0.06274  -0.0465   0.2978   1.0000
  14.000   1.1746   0.08507   0.07657  -0.0471   0.2840   1.0000
  14.250   1.1976   0.08491   0.07642  -0.0467   0.2825   1.0000
  14.750   1.1410   0.09932   0.09106  -0.0485   0.2679   1.0000
  15.000   1.1667   0.09861   0.09037  -0.0480   0.2666   1.0000
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