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GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 621 AIRFOIL (goe621-il)
Reynolds number: 500,000
Max Cl/Cd: 105.51 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe621-il-500000.txt
Download as CSV file: xf-goe621-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 621 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.5154   0.03832   0.03488  -0.1342   0.9719   0.0376
 -11.500  -0.5184   0.03413   0.03032  -0.1380   0.9639   0.0379
 -11.250  -0.5117   0.03118   0.02705  -0.1392   0.9566   0.0381
 -11.000  -0.5059   0.02928   0.02489  -0.1380   0.9479   0.0383
 -10.750  -0.4944   0.02771   0.02305  -0.1370   0.9406   0.0385
 -10.500  -0.4853   0.02666   0.02178  -0.1347   0.9318   0.0387
 -10.250  -0.4738   0.02471   0.01961  -0.1332   0.9249   0.0390
 -10.000  -0.4600   0.02324   0.01803  -0.1315   0.9172   0.0394
  -9.750  -0.4416   0.02216   0.01688  -0.1303   0.9103   0.0397
  -9.500  -0.4220   0.02131   0.01595  -0.1292   0.9037   0.0402
  -9.250  -0.4025   0.02058   0.01514  -0.1279   0.8954   0.0406
  -9.000  -0.3802   0.01990   0.01436  -0.1270   0.8891   0.0412
  -8.750  -0.3601   0.01921   0.01358  -0.1257   0.8799   0.0418
  -8.500  -0.3372   0.01845   0.01269  -0.1249   0.8729   0.0423
  -8.250  -0.3158   0.01779   0.01193  -0.1238   0.8633   0.0428
  -8.000  -0.2920   0.01715   0.01115  -0.1230   0.8557   0.0433
  -7.750  -0.2691   0.01662   0.01052  -0.1220   0.8454   0.0437
  -7.500  -0.2443   0.01618   0.00993  -0.1213   0.8371   0.0441
  -7.250  -0.2232   0.01518   0.00890  -0.1203   0.8267   0.0449
  -7.000  -0.1992   0.01464   0.00831  -0.1195   0.8183   0.0457
  -6.750  -0.1750   0.01423   0.00786  -0.1188   0.8089   0.0465
  -6.500  -0.1499   0.01388   0.00744  -0.1181   0.8008   0.0476
  -6.250  -0.1251   0.01356   0.00704  -0.1175   0.7920   0.0486
  -6.000  -0.0996   0.01326   0.00664  -0.1169   0.7844   0.0496
  -5.750  -0.0752   0.01285   0.00617  -0.1161   0.7764   0.0505
  -5.500  -0.0509   0.01241   0.00569  -0.1154   0.7698   0.0520
  -5.250  -0.0256   0.01213   0.00539  -0.1148   0.7631   0.0535
  -5.000   0.0001   0.01189   0.00510  -0.1143   0.7565   0.0553
  -4.750   0.0264   0.01168   0.00479  -0.1138   0.7506   0.0572
  -4.500   0.0512   0.01134   0.00448  -0.1132   0.7443   0.0603
  -4.250   0.0775   0.01116   0.00425  -0.1127   0.7379   0.0638
  -4.000   0.1033   0.01092   0.00398  -0.1122   0.7316   0.0693
  -3.750   0.1290   0.01068   0.00379  -0.1116   0.7250   0.0779
  -3.500   0.1553   0.01049   0.00363  -0.1112   0.7192   0.0944
  -3.250   0.1821   0.01035   0.00352  -0.1108   0.7139   0.1129
  -3.000   0.2083   0.01020   0.00342  -0.1104   0.7080   0.1275
  -2.750   0.2349   0.01007   0.00331  -0.1100   0.7024   0.1414
  -2.500   0.2622   0.01000   0.00322  -0.1098   0.6973   0.1565
