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GOE 573 AIRFOIL (goe573-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 573 AIRFOIL (goe573-il)
Reynolds number: 200,000
Max Cl/Cd: 69.66 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe573-il-200000-n5.txt
Download as CSV file: xf-goe573-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 573 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.0229   0.09189   0.08775  -0.1059   0.8207   0.0309
  -9.750   0.0345   0.08782   0.08354  -0.1133   0.7928   0.0318
  -9.250   0.0461   0.08119   0.07667  -0.1188   0.7460   0.0320
  -9.000   0.0489   0.07811   0.07351  -0.1202   0.7279   0.0320
  -8.750   0.0479   0.07496   0.07029  -0.1220   0.7121   0.0321
  -8.250   0.0591   0.06988   0.06506  -0.1209   0.6838   0.0315
  -8.000   0.0619   0.06745   0.06257  -0.1203   0.6720   0.0306
  -7.750   0.0573   0.06480   0.05989  -0.1201   0.6616   0.0298
  -7.500   0.0513   0.06215   0.05720  -0.1197   0.6530   0.0293
  -7.250   0.0485   0.05905   0.05403  -0.1199   0.6443   0.0289
  -7.000   0.0489   0.05604   0.05094  -0.1202   0.6360   0.0299
  -6.750   0.0501   0.05278   0.04756  -0.1201   0.6284   0.0303
  -6.500   0.0521   0.04907   0.04368  -0.1198   0.6216   0.0309
  -6.250   0.0564   0.04573   0.04017  -0.1188   0.6145   0.0309
  -6.000   0.0607   0.04199   0.03618  -0.1172   0.6086   0.0312
  -5.750   0.0621   0.03734   0.03112  -0.1145   0.6029   0.0326
  -5.500   0.0780   0.03685   0.03059  -0.1134   0.5953   0.0334
  -5.250   0.0926   0.03555   0.02917  -0.1119   0.5882   0.0343
  -5.000   0.1042   0.03323   0.02658  -0.1096   0.5818   0.0346
  -4.750   0.1166   0.03094   0.02398  -0.1073   0.5758   0.0349
  -4.500   0.1317   0.02923   0.02202  -0.1052   0.5690   0.0360
  -4.250   0.1468   0.02738   0.01982  -0.1029   0.5631   0.0373
  -4.000   0.1628   0.02552   0.01762  -0.1006   0.5566   0.0376
  -3.750   0.1804   0.02392   0.01567  -0.0985   0.5503   0.0381
  -3.500   0.1998   0.02264   0.01403  -0.0967   0.5447   0.0386
  -3.250   0.2211   0.02179   0.01285  -0.0952   0.5385   0.0397
  -3.000   0.2425   0.02082   0.01159  -0.0939   0.5330   0.0404
  -2.750   0.2652   0.01985   0.01044  -0.0929   0.5278   0.0409
  -2.500   0.2887   0.01913   0.00957  -0.0920   0.5221   0.0414
  -2.250   0.3125   0.01858   0.00888  -0.0912   0.5172   0.0421
  -2.000   0.3369   0.01809   0.00828  -0.0905   0.5124   0.0427
  -1.750   0.3613   0.01768   0.00779  -0.0898   0.5071   0.0437
  -1.500   0.3854   0.01739   0.00740  -0.0890   0.5025   0.0452
  -1.250   0.4097   0.01708   0.00699  -0.0883   0.4983   0.0466
  -1.000   0.4341   0.01674   0.00660  -0.0876   0.4937   0.0474
  -0.750   0.4580   0.01647   0.00627  -0.0868   0.4897   0.0482
  -0.500   0.4815   0.01626   0.00599  -0.0859   0.4862   0.0491
  -0.250   0.5050   0.01611   0.00576  -0.0850   0.4830   0.0500
   0.000   0.5276   0.01585   0.00553  -0.0840   0.4795   0.0517
   0.250   0.5504   0.01571   0.00539  -0.0831   0.4760   0.0544
   0.500   0.5737   0.01566   0.00530  -0.0822   0.4729   0.0582
   0.750   0.5972   0.01565   0.00520  -0.0814   0.4701   0.0618
   1.000   0.6205   0.01559   0.00513  -0.0805   0.4672   0.0679
   1.250   0.6434   0.01554   0.00514  -0.0796   0.4640   0.0820
   1.500   0.6652   0.01541   0.00518  -0.0785   0.4609   0.1467
   1.750   0.8800   0.01451   0.00600  -0.1197   0.4549   1.0000
   2.000   0.9029   0.01470   0.00607  -0.1188   0.4528   1.0000
