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GOE 550 AIRFOIL (goe550-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 550 AIRFOIL (goe550-il)
Reynolds number: 500,000
Max Cl/Cd: 106.3 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe550-il-500000.txt
Download as CSV file: xf-goe550-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 550 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
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.7238   0.10218   0.09919  -0.0550   1.0000   0.0286
 -16.000  -0.7642   0.09128   0.08812  -0.0614   1.0000   0.0288
 -15.750  -0.7888   0.08372   0.08042  -0.0658   1.0000   0.0289
 -15.500  -0.8035   0.07858   0.07525  -0.0684   1.0000   0.0294
 -15.250  -0.8100   0.07466   0.07131  -0.0703   1.0000   0.0299
 -15.000  -0.8186   0.07052   0.06716  -0.0724   1.0000   0.0304
 -14.750  -0.8325   0.06593   0.06252  -0.0748   1.0000   0.0307
 -14.500  -0.8483   0.06123   0.05777  -0.0772   1.0000   0.0310
 -14.250  -0.8654   0.05651   0.05300  -0.0796   1.0000   0.0314
 -14.000  -0.8868   0.05163   0.04805  -0.0817   1.0000   0.0315
 -13.750  -0.9105   0.04669   0.04305  -0.0837   1.0000   0.0317
 -13.500  -0.9434   0.04159   0.03789  -0.0847   1.0000   0.0316
 -13.250  -0.9816   0.03493   0.03109  -0.0883   1.0000   0.0314
 -13.000  -0.9874   0.03161   0.02760  -0.0894   1.0000   0.0319
 -12.750  -0.9858   0.02981   0.02567  -0.0884   1.0000   0.0326
 -12.500  -0.9808   0.02835   0.02406  -0.0871   1.0000   0.0333
 -12.250  -0.9736   0.02710   0.02265  -0.0856   1.0000   0.0340
 -12.000  -0.9442   0.02524   0.02076  -0.0887   0.9972   0.0354
 -11.750  -0.9105   0.02426   0.01972  -0.0915   0.9947   0.0368
 -11.500  -0.8776   0.02335   0.01867  -0.0938   0.9921   0.0383
 -11.250  -0.8450   0.02258   0.01773  -0.0957   0.9888   0.0395
 -11.000  -0.8146   0.02109   0.01621  -0.0980   0.9856   0.0413
 -10.750  -0.7795   0.02033   0.01540  -0.1003   0.9836   0.0429
 -10.500  -0.7469   0.01967   0.01463  -0.1019   0.9805   0.0447
 -10.250  -0.7151   0.01908   0.01391  -0.1032   0.9763   0.0460
 -10.000  -0.6832   0.01787   0.01267  -0.1051   0.9731   0.0482
  -9.750  -0.6472   0.01723   0.01198  -0.1072   0.9712   0.0503
  -9.500  -0.6152   0.01667   0.01133  -0.1084   0.9672   0.0523
  -9.250  -0.5839   0.01599   0.01056  -0.1094   0.9623   0.0542
  -9.000  -0.5492   0.01514   0.00970  -0.1113   0.9594   0.0570
  -8.750  -0.5118   0.01458   0.00908  -0.1135   0.9574   0.0598
  -8.500  -0.4805   0.01412   0.00853  -0.1142   0.9523   0.0621
  -8.250  -0.4489   0.01337   0.00779  -0.1153   0.9473   0.0660
  -8.000  -0.4122   0.01292   0.00728  -0.1171   0.9442   0.0698
  -7.750  -0.3762   0.01236   0.00671  -0.1189   0.9410   0.0749
  -7.500  -0.3477   0.01201   0.00633  -0.1190   0.9322   0.0799
  -7.250  -0.3118   0.01154   0.00585  -0.1207   0.9275   0.0865
  -7.000  -0.2811   0.01131   0.00556  -0.1212   0.9185   0.0931
  -6.750  -0.2469   0.01088   0.00513  -0.1225   0.9116   0.1019
  -6.500  -0.2176   0.01060   0.00480  -0.1227   0.9014   0.1091