  -2.250   0.2882   0.00985   0.00316  -0.1093   0.6921   0.1755
  -2.000   0.3143   0.00970   0.00309  -0.1088   0.6863   0.2020
  -1.750   0.3410   0.00961   0.00304  -0.1085   0.6806   0.2342
  -1.500   0.3672   0.00951   0.00304  -0.1080   0.6750   0.2645
  -1.250   0.3935   0.00943   0.00303  -0.1076   0.6696   0.2917
  -1.000   0.4205   0.00939   0.00303  -0.1073   0.6648   0.3182
  -0.750   0.4475   0.00939   0.00304  -0.1069   0.6599   0.3417
  -0.500   0.4737   0.00933   0.00306  -0.1065   0.6545   0.3631
  -0.250   0.5003   0.00930   0.00307  -0.1061   0.6495   0.3823
   0.000   0.5275   0.00932   0.00307  -0.1058   0.6447   0.3994
   0.250   0.5537   0.00930   0.00309  -0.1053   0.6394   0.4162
   0.500   0.5797   0.00926   0.00310  -0.1048   0.6335   0.4336
   0.750   0.6060   0.00926   0.00310  -0.1043   0.6277   0.4522
   1.000   0.6318   0.00923   0.00313  -0.1037   0.6221   0.4726
   1.250   0.6570   0.00917   0.00316  -0.1031   0.6159   0.4969
   1.500   0.6819   0.00912   0.00317  -0.1024   0.6097   0.5319
   1.750   0.7046   0.00894   0.00322  -0.1012   0.6027   0.5917
   2.000   0.7882   0.00827   0.00345  -0.1128   0.5926   0.9761
   2.250   0.8447   0.00837   0.00352  -0.1189   0.5821   1.0000
   2.500   0.8666   0.00848   0.00354  -0.1176   0.5729   1.0000
   2.750   0.8885   0.00856   0.00360  -0.1163   0.5619   1.0000
   3.000   0.9097   0.00868   0.00366  -0.1148   0.5503   1.0000
   3.250   0.9296   0.00882   0.00372  -0.1131   0.5357   1.0000
   3.500   0.9485   0.00899   0.00381  -0.1112   0.5179   1.0000
   3.750   0.9657   0.00920   0.00393  -0.1090   0.4958   1.0000
   4.000   0.9789   0.00953   0.00409  -0.1061   0.4665   1.0000
   4.250   0.9890   0.00996   0.00432  -0.1026   0.4332   1.0000
   4.750   1.0096   0.01085   0.00488  -0.0958   0.3821   1.0000
   5.000   1.0193   0.01122   0.00514  -0.0923   0.3667   1.0000
   5.250   1.0310   0.01155   0.00539  -0.0892   0.3552   1.0000
   5.500   1.0452   0.01185   0.00565  -0.0866   0.3458   1.0000
   5.750   1.0585   0.01222   0.00595  -0.0840   0.3371   1.0000
   6.000   1.0751   0.01251   0.00622  -0.0819   0.3299   1.0000
   6.250   1.0908   0.01286   0.00653  -0.0798   0.3226   1.0000
   6.500   1.1062   0.01324   0.00687  -0.0777   0.3165   1.0000
   6.750   1.1248   0.01352   0.00716  -0.0761   0.3109   1.0000
   7.000   1.1413   0.01390   0.00750  -0.0743   0.3053   1.0000
   7.250   1.1566   0.01434   0.00790  -0.0723   0.2998   1.0000
   7.500   1.1762   0.01462   0.00822  -0.0710   0.2951   1.0000
   7.750   1.1935   0.01500   0.00859  -0.0694   0.2899   1.0000
   8.000   1.2085   0.01550   0.00905  -0.0675   0.2846   1.0000
   8.250   1.2270   0.01585   0.00944  -0.0662   0.2803   1.0000
   8.500   1.2453   0.01623   0.00983  -0.0649   0.2752   1.0000
