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GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 479 AIRFOIL (goe479-il)
Reynolds number: 100,000
Max Cl/Cd: 53.93 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe479-il-100000.txt
Download as CSV file: xf-goe479-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 479 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3273   0.10060   0.09548  -0.0356   1.0000   0.1246
  -8.750  -0.3565   0.09985   0.09488  -0.0369   1.0000   0.1281
  -8.500  -0.3972   0.09970   0.09492  -0.0365   1.0000   0.1288
  -8.250  -0.3667   0.09399   0.08919  -0.0341   1.0000   0.1312
  -8.000  -0.3510   0.09151   0.08671  -0.0312   1.0000   0.1354
  -7.750  -0.3620   0.08993   0.08521  -0.0290   1.0000   0.1388
  -7.500  -0.3869   0.08890   0.08432  -0.0264   1.0000   0.1412
  -7.250  -0.4234   0.08797   0.08353  -0.0255   1.0000   0.1432
  -7.000  -0.4755   0.08655   0.08206  -0.0315   1.0000   0.1448
  -6.750  -0.4569   0.08261   0.07830  -0.0244   1.0000   0.1466
  -6.500  -0.4535   0.08084   0.07660  -0.0201   1.0000   0.1487
  -6.250  -0.4578   0.07910   0.07489  -0.0178   1.0000   0.1514
  -6.000  -0.4525   0.07357   0.06918  -0.0304   0.9939   0.1623
  -5.750  -0.4252   0.07057   0.06625  -0.0294   0.9882   0.1656
  -5.500  -0.3961   0.06565   0.06111  -0.0390   0.9784   0.1798
  -5.250  -0.3659   0.06312   0.05862  -0.0395   0.9722   0.1867
  -5.000  -0.3397   0.05911   0.05447  -0.0448   0.9624   0.1995
  -4.750  -0.2995   0.04132   0.03484  -0.0603   0.9551   0.1160
  -4.500  -0.2703   0.03801   0.03109  -0.0617   0.9458   0.1118
  -4.250  -0.2305   0.03461   0.02722  -0.0649   0.9402   0.1096
  -4.000  -0.2017   0.03213   0.02429  -0.0655   0.9300   0.1084
  -3.750  -0.1566   0.02996   0.02163  -0.0687   0.9250   0.1102
  -3.500  -0.1297   0.02874   0.01999  -0.0684   0.9141   0.1129
  -3.250  -0.0849   0.02697   0.01795  -0.0714   0.9094   0.1161
  -3.000  -0.0589   0.02617   0.01712  -0.0711   0.8988   0.1205
  -2.750  -0.0136   0.02524   0.01594  -0.0739   0.8938   0.1287
  -2.500   0.0131   0.02437   0.01517  -0.0737   0.8839   0.1352
  -2.250   0.0565   0.02342   0.01422  -0.0762   0.8785   0.1491
  -1.750   0.1263   0.02182   0.01291  -0.0782   0.8634   0.1993
  -1.500   0.1708   0.02048   0.01209  -0.0808   0.8597   0.2897
  -1.250   0.1903   0.01960   0.01194  -0.0793   0.8484   0.4250
  -1.000   0.3208   0.01754   0.01125  -0.0972   0.8517   1.0000
  -0.750   0.3622   0.01723   0.01071  -0.0992   0.8447   1.0000
  -0.500   0.3853   0.01729   0.01061  -0.0981   0.8330   1.0000
  -0.250   0.4275   0.01693   0.01007  -0.1001   0.8268   1.0000
   0.000   0.4479   0.01706   0.01008  -0.0984   0.8141   1.0000
   0.250   0.4748   0.01705   0.00996  -0.0978   0.8033   1.0000
   0.500   0.5099   0.01682   0.00960  -0.0985   0.7949   1.0000
   0.750   0.5317   0.01697   0.00965  -0.0970   0.7824   1.0000
   1.000   0.5591   0.01698   0.00957  -0.0965   0.7716   1.0000
   1.250   0.5912   0.01685   0.00933  -0.0966   0.7618   1.0000
   1.500   0.6131   0.01704   0.00946  -0.0951   0.7489   1.0000
   1.750   0.6382   0.01716   0.00950  -0.0941   0.7368   1.0000
   2.000   0.6692   0.01712   0.00935  -0.0940   0.7264   1.0000
   2.250   0.6931   0.01725   0.00941  -0.0928   0.7129   1.0000
   2.500   0.7160   0.01743   0.00953  -0.0915   0.6989   1.0000
   2.750   0.7401   0.01758   0.00963  -0.0903   0.6854   1.0000
   3.000   0.7662   0.01772   0.00968  -0.0895   0.6731   1.0000
   3.250   0.7934   0.01784   0.00972  -0.0888   0.6614   1.0000
   3.500   0.8145   0.01815   0.01004  -0.0874   0.6480   1.0000