   2.250   0.9253   0.01485   0.00620  -0.1179   0.4504   1.0000
   2.500   0.9474   0.01502   0.00635  -0.1169   0.4478   1.0000
   2.750   0.9693   0.01518   0.00649  -0.1158   0.4451   1.0000
   3.000   0.9912   0.01536   0.00663  -0.1148   0.4427   1.0000
   3.250   1.0133   0.01555   0.00678  -0.1138   0.4404   1.0000
   3.500   1.0359   0.01575   0.00693  -0.1130   0.4385   1.0000
   3.750   1.0590   0.01599   0.00710  -0.1123   0.4367   1.0000
   4.000   1.0798   0.01618   0.00734  -0.1111   0.4344   1.0000
   4.250   1.1006   0.01638   0.00758  -0.1099   0.4319   1.0000
   4.500   1.1216   0.01660   0.00781  -0.1087   0.4295   1.0000
   4.750   1.1426   0.01681   0.00804  -0.1076   0.4273   1.0000
   5.000   1.1636   0.01703   0.00826  -0.1064   0.4250   1.0000
   5.250   1.1851   0.01726   0.00844  -0.1054   0.4224   1.0000
   5.500   1.2045   0.01749   0.00871  -0.1040   0.4193   1.0000
   5.750   1.2217   0.01770   0.00899  -0.1021   0.4158   1.0000
   6.000   1.2399   0.01792   0.00925  -0.1005   0.4126   1.0000
   6.250   1.2590   0.01815   0.00951  -0.0990   0.4100   1.0000
   6.500   1.2791   0.01840   0.00978  -0.0978   0.4079   1.0000
   6.750   1.3006   0.01867   0.01004  -0.0969   0.4059   1.0000
   7.000   1.3173   0.01895   0.01041  -0.0950   0.4034   1.0000
   7.250   1.3333   0.01923   0.01081  -0.0930   0.4007   1.0000
   7.500   1.3499   0.01951   0.01117  -0.0912   0.3982   1.0000
   7.750   1.3668   0.01979   0.01152  -0.0894   0.3958   1.0000
   8.000   1.3841   0.02008   0.01186  -0.0877   0.3935   1.0000
   8.250   1.4029   0.02036   0.01217  -0.0863   0.3914   1.0000
   8.500   1.4157   0.02065   0.01255  -0.0838   0.3880   1.0000
   8.750   1.4196   0.02089   0.01291  -0.0795   0.3834   1.0000
   9.000   1.4248   0.02105   0.01312  -0.0754   0.3781   1.0000
   9.250   1.4330   0.02128   0.01336  -0.0720   0.3732   1.0000
   9.500   1.4363   0.02161   0.01384  -0.0680   0.3672   1.0000
   9.750   1.4449   0.02193   0.01421  -0.0649   0.3623   1.0000
  10.000   1.4526   0.02233   0.01470  -0.0619   0.3571   1.0000
  10.250   1.4562   0.02282   0.01529  -0.0583   0.3493   1.0000
  10.500   1.4597   0.02340   0.01594  -0.0549   0.3411   1.0000
  10.750   1.4636   0.02409   0.01670  -0.0519   0.3330   1.0000
  11.000   1.4671   0.02493   0.01764  -0.0490   0.3237   1.0000
  11.250   1.4677   0.02598   0.01876  -0.0460   0.3122   1.0000
  11.500   1.4607   0.02755   0.02031  -0.0426   0.2932   1.0000
  11.750   1.4529   0.02946   0.02219  -0.0396   0.2766   1.0000
  12.000   1.4418   0.03187   0.02456  -0.0368   0.2607   1.0000
  12.250   1.4232   0.03514   0.02777  -0.0341   0.2409   1.0000
  12.500   1.4061   0.03861   0.03122  -0.0319   0.2252   1.0000
  12.750   1.3861   0.04264   0.03522  -0.0302   0.2089   1.0000
  13.000   1.3690   0.04661   0.03920  -0.0289   0.1945   1.0000
  13.250   1.3442   0.05159   0.04413  -0.0278   0.1729   1.0000
  13.500   1.3158   0.05720   0.04966  -0.0269   0.1460   1.0000
  13.750   1.2895   0.06282   0.05520  -0.0264   0.1246   1.0000
  14.000   1.2614   0.06886   0.06114  -0.0261   0.1025   1.0000
  14.250   1.2381   0.07451   0.06671  -0.0261   0.0775   1.0000
  14.500   1.2131   0.08053   0.07263  -0.0262   0.0543   1.0000
  14.750   1.1919   0.08624   0.07828  -0.0265   0.0364   1.0000
  15.000   1.1795   0.09094   0.08299  -0.0269   0.0286   1.0000
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