   8.750   1.2606   0.01674   0.01032  -0.0632   0.2698   1.0000
   9.000   1.2768   0.01724   0.01082  -0.0617   0.2648   1.0000
   9.250   1.2951   0.01765   0.01127  -0.0605   0.2594   1.0000
   9.500   1.3104   0.01821   0.01182  -0.0589   0.2541   1.0000
   9.750   1.3251   0.01883   0.01243  -0.0574   0.2489   1.0000
  10.000   1.3427   0.01930   0.01295  -0.0562   0.2436   1.0000
  10.250   1.3572   0.01996   0.01360  -0.0547   0.2379   1.0000
  10.500   1.3710   0.02068   0.01432  -0.0533   0.2325   1.0000
  10.750   1.3874   0.02127   0.01495  -0.0521   0.2265   1.0000
  11.000   1.3989   0.02216   0.01581  -0.0505   0.2201   1.0000
  11.250   1.4139   0.02287   0.01656  -0.0493   0.2136   1.0000
  11.500   1.4255   0.02381   0.01748  -0.0479   0.2064   1.0000
  11.750   1.4378   0.02473   0.01841  -0.0466   0.2000   1.0000
  12.000   1.4492   0.02575   0.01943  -0.0453   0.1927   1.0000
  12.250   1.4591   0.02688   0.02056  -0.0439   0.1866   1.0000
  12.500   1.4706   0.02795   0.02164  -0.0427   0.1800   1.0000
  12.750   1.4775   0.02937   0.02302  -0.0413   0.1743   1.0000
  13.000   1.4901   0.03041   0.02412  -0.0403   0.1694   1.0000
  13.250   1.4992   0.03172   0.02545  -0.0392   0.1647   1.0000
  13.500   1.5047   0.03336   0.02706  -0.0379   0.1599   1.0000
  13.750   1.5170   0.03448   0.02826  -0.0370   0.1567   1.0000
  14.000   1.5263   0.03585   0.02967  -0.0361   0.1527   1.0000
  14.250   1.5324   0.03753   0.03135  -0.0351   0.1491   1.0000
  14.500   1.5389   0.03919   0.03303  -0.0341   0.1458   1.0000
  14.750   1.5499   0.04050   0.03442  -0.0334   0.1429   1.0000
  15.000   1.5580   0.04207   0.03603  -0.0326   0.1398   1.0000
  15.250   1.5636   0.04388   0.03788  -0.0318   0.1370   1.0000
  15.500   1.5658   0.04603   0.04003  -0.0310   0.1338   1.0000
  15.750   1.5755   0.04753   0.04162  -0.0304   0.1317   1.0000
  16.000   1.5837   0.04919   0.04336  -0.0299   0.1294   1.0000
  16.250   1.5897   0.05108   0.04530  -0.0294   0.1266   1.0000
  16.500   1.5929   0.05327   0.04753  -0.0289   0.1242   1.0000
  16.750   1.5923   0.05586   0.05013  -0.0283   0.1210   1.0000
  17.000   1.6009   0.05760   0.05198  -0.0281   0.1187   1.0000
  17.250   1.6065   0.05964   0.05410  -0.0278   0.1161   1.0000
  17.500   1.6077   0.06220   0.05671  -0.0276   0.1130   1.0000
  17.750   1.6048   0.06523   0.05976  -0.0274   0.1100   1.0000
  18.000   1.6095   0.06747   0.06210  -0.0274   0.1069   1.0000
  18.250   1.6111   0.07011   0.06482  -0.0274   0.1035   1.0000
  18.500   1.6054   0.07366   0.06840  -0.0276   0.0995   1.0000
  18.750   1.6049   0.07662   0.07143  -0.0278   0.0952   1.0000
  19.000   1.6008   0.08006   0.07493  -0.0281   0.0905   1.0000
  19.250   1.5930   0.08407   0.07899  -0.0287   0.0848   1.0000
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