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GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 553 AIRFOIL (goe553-il)
Reynolds number: 500,000
Max Cl/Cd: 102.31 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe553-il-500000-n5.txt
Download as CSV file: xf-goe553-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 553 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3447   0.09291   0.09047  -0.0452   1.0000   0.0210
 -10.000  -0.4758   0.02801   0.02392  -0.1130   0.8973   0.0243
  -9.750  -0.4623   0.02545   0.02084  -0.1134   0.8681   0.0248
  -9.500  -0.4431   0.02430   0.01949  -0.1129   0.8387   0.0250
  -9.250  -0.4230   0.02358   0.01857  -0.1122   0.8068   0.0252
  -9.000  -0.4028   0.02286   0.01763  -0.1114   0.7749   0.0255
  -8.750  -0.3824   0.02203   0.01656  -0.1107   0.7482   0.0257
  -8.500  -0.3609   0.02127   0.01559  -0.1101   0.7254   0.0260
  -8.250  -0.3386   0.02049   0.01459  -0.1095   0.7069   0.0263
  -8.000  -0.3155   0.01973   0.01363  -0.1090   0.6922   0.0266
  -7.750  -0.2919   0.01897   0.01268  -0.1086   0.6797   0.0269
  -7.500  -0.2675   0.01829   0.01182  -0.1082   0.6687   0.0274
  -7.250  -0.2426   0.01765   0.01100  -0.1078   0.6597   0.0279
  -7.000  -0.2173   0.01702   0.01021  -0.1075   0.6512   0.0282
  -6.750  -0.1917   0.01645   0.00948  -0.1071   0.6441   0.0285
  -6.500  -0.1655   0.01594   0.00885  -0.1068   0.6372   0.0287
  -6.250  -0.1399   0.01534   0.00814  -0.1065   0.6307   0.0290
  -6.000  -0.1139   0.01477   0.00751  -0.1062   0.6248   0.0293
  -5.750  -0.0875   0.01433   0.00702  -0.1060   0.6188   0.0296
  -5.500  -0.0610   0.01398   0.00661  -0.1057   0.6127   0.0300
  -5.250  -0.0341   0.01365   0.00624  -0.1054   0.6074   0.0304
  -5.000  -0.0070   0.01335   0.00590  -0.1052   0.6016   0.0309
  -4.750   0.0199   0.01307   0.00556  -0.1050   0.5959   0.0314
  -4.500   0.0469   0.01279   0.00523  -0.1047   0.5908   0.0319
  -4.250   0.0743   0.01249   0.00489  -0.1045   0.5856   0.0324
  -4.000   0.1016   0.01224   0.00459  -0.1043   0.5803   0.0328
  -3.750   0.1288   0.01203   0.00432  -0.1041   0.5754   0.0332
  -3.500   0.1565   0.01180   0.00407  -0.1039   0.5707   0.0336
  -3.250   0.1838   0.01150   0.00375  -0.1038   0.5651   0.0342
  -3.000   0.2112   0.01131   0.00353  -0.1036   0.5596   0.0349
  -2.750   0.2389   0.01115   0.00335  -0.1034   0.5548   0.0356
  -2.500   0.2669   0.01100   0.00319  -0.1033   0.5494   0.0366
  -2.250   0.2946   0.01089   0.00305  -0.1032   0.5434   0.0377
  -2.000   0.3224   0.01079   0.00291  -0.1030   0.5375   0.0387
  -1.750   0.3503   0.01065   0.00276  -0.1029   0.5309   0.0400
  -1.500   0.3779   0.01056   0.00264  -0.1027   0.5244   0.0416
  -1.250   0.4059   0.01049   0.00255  -0.1026   0.5183   0.0437
  -1.000   0.4338   0.01042   0.00246  -0.1024   0.5113   0.0468
  -0.750   0.4613   0.01036   0.00238  -0.1022   0.5040   0.0529
  -0.500   0.4886   0.01015   0.00232  -0.1021   0.4943   0.1015
  -0.250   0.5157   0.01004   0.00228  -0.1020   0.4844   0.1400
   0.000   0.5419   0.00969   0.00224  -0.1019   0.4740   0.2682
   0.250   0.5682   0.00935   0.00227  -0.1018   0.4647   0.4087
   0.500   0.5947   0.00931   0.00235  -0.1015   0.4555   0.4751
   0.750   0.6218   0.00931   0.00243  -0.1012   0.4463   0.5207
   1.000   0.6484   0.00936   0.00252  -0.1008   0.4382   0.5608
   1.250   0.6753   0.00939   0.00262  -0.1005   0.4303   0.5926
   1.500   0.7020   0.00949   0.00270  -0.1002   0.4225   0.6105
   1.750   0.7290   0.00956   0.00278  -0.0999   0.4141   0.6246
   2.000   0.7555   0.00968   0.00287  -0.0996   0.4058   0.6379
   2.500   0.8090   0.00990   0.00306  -0.0990   0.3913   0.6605
   2.750   0.8359   0.00998   0.00317  -0.0987   0.3855   0.6727
   3.000   0.8624   0.01007   0.00328  -0.0984   0.3793   0.6905