  -6.250  -0.1859   0.01035   0.00451  -0.1235   0.8926   0.1166
  -6.000  -0.1574   0.01011   0.00422  -0.1235   0.8820   0.1236
  -5.750  -0.1288   0.00994   0.00401  -0.1235   0.8721   0.1307
  -5.500  -0.0999   0.00975   0.00378  -0.1236   0.8626   0.1379
  -5.250  -0.0729   0.00963   0.00362  -0.1233   0.8523   0.1454
  -5.000  -0.0447   0.00950   0.00347  -0.1232   0.8435   0.1541
  -4.750  -0.0176   0.00942   0.00335  -0.1228   0.8340   0.1628
  -4.500   0.0104   0.00937   0.00328  -0.1227   0.8256   0.1728
  -4.250   0.0375   0.00932   0.00321  -0.1223   0.8164   0.1819
  -4.000   0.0655   0.00935   0.00316  -0.1221   0.8082   0.1906
  -3.750   0.0926   0.00931   0.00313  -0.1218   0.7995   0.1989
  -3.500   0.1207   0.00939   0.00312  -0.1216   0.7916   0.2064
  -3.250   0.1475   0.00935   0.00310  -0.1212   0.7826   0.2141
  -3.000   0.1749   0.00941   0.00308  -0.1208   0.7733   0.2204
  -2.750   0.2016   0.00937   0.00298  -0.1203   0.7627   0.2255
  -2.500   0.2280   0.00933   0.00293  -0.1198   0.7518   0.2303
  -2.250   0.2553   0.00936   0.00289  -0.1195   0.7427   0.2349
  -2.000   0.2823   0.00937   0.00284  -0.1191   0.7333   0.2387
  -1.750   0.3091   0.00929   0.00275  -0.1187   0.7249   0.2434
  -1.500   0.3359   0.00927   0.00273  -0.1183   0.7155   0.2479
  -1.250   0.3630   0.00929   0.00270  -0.1179   0.7068   0.2521
  -1.000   0.3899   0.00931   0.00266  -0.1175   0.6972   0.2555
  -0.750   0.4164   0.00923   0.00259  -0.1170   0.6878   0.2595
  -0.500   0.4430   0.00922   0.00256  -0.1166   0.6785   0.2635
  -0.250   0.4698   0.00921   0.00254  -0.1162   0.6689   0.2675
   0.000   0.4964   0.00927   0.00253  -0.1157   0.6594   0.2720
   0.250   0.5227   0.00922   0.00251  -0.1152   0.6488   0.2774
   0.500   0.5491   0.00924   0.00252  -0.1147   0.6390   0.2828
   0.750   0.5755   0.00929   0.00253  -0.1143   0.6291   0.2884
   1.000   0.6017   0.00927   0.00253  -0.1138   0.6192   0.2938
   1.250   0.6277   0.00929   0.00254  -0.1132   0.6095   0.2990
   1.500   0.6538   0.00932   0.00256  -0.1127   0.5988   0.3046
   1.750   0.6797   0.00934   0.00258  -0.1122   0.5888   0.3108
   2.000   0.7054   0.00938   0.00262  -0.1116   0.5790   0.3184
   2.250   0.7314   0.00940   0.00267  -0.1111   0.5690   0.3272
   2.500   0.7566   0.00945   0.00273  -0.1104   0.5584   0.3389
   2.750   0.7816   0.00948   0.00280  -0.1098   0.5470   0.3557
   3.000   0.8066   0.00946   0.00291  -0.1091   0.5359   0.3893
   3.250   0.8307   0.00941   0.00306  -0.1083   0.5256   0.4749
   3.500   0.8525   0.00915   0.00322  -0.1071   0.5146   0.6198
   3.750   0.8936   0.00861   0.00343  -0.1098   0.5020   1.0000
   4.000   0.9178   0.00878   0.00354  -0.1089   0.4908   1.0000
   4.500   0.9657   0.00914   0.00379  -0.1071   0.4658   1.0000
   4.750   0.9895   0.00933   0.00394  -0.1062   0.4530   1.0000
   5.000   1.0130   0.00953   0.00409  -0.1052   0.4406   1.0000
   5.250   1.0358   0.00976   0.00427  -0.1042   0.4274   1.0000
   5.500   1.0587   0.01000   0.00445  -0.1031   0.4147   1.0000
   5.750   1.0819   0.01021   0.00465  -0.1021   0.4029   1.0000
