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GOE 418 AIRFOIL (goe418-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 418 AIRFOIL (goe418-il)
Reynolds number: 100,000
Max Cl/Cd: 52.6 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe418-il-100000.txt
Download as CSV file: xf-goe418-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 418 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2701   0.10070   0.09585  -0.0257   1.0000   0.1310
  -7.750  -0.2987   0.10117   0.09646  -0.0222   1.0000   0.1324
  -7.500  -0.3346   0.10084   0.09621  -0.0373   0.9852   0.1346
  -7.250  -0.2979   0.09545   0.09084  -0.0319   0.9849   0.1359
  -7.000  -0.2533   0.09106   0.08642  -0.0336   0.9817   0.1395
  -6.750  -0.2279   0.08757   0.08292  -0.0401   0.9701   0.1453
  -6.500  -0.2095   0.08202   0.07730  -0.0569   0.9532   0.1511
  -6.250  -0.1791   0.07873   0.07403  -0.0555   0.9449   0.1537
  -6.000  -0.1537   0.07561   0.07068  -0.0729   0.9273   0.1660
  -5.750  -0.1217   0.07037   0.06551  -0.0731   0.9231   0.1685
  -5.500  -0.0802   0.06702   0.06219  -0.0746   0.9200   0.1736
  -5.250  -0.0587   0.06325   0.05820  -0.0857   0.9041   0.1857
  -5.000  -0.0294   0.06032   0.05534  -0.0848   0.8965   0.1891
  -4.750  -0.0024   0.05746   0.05225  -0.0924   0.8847   0.2043
  -4.500   0.0185   0.05506   0.04994  -0.0903   0.8741   0.2078
  -4.250   0.0474   0.05245   0.04711  -0.0957   0.8646   0.2237
  -4.000   0.0633   0.05046   0.04520  -0.0934   0.8526   0.2276
  -3.750   0.0911   0.04815   0.04273  -0.0964   0.8446   0.2443
  -3.500   0.1072   0.04720   0.04173  -0.0953   0.8321   0.2577
  -3.250   0.1318   0.04451   0.03902  -0.0955   0.8251   0.2674
  -3.000   0.1464   0.04317   0.03759  -0.0951   0.8130   0.2835
  -2.750   0.1941   0.03447   0.02749  -0.1051   0.8060   0.1808
  -2.500   0.2138   0.03256   0.02536  -0.1043   0.7953   0.1768
  -2.250   0.2433   0.03056   0.02301  -0.1046   0.7876   0.1768
  -2.000   0.2667   0.02916   0.02133  -0.1039   0.7778   0.1769
  -1.750   0.2953   0.02789   0.01972  -0.1036   0.7694   0.1800
  -1.500   0.3222   0.02699   0.01848  -0.1031   0.7610   0.1830
  -1.250   0.3475   0.02597   0.01730  -0.1024   0.7518   0.1863
  -1.000   0.3787   0.02519   0.01648  -0.1024   0.7455   0.1918
  -0.750   0.3998   0.02491   0.01612  -0.1012   0.7350   0.1959
  -0.500   0.4316   0.02432   0.01525  -0.1011   0.7284   0.2016
  -0.250   0.4538   0.02394   0.01487  -0.1000   0.7188   0.2059
   0.000   0.4828   0.02349   0.01439  -0.0997   0.7111   0.2119
   0.250   0.5089   0.02331   0.01412  -0.0990   0.7028   0.2182
   0.500   0.5353   0.02302   0.01377  -0.0983   0.6940   0.2236
   0.750   0.5663   0.02262   0.01338  -0.0982   0.6874   0.2315
   1.000   0.5876   0.02271   0.01348  -0.0969   0.6769   0.2387
   1.250   0.6190   0.02228   0.01305  -0.0967   0.6699   0.2473
   1.500   0.6401   0.02244   0.01328  -0.0954   0.6595   0.2576
   1.750   0.6698   0.02213   0.01303  -0.0951   0.6519   0.2714
   2.000   0.6929   0.02215   0.01316  -0.0939   0.6417   0.2882
   2.250   0.7224   0.02172   0.01284  -0.0935   0.6325   0.3259
   2.500   0.7718   0.02001   0.01266  -0.0970   0.6200   1.0000
   2.750   0.8021   0.02003   0.01239  -0.0965   0.6111   1.0000
   3.000   0.8214   0.02044   0.01276  -0.0948   0.5991   1.0000
   3.250   0.8523   0.02047   0.01254  -0.0945   0.5906   1.0000
   3.500   0.8705   0.02090   0.01300  -0.0926   0.5784   1.0000
   3.750   0.9016   0.02096   0.01283  -0.0924   0.5706   1.0000
   4.000   0.9190   0.02142   0.01337  -0.0905   0.5587   1.0000
