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GOE 496 AIRFOIL (goe496-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 496 AIRFOIL (goe496-il)
Reynolds number: 100,000
Max Cl/Cd: 62.88 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe496-il-100000.txt
Download as CSV file: xf-goe496-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 496 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3356   0.10455   0.09977  -0.0329   1.0000   0.1183
  -8.000  -0.3666   0.10533   0.10072  -0.0308   1.0000   0.1190
  -7.750  -0.3968   0.10580   0.10134  -0.0287   1.0000   0.1193
  -7.500  -0.4053   0.10271   0.09834  -0.0274   1.0000   0.1201
  -7.250  -0.3646   0.09658   0.09211  -0.0234   1.0000   0.1234
  -7.000  -0.3726   0.09520   0.09080  -0.0204   1.0000   0.1251
  -6.750  -0.3859   0.09416   0.08982  -0.0174   1.0000   0.1269
  -6.500  -0.3981   0.09285   0.08860  -0.0156   1.0000   0.1292
  -6.250  -0.4124   0.09140   0.08723  -0.0162   1.0000   0.1325
  -6.000  -0.4268   0.08809   0.08397  -0.0289   1.0000   0.1356
  -5.750  -0.4096   0.08467   0.08056  -0.0232   0.9968   0.1375
  -5.500  -0.3827   0.08172   0.07757  -0.0241   0.9915   0.1430
  -5.250  -0.3438   0.07519   0.07093  -0.0409   0.9827   0.1529
  -5.000  -0.2983   0.06947   0.06498  -0.0582   0.9735   0.1669
  -4.750  -0.2801   0.06657   0.06215  -0.0552   0.9681   0.1687
  -4.500  -0.1919   0.04084   0.03479  -0.0929   0.9655   0.1057
  -4.250  -0.1479   0.03631   0.02973  -0.0987   0.9607   0.1027
  -4.000  -0.0978   0.03276   0.02533  -0.1049   0.9571   0.1042
  -3.750  -0.0642   0.03032   0.02259  -0.1073   0.9500   0.1066
  -3.500  -0.0221   0.02868   0.02069  -0.1106   0.9446   0.1096
  -3.250   0.0153   0.02744   0.01913  -0.1127   0.9381   0.1142
  -3.000   0.0542   0.02630   0.01771  -0.1151   0.9313   0.1225
  -2.750   0.0980   0.02539   0.01660  -0.1181   0.9265   0.1334
  -2.500   0.1283   0.02456   0.01578  -0.1187   0.9176   0.1467
  -2.250   0.1730   0.02361   0.01488  -0.1219   0.9131   0.1829
  -2.000   0.2012   0.02330   0.01470  -0.1222   0.9035   0.2156
  -1.750   0.2446   0.02302   0.01448  -0.1250   0.8983   0.2481
  -1.500   0.2722   0.02302   0.01453  -0.1251   0.8884   0.2725
  -1.250   0.3162   0.02275   0.01431  -0.1280   0.8834   0.3094
  -1.000   0.3434   0.02262   0.01431  -0.1279   0.8736   0.3389
  -0.750   0.3870   0.02203   0.01394  -0.1305   0.8688   0.3917
  -0.500   0.4153   0.02187   0.01397  -0.1304   0.8598   0.4490
  -0.250   0.4569   0.02136   0.01364  -0.1324   0.8545   0.5163
   0.000   0.4954   0.02090   0.01341  -0.1339   0.8490   0.5802
   0.250   0.5241   0.02063   0.01339  -0.1336   0.8402   0.6526
   0.500   0.5645   0.01936   0.01276  -0.1344   0.8365   1.0000
   0.750   0.5913   0.01968   0.01287  -0.1345   0.8256   1.0000
   1.000   0.6355   0.01939   0.01241  -0.1369   0.8211   1.0000
   1.250   0.6596   0.01975   0.01266  -0.1363   0.8102   1.0000
   1.500   0.7015   0.01946   0.01228  -0.1381   0.8054   1.0000
   1.750   0.7243   0.01987   0.01262  -0.1372   0.7943   1.0000
   2.000   0.7663   0.01949   0.01217  -0.1389   0.7892   1.0000
   2.250   0.7906   0.01968   0.01232  -0.1379   0.7768   1.0000
   2.500   0.8202   0.01956   0.01216  -0.1374   0.7651   1.0000
   2.750   0.8555   0.01913   0.01167  -0.1376   0.7544   1.0000
   3.000   0.8880   0.01888   0.01137  -0.1375   0.7435   1.0000
   3.250   0.9124   0.01910   0.01160  -0.1365   0.7316   1.0000
