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GOE 798 AIRFOIL (goe798-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 798 AIRFOIL (goe798-il)
Reynolds number: 100,000
Max Cl/Cd: 31.88 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe798-il-100000-n5.txt
Download as CSV file: xf-goe798-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 798 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.0091   0.10620   0.10002  -0.1187   0.8922   0.0723
 -11.000  -0.0129   0.10134   0.09512  -0.1213   0.8853   0.0732
 -10.750  -0.0216   0.09570   0.08945  -0.1241   0.8787   0.0738
 -10.500  -0.0223   0.09196   0.08570  -0.1255   0.8703   0.0742
 -10.250  -0.0142   0.08923   0.08293  -0.1266   0.8644   0.0749
 -10.000  -0.0096   0.08666   0.08035  -0.1274   0.8563   0.0758
  -9.750  -0.0101   0.08307   0.07674  -0.1289   0.8490   0.0771
  -9.500  -0.0237   0.07719   0.07082  -0.1321   0.8429   0.0785
  -9.250  -0.2579   0.04587   0.03854  -0.1445   0.8244   0.0808
  -9.000  -0.2498   0.04514   0.03777  -0.1427   0.8163   0.0815
  -8.750  -0.2363   0.04398   0.03652  -0.1419   0.8110   0.0826
  -8.500  -0.2241   0.04222   0.03454  -0.1413   0.8072   0.0842
  -8.250  -0.2272   0.04004   0.03202  -0.1387   0.8001   0.0862
  -8.000  -0.2256   0.03745   0.02893  -0.1366   0.7943   0.0885
  -7.750  -0.2009   0.03680   0.02824  -0.1366   0.7906   0.0899
  -7.500  -0.1772   0.03566   0.02692  -0.1367   0.7876   0.0919
  -7.250  -0.1691   0.03467   0.02570  -0.1342   0.7807   0.0942
  -7.000  -0.1534   0.03340   0.02408  -0.1329   0.7761   0.0971
  -6.750  -0.1275   0.03289   0.02356  -0.1329   0.7728   0.0991
  -6.500  -0.1016   0.03200   0.02249  -0.1331   0.7700   0.1022
  -6.250  -0.0835   0.03099   0.02109  -0.1319   0.7658   0.1058
  -6.000  -0.0655   0.03075   0.02092  -0.1305   0.7603   0.1077
  -5.750  -0.0419   0.03031   0.02041  -0.1300   0.7562   0.1108
  -5.500  -0.0160   0.02954   0.01935  -0.1299   0.7531   0.1151
  -5.250   0.0132   0.02892   0.01869  -0.1304   0.7506   0.1181
  -5.000   0.0391   0.02856   0.01829  -0.1303   0.7476   0.1215
  -4.750   0.0529   0.02848   0.01811  -0.1281   0.7420   0.1250
  -4.500   0.0752   0.02811   0.01763  -0.1273   0.7377   0.1283
  -4.250   0.1024   0.02777   0.01731  -0.1274   0.7345   0.1316
  -4.000   0.1323   0.02737   0.01680  -0.1278   0.7319   0.1358
  -3.750   0.1638   0.02693   0.01618  -0.1286   0.7298   0.1400
  -3.500   0.1793   0.02701   0.01636  -0.1267   0.7250   0.1429
  -3.250   0.1957   0.02711   0.01649  -0.1249   0.7199   0.1464
  -3.000   0.2204   0.02697   0.01625  -0.1244   0.7162   0.1508
  -2.750   0.2488   0.02668   0.01594  -0.1246   0.7134   0.1546
  -2.500   0.2800   0.02638   0.01564  -0.1253   0.7111   0.1583
  -2.250   0.3138   0.02602   0.01522  -0.1264   0.7091   0.1620
  -2.000   0.3173   0.02656   0.01580  -0.1224   0.7024   0.1639
  -1.750   0.3356   0.02669   0.01589  -0.1209   0.6978   0.1666
  -1.500   0.3618   0.02651   0.01577  -0.1207   0.6944   0.1698
  -1.250   0.3943   0.02617   0.01542  -0.1215   0.6916   0.1737
  -1.000   0.4322   0.02568   0.01488  -0.1231   0.6890   0.1782
  -0.750   0.4317   0.02633   0.01559  -0.1183   0.6809   0.1806
  -0.500   0.4548   0.02617   0.01546  -0.1174   0.6752   0.1848
  -0.250   0.4919   0.02557   0.01485  -0.1188   0.6711   0.1921