   6.000   1.1046   0.01046   0.00486  -0.1011   0.3918   1.0000
   6.250   1.1262   0.01075   0.00509  -0.0998   0.3812   1.0000
   6.500   1.1482   0.01101   0.00532  -0.0987   0.3683   1.0000
   6.750   1.1694   0.01130   0.00556  -0.0974   0.3545   1.0000
   7.000   1.1905   0.01159   0.00582  -0.0961   0.3425   1.0000
   7.250   1.2107   0.01191   0.00610  -0.0946   0.3314   1.0000
   7.500   1.2319   0.01218   0.00637  -0.0934   0.3214   1.0000
   7.750   1.2522   0.01248   0.00665  -0.0920   0.3104   1.0000
   8.000   1.2702   0.01281   0.00695  -0.0901   0.2990   1.0000
   8.250   1.2875   0.01315   0.00726  -0.0882   0.2861   1.0000
   8.500   1.3053   0.01347   0.00757  -0.0863   0.2724   1.0000
   8.750   1.3211   0.01388   0.00793  -0.0841   0.2560   1.0000
   9.000   1.3356   0.01436   0.00834  -0.0818   0.2358   1.0000
   9.250   1.3456   0.01506   0.00888  -0.0789   0.2045   1.0000
   9.500   1.3487   0.01612   0.00969  -0.0751   0.1633   1.0000
   9.750   1.3526   0.01720   0.01058  -0.0715   0.1366   1.0000
  10.000   1.3608   0.01808   0.01141  -0.0687   0.1229   1.0000
  10.250   1.3703   0.01892   0.01222  -0.0662   0.1127   1.0000
  10.500   1.3813   0.01970   0.01301  -0.0639   0.1036   1.0000
  10.750   1.3906   0.02061   0.01389  -0.0616   0.0937   1.0000
  11.000   1.3990   0.02160   0.01484  -0.0592   0.0809   1.0000
  11.250   1.4048   0.02280   0.01596  -0.0568   0.0673   1.0000
  11.500   1.4093   0.02414   0.01725  -0.0544   0.0577   1.0000
  11.750   1.4140   0.02553   0.01864  -0.0522   0.0512   1.0000
  12.000   1.4163   0.02716   0.02027  -0.0499   0.0461   1.0000
  12.250   1.4220   0.02863   0.02178  -0.0481   0.0422   1.0000
  12.500   1.4231   0.03052   0.02369  -0.0462   0.0390   1.0000
  12.750   1.4288   0.03213   0.02538  -0.0448   0.0365   1.0000
  13.000   1.4291   0.03426   0.02754  -0.0432   0.0341   1.0000
  13.250   1.4312   0.03631   0.02966  -0.0419   0.0323   1.0000
  13.500   1.4348   0.03830   0.03172  -0.0409   0.0307   1.0000
  13.750   1.4351   0.04069   0.03416  -0.0399   0.0294   1.0000
  14.000   1.4286   0.04386   0.03739  -0.0389   0.0282   1.0000
  14.250   1.4315   0.04619   0.03981  -0.0383   0.0273   1.0000
  14.500   1.4325   0.04880   0.04251  -0.0379   0.0264   1.0000
  14.750   1.4326   0.05158   0.04538  -0.0375   0.0256   1.0000
  15.000   1.4307   0.05468   0.04854  -0.0374   0.0248   1.0000
  15.250   1.4249   0.05837   0.05230  -0.0374   0.0241   1.0000
  15.500   1.4174   0.06235   0.05636  -0.0377   0.0235   1.0000
  15.750   1.4188   0.06534   0.05945  -0.0379   0.0229   1.0000
  16.000   1.4176   0.06870   0.06291  -0.0383   0.0223   1.0000
  16.250   1.4155   0.07228   0.06658  -0.0388   0.0218   1.0000
  16.500   1.4137   0.07586   0.07024  -0.0395   0.0213   1.0000
  16.750   1.4104   0.07971   0.07416  -0.0403   0.0208   1.0000
  17.000   1.4061   0.08376   0.07829  -0.0412   0.0205   1.0000
  17.250   1.3997   0.08815   0.08272  -0.0423   0.0200   1.0000
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