   4.250   0.9489   0.02147   0.01324  -0.0902   0.5505   1.0000
   4.500   0.9675   0.02182   0.01365  -0.0884   0.5386   1.0000
   4.750   0.9950   0.02192   0.01362  -0.0878   0.5299   1.0000
   5.000   1.0158   0.02217   0.01389  -0.0863   0.5186   1.0000
   5.250   1.0404   0.02229   0.01394  -0.0853   0.5086   1.0000
   5.500   1.0644   0.02235   0.01395  -0.0841   0.4980   1.0000
   5.750   1.0859   0.02260   0.01421  -0.0828   0.4876   1.0000
   6.000   1.1118   0.02267   0.01421  -0.0820   0.4785   1.0000
   6.250   1.1315   0.02302   0.01462  -0.0804   0.4682   1.0000
   6.500   1.1587   0.02302   0.01451  -0.0798   0.4591   1.0000
   6.750   1.1760   0.02339   0.01498  -0.0779   0.4477   1.0000
   7.000   1.2004   0.02346   0.01497  -0.0769   0.4374   1.0000
   7.250   1.2205   0.02362   0.01515  -0.0753   0.4252   1.0000
   7.500   1.2382   0.02387   0.01544  -0.0733   0.4122   1.0000
   7.750   1.2574   0.02405   0.01558  -0.0716   0.3986   1.0000
   8.000   1.2756   0.02425   0.01573  -0.0697   0.3837   1.0000
   8.250   1.2912   0.02458   0.01598  -0.0674   0.3670   1.0000
   8.500   1.3033   0.02506   0.01641  -0.0647   0.3480   1.0000
   8.750   1.3131   0.02572   0.01699  -0.0618   0.3274   1.0000
   9.000   1.3224   0.02654   0.01768  -0.0589   0.3073   1.0000
   9.250   1.3324   0.02748   0.01849  -0.0562   0.2898   1.0000
   9.500   1.3434   0.02844   0.01935  -0.0537   0.2758   1.0000
   9.750   1.3589   0.02937   0.02011  -0.0520   0.2648   1.0000
  10.000   1.3693   0.03035   0.02114  -0.0496   0.2554   1.0000
  10.250   1.3898   0.03134   0.02202  -0.0487   0.2482   1.0000
  10.500   1.4024   0.03242   0.02320  -0.0467   0.2418   1.0000
  10.750   1.4241   0.03335   0.02405  -0.0461   0.2361   1.0000
  11.000   1.4395   0.03450   0.02525  -0.0446   0.2309   1.0000
  11.250   1.4492   0.03560   0.02645  -0.0425   0.2257   1.0000
  11.500   1.4695   0.03645   0.02720  -0.0417   0.2202   1.0000
  11.750   1.4777   0.03769   0.02855  -0.0396   0.2154   1.0000
  12.000   1.4808   0.03889   0.02988  -0.0370   0.2102   1.0000
  12.250   1.5026   0.03961   0.03039  -0.0365   0.2038   1.0000
  12.500   1.4997   0.04117   0.03217  -0.0336   0.1998   1.0000
  12.750   1.5019   0.04263   0.03377  -0.0315   0.1954   1.0000
  13.000   1.5202   0.04358   0.03465  -0.0307   0.1907   1.0000
  13.250   1.5328   0.04507   0.03619  -0.0296   0.1867   1.0000
  13.500   1.5270   0.04710   0.03847  -0.0273   0.1835   1.0000
  13.750   1.5301   0.04880   0.04028  -0.0258   0.1795   1.0000
  14.000   1.5647   0.04937   0.04061  -0.0262   0.1736   1.0000
  14.250   1.5480   0.05206   0.04362  -0.0237   0.1711   1.0000
  14.500   1.5368   0.05476   0.04656  -0.0220   0.1678   1.0000
  14.750   1.5493   0.05604   0.04781  -0.0212   0.1627   1.0000
  15.000   1.5566   0.05806   0.04985  -0.0204   0.1580   1.0000
  15.250   1.5343   0.06186   0.05395  -0.0192   0.1550   1.0000
  15.500   1.5283   0.06464   0.05684  -0.0185   0.1506   1.0000
  15.750   1.5444   0.06611   0.05822  -0.0180   0.1445   1.0000
  16.000   1.5135   0.07130   0.06375  -0.0179   0.1419   1.0000
  16.250   1.4935   0.07592   0.06856  -0.0182   0.1382   1.0000
  16.500   1.5128   0.07705   0.06955  -0.0175   0.1315   1.0000
  16.750   1.4688   0.08464   0.07750  -0.0193   0.1299   1.0000
  17.000   1.4161   0.09439   0.08762  -0.0228   0.1286   1.0000
  17.250   1.4752   0.09017   0.08301  -0.0195   0.1201   1.0000
  17.500   1.4167   0.10086   0.09409  -0.0239   0.1197   1.0000
  17.750   1.3310   0.11779   0.11144  -0.0326   0.1202   1.0000
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