   3.750   0.8375   0.01843   0.01030  -0.0862   0.6357   1.0000
   4.000   0.8641   0.01861   0.01042  -0.0855   0.6245   1.0000
   4.250   0.8879   0.01885   0.01065  -0.0844   0.6122   1.0000
   4.500   0.9093   0.01917   0.01099  -0.0831   0.5993   1.0000
   4.750   0.9329   0.01943   0.01124  -0.0820   0.5873   1.0000
   5.000   0.9602   0.01957   0.01133  -0.0814   0.5760   1.0000
   5.250   0.9814   0.01985   0.01165  -0.0800   0.5626   1.0000
   5.500   1.0028   0.02014   0.01199  -0.0786   0.5493   1.0000
   5.750   1.0255   0.02038   0.01223  -0.0773   0.5358   1.0000
   6.000   1.0482   0.02052   0.01238  -0.0760   0.5210   1.0000
   6.250   1.0699   0.02061   0.01244  -0.0745   0.5045   1.0000
   6.500   1.0905   0.02068   0.01246  -0.0727   0.4864   1.0000
   6.750   1.1108   0.02079   0.01253  -0.0710   0.4680   1.0000
   7.000   1.1309   0.02102   0.01272  -0.0693   0.4504   1.0000
   7.250   1.1503   0.02133   0.01300  -0.0676   0.4332   1.0000
   7.500   1.1689   0.02168   0.01334  -0.0657   0.4162   1.0000
   7.750   1.1863   0.02204   0.01369  -0.0638   0.3990   1.0000
   8.000   1.2025   0.02241   0.01407  -0.0616   0.3820   1.0000
   8.250   1.2165   0.02278   0.01446  -0.0592   0.3645   1.0000
   8.500   1.2282   0.02316   0.01493  -0.0564   0.3466   1.0000
   8.750   1.2384   0.02356   0.01541  -0.0534   0.3278   1.0000
   9.000   1.2472   0.02401   0.01591  -0.0503   0.3085   1.0000
   9.250   1.2521   0.02455   0.01641  -0.0466   0.2874   1.0000
   9.500   1.2515   0.02525   0.01711  -0.0421   0.2620   1.0000
   9.750   1.2461   0.02635   0.01808  -0.0373   0.2304   1.0000
  10.000   1.2362   0.02800   0.01953  -0.0326   0.1922   1.0000
  10.250   1.2249   0.03012   0.02138  -0.0284   0.1552   1.0000
  10.500   1.2174   0.03232   0.02338  -0.0250   0.1339   1.0000
  10.750   1.2136   0.03444   0.02538  -0.0223   0.1219   1.0000
  11.000   1.2126   0.03651   0.02738  -0.0201   0.1139   1.0000
  11.250   1.2155   0.03841   0.02928  -0.0183   0.1076   1.0000
  11.500   1.2192   0.04032   0.03117  -0.0167   0.1025   1.0000
  11.750   1.2268   0.04210   0.03291  -0.0151   0.0985   1.0000
  12.000   1.2386   0.04365   0.03453  -0.0138   0.0950   1.0000
  12.250   1.2518   0.04516   0.03603  -0.0127   0.0918   1.0000
  12.500   1.2749   0.04649   0.03719  -0.0118   0.0882   1.0000
  12.750   1.2880   0.04819   0.03910  -0.0107   0.0856   1.0000
  13.000   1.3061   0.04983   0.04086  -0.0099   0.0834   1.0000
  13.250   1.3260   0.05152   0.04262  -0.0092   0.0812   1.0000
  13.500   1.3708   0.05342   0.04432  -0.0100   0.0777   1.0000
  13.750   1.3731   0.05579   0.04701  -0.0085   0.0767   1.0000
  14.000   1.3760   0.05846   0.04997  -0.0073   0.0758   1.0000
  14.250   1.3756   0.06141   0.05320  -0.0061   0.0750   1.0000
  14.500   1.3712   0.06461   0.05667  -0.0051   0.0742   1.0000
  14.750   1.3634   0.06814   0.06047  -0.0043   0.0735   1.0000
  15.000   1.3526   0.07196   0.06455  -0.0039   0.0729   1.0000
  15.250   1.3386   0.07620   0.06905  -0.0038   0.0724   1.0000
  15.500   1.3190   0.08121   0.07433  -0.0044   0.0722   1.0000
  15.750   1.2931   0.08715   0.08056  -0.0058   0.0724   1.0000
  16.000   1.2598   0.09440   0.08811  -0.0085   0.0728   1.0000
  16.250   1.2185   0.10365   0.09765  -0.0129   0.0738   1.0000
  16.500   1.1724   0.11496   0.10923  -0.0192   0.0752   1.0000
  16.750   1.1259   0.12801   0.12244  -0.0270   0.0767   1.0000
  17.000   1.0919   0.14022   0.13476  -0.0339   0.0777   1.0000
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