   3.250   0.8882   0.01018   0.00342  -0.0980   0.3735   0.7113
   3.500   0.9145   0.01025   0.00354  -0.0976   0.3674   0.7319
   3.750   0.9400   0.01035   0.00368  -0.0971   0.3607   0.7553
   4.000   0.9646   0.01040   0.00382  -0.0964   0.3545   0.7912
   4.250   0.9943   0.01024   0.00396  -0.0966   0.3474   0.9280
   4.500   1.0242   0.01044   0.00411  -0.0972   0.3417   1.0000
   4.750   1.0507   0.01060   0.00426  -0.0969   0.3373   1.0000
   5.000   1.0768   0.01077   0.00442  -0.0966   0.3320   1.0000
   5.250   1.1020   0.01100   0.00461  -0.0962   0.3259   1.0000
   5.500   1.1278   0.01119   0.00479  -0.0958   0.3208   1.0000
   5.750   1.1535   0.01137   0.00498  -0.0954   0.3159   1.0000
   6.000   1.1785   0.01160   0.00518  -0.0950   0.3108   1.0000
   6.250   1.2034   0.01182   0.00539  -0.0945   0.3062   1.0000
   6.500   1.2287   0.01201   0.00561  -0.0941   0.3012   1.0000
   6.750   1.2529   0.01226   0.00584  -0.0935   0.2952   1.0000
   7.000   1.2767   0.01252   0.00609  -0.0929   0.2871   1.0000
   7.250   1.2996   0.01283   0.00636  -0.0921   0.2777   1.0000
   7.500   1.3227   0.01311   0.00663  -0.0914   0.2680   1.0000
   7.750   1.3446   0.01345   0.00694  -0.0905   0.2577   1.0000
   8.000   1.3656   0.01383   0.00728  -0.0895   0.2459   1.0000
   8.250   1.3853   0.01426   0.00765  -0.0883   0.2313   1.0000
   8.500   1.4030   0.01478   0.00809  -0.0868   0.2138   1.0000
   8.750   1.4194   0.01534   0.00857  -0.0851   0.1991   1.0000
   9.000   1.4343   0.01587   0.00906  -0.0832   0.1891   1.0000
   9.250   1.4491   0.01635   0.00953  -0.0811   0.1826   1.0000
   9.500   1.4626   0.01688   0.01006  -0.0790   0.1770   1.0000
   9.750   1.4777   0.01735   0.01056  -0.0771   0.1730   1.0000
  10.000   1.4917   0.01788   0.01112  -0.0751   0.1689   1.0000
  10.250   1.5043   0.01849   0.01174  -0.0731   0.1651   1.0000
  10.500   1.5161   0.01916   0.01243  -0.0710   0.1614   1.0000
  10.750   1.5302   0.01974   0.01307  -0.0693   0.1581   1.0000
  11.000   1.5426   0.02044   0.01381  -0.0675   0.1546   1.0000
  11.250   1.5527   0.02128   0.01469  -0.0656   0.1509   1.0000
  11.500   1.5609   0.02229   0.01572  -0.0637   0.1467   1.0000
  11.750   1.5740   0.02306   0.01656  -0.0623   0.1425   1.0000
  12.000   1.5822   0.02418   0.01771  -0.0606   0.1361   1.0000
  12.250   1.5898   0.02541   0.01897  -0.0591   0.1294   1.0000
  12.500   1.5935   0.02700   0.02054  -0.0575   0.1156   1.0000
  12.750   1.5777   0.03030   0.02363  -0.0552   0.0858   1.0000
  13.000   1.5697   0.03325   0.02656  -0.0538   0.0756   1.0000
  13.250   1.5668   0.03592   0.02927  -0.0529   0.0702   1.0000
  13.500   1.5647   0.03862   0.03203  -0.0522   0.0659   1.0000
  13.750   1.5642   0.04125   0.03472  -0.0517   0.0629   1.0000
  14.000   1.5620   0.04412   0.03766  -0.0514   0.0605   1.0000
  14.250   1.5604   0.04699   0.04059  -0.0511   0.0583   1.0000
  14.500   1.5602   0.04978   0.04346  -0.0510   0.0566   1.0000
  14.750   1.5580   0.05286   0.04663  -0.0509   0.0546   1.0000
  15.000   1.5539   0.05624   0.05007  -0.0510   0.0528   1.0000
  15.250   1.5492   0.05980   0.05371  -0.0513   0.0513   1.0000
  15.500   1.5474   0.06309   0.05710  -0.0517   0.0499   1.0000
  15.750   1.5451   0.06655   0.06064  -0.0522   0.0484   1.0000
  16.000   1.5413   0.07027   0.06444  -0.0528   0.0468   1.0000
  16.250   1.5365   0.07423   0.06847  -0.0536   0.0454   1.0000
  16.500   1.5300   0.07851   0.07283  -0.0546   0.0441   1.0000
  16.750   1.5273   0.08232   0.07674  -0.0555   0.0427   1.0000
  17.000   1.5238   0.08631   0.08082  -0.0565   0.0415   1.0000
  17.250   1.5189   0.09059   0.08518  -0.0578   0.0399   1.0000
  17.500   1.5124   0.09516   0.08983  -0.0592   0.0385   1.0000
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