   3.500   0.9409   0.01917   0.01166  -0.1361   0.7214   1.0000
   3.750   0.9728   0.01908   0.01155  -0.1361   0.7119   1.0000
   4.000   0.9967   0.01932   0.01183  -0.1351   0.6996   1.0000
   4.250   1.0231   0.01945   0.01198  -0.1344   0.6880   1.0000
   4.500   1.0528   0.01943   0.01197  -0.1340   0.6771   1.0000
   4.750   1.0813   0.01942   0.01197  -0.1335   0.6650   1.0000
   5.000   1.1059   0.01957   0.01217  -0.1324   0.6511   1.0000
   5.250   1.1312   0.01969   0.01235  -0.1314   0.6370   1.0000
   5.500   1.1569   0.01976   0.01246  -0.1305   0.6219   1.0000
   5.750   1.1825   0.01982   0.01254  -0.1294   0.6058   1.0000
   6.000   1.2083   0.01987   0.01263  -0.1284   0.5886   1.0000
   6.250   1.2330   0.01998   0.01273  -0.1272   0.5694   1.0000
   6.500   1.2541   0.02018   0.01299  -0.1254   0.5467   1.0000
   6.750   1.2780   0.02035   0.01310  -0.1240   0.5232   1.0000
   7.000   1.2972   0.02063   0.01337  -0.1220   0.4950   1.0000
   7.250   1.3141   0.02091   0.01358  -0.1195   0.4634   1.0000
   7.500   1.3292   0.02130   0.01385  -0.1169   0.4311   1.0000
   7.750   1.3434   0.02183   0.01429  -0.1143   0.4004   1.0000
   8.000   1.3573   0.02248   0.01489  -0.1118   0.3720   1.0000
   8.250   1.3700   0.02321   0.01555  -0.1092   0.3447   1.0000
   8.500   1.3815   0.02402   0.01628  -0.1066   0.3189   1.0000
   8.750   1.3913   0.02493   0.01707  -0.1037   0.2948   1.0000
   9.000   1.3995   0.02587   0.01802  -0.1008   0.2702   1.0000
   9.250   1.4036   0.02693   0.01902  -0.0972   0.2467   1.0000
   9.500   1.4030   0.02817   0.02020  -0.0931   0.2197   1.0000
   9.750   1.3978   0.02972   0.02171  -0.0888   0.1827   1.0000
  10.000   1.3870   0.03198   0.02369  -0.0843   0.1387   1.0000
  10.250   1.3784   0.03459   0.02599  -0.0806   0.1108   1.0000
  10.500   1.3733   0.03718   0.02840  -0.0775   0.0959   1.0000
  10.750   1.3726   0.03967   0.03086  -0.0749   0.0858   1.0000
  11.000   1.3743   0.04218   0.03331  -0.0727   0.0786   1.0000
  11.250   1.3798   0.04443   0.03556  -0.0709   0.0723   1.0000
  11.500   1.3927   0.04672   0.03784  -0.0693   0.0674   1.0000
  11.750   1.4085   0.04875   0.03998  -0.0680   0.0633   1.0000
  12.000   1.4412   0.05122   0.04223  -0.0680   0.0584   1.0000
  12.250   1.4498   0.05347   0.04480  -0.0664   0.0562   1.0000
  12.500   1.4651   0.05602   0.04758  -0.0653   0.0540   1.0000
  12.750   1.4805   0.05882   0.05062  -0.0643   0.0524   1.0000
  13.000   1.4921   0.06185   0.05384  -0.0633   0.0511   1.0000
  13.250   1.5114   0.06560   0.05766  -0.0630   0.0493   1.0000
  13.500   1.5112   0.07023   0.06257  -0.0619   0.0484   1.0000
  13.750   1.4967   0.07379   0.06647  -0.0600   0.0481   1.0000
  14.000   1.4810   0.07782   0.07083  -0.0588   0.0479   1.0000
  14.250   1.4642   0.08233   0.07566  -0.0581   0.0477   1.0000
  14.500   1.4461   0.08731   0.08094  -0.0581   0.0477   1.0000
  14.750   1.4266   0.09279   0.08669  -0.0588   0.0477   1.0000
  15.000   1.4062   0.09871   0.09288  -0.0601   0.0478   1.0000
  15.250   1.3852   0.10509   0.09950  -0.0622   0.0480   1.0000
  15.500   1.3639   0.11195   0.10658  -0.0649   0.0482   1.0000
  15.750   1.3438   0.11925   0.11407  -0.0683   0.0485   1.0000
  16.000   1.3186   0.12686   0.12194  -0.0732   0.0489   1.0000
  16.250   1.1653   0.17221   0.16783  -0.1076   0.0599   1.0000
  16.500   1.1755   0.17364   0.16927  -0.1071   0.0588   1.0000
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