   0.000   0.5349   0.02488   0.01410  -0.1211   0.6679   0.2027
   0.250   0.5255   0.02570   0.01508  -0.1149   0.6581   0.2075
   0.500   0.5520   0.02552   0.01493  -0.1146   0.6536   0.2212
   0.750   0.5856   0.02515   0.01463  -0.1156   0.6506   0.2447
   1.000   0.6234   0.02468   0.01427  -0.1173   0.6481   0.2863
   1.250   0.6111   0.02571   0.01549  -0.1108   0.6393   0.3075
   1.500   0.6327   0.02554   0.01560  -0.1099   0.6346   0.3764
   1.750   0.6637   0.02472   0.01542  -0.1103   0.6313   0.5583
   2.000   0.7374   0.02366   0.01523  -0.1175   0.6289   0.9550
   2.250   0.7343   0.02476   0.01638  -0.1129   0.6201   1.0000
   2.500   0.7483   0.02496   0.01648  -0.1104   0.6147   1.0000
   2.750   0.7833   0.02473   0.01610  -0.1116   0.6112   1.0000
   3.000   0.7777   0.02549   0.01685  -0.1060   0.6041   1.0000
   3.250   0.7793   0.02619   0.01751  -0.1018   0.5966   1.0000
   3.500   0.8127   0.02591   0.01711  -0.1026   0.5928   1.0000
   3.750   0.8148   0.02671   0.01789  -0.0987   0.5851   1.0000
   4.000   0.8218   0.02738   0.01853  -0.0957   0.5772   1.0000
   4.250   0.8580   0.02691   0.01794  -0.0967   0.5733   1.0000
   4.500   0.8449   0.02855   0.01963  -0.0912   0.5620   1.0000
   4.750   0.8727   0.02840   0.01938  -0.0911   0.5565   1.0000
   5.250   0.8939   0.02986   0.02079  -0.0867   0.5398   1.0000
   5.500   0.9298   0.02929   0.02012  -0.0876   0.5356   1.0000
   5.750   0.9209   0.03119   0.02207  -0.0834   0.5230   1.0000
   6.000   0.9538   0.03073   0.02151  -0.0838   0.5181   1.0000
   6.250   0.9525   0.03236   0.02316  -0.0808   0.5064   1.0000
   6.500   0.9829   0.03203   0.02274  -0.0809   0.5007   1.0000
   6.750   0.9886   0.03332   0.02402  -0.0787   0.4900   1.0000
   7.000   1.0156   0.03320   0.02382  -0.0785   0.4833   1.0000
   7.250   1.0280   0.03411   0.02471  -0.0770   0.4742   1.0000
   7.500   1.0491   0.03444   0.02498  -0.0763   0.4669   1.0000
   7.750   1.0758   0.03442   0.02487  -0.0761   0.4611   1.0000
   8.000   1.0836   0.03575   0.02621  -0.0744   0.4523   1.0000
   8.250   1.1112   0.03568   0.02605  -0.0743   0.4471   1.0000
   8.500   1.1275   0.03646   0.02681  -0.0734   0.4407   1.0000
   8.750   1.1408   0.03747   0.02782  -0.0722   0.4341   1.0000
   9.000   1.1671   0.03753   0.02780  -0.0721   0.4294   1.0000
   9.250   1.1858   0.03817   0.02842  -0.0713   0.4239   1.0000
   9.500   1.1936   0.03958   0.02986  -0.0698   0.4170   1.0000
   9.750   1.2173   0.03980   0.03001  -0.0695   0.4118   1.0000
  10.000   1.2370   0.04037   0.03054  -0.0689   0.4067   1.0000
  10.250   1.2416   0.04207   0.03232  -0.0672   0.4004   1.0000
  10.500   1.2594   0.04276   0.03297  -0.0665   0.3952   1.0000
  10.750   1.2911   0.04243   0.03253  -0.0668   0.3912   1.0000
  11.000   1.2873   0.04481   0.03504  -0.0647   0.3851   1.0000
  11.250   1.2966   0.04619   0.03645  -0.0635   0.3795   1.0000
  11.500   1.3196   0.04646   0.03667  -0.0632   0.3751   1.0000
  11.750   1.3367   0.04726   0.03746  -0.0626   0.3707   1.0000
  12.000   1.3319   0.04987   0.04021  -0.0607   0.3649   1.0000
  12.250   1.3429   0.05118   0.04156  -0.0598   0.3603   1.0000
  12.500   1.3655   0.05150   0.04185  -0.0595   0.3566   1.0000
  12.750   1.3849   0.05212   0.04246  -0.0591   0.3529   1.0000
  13.000   1.3708   0.05573   0.04627  -0.0571   0.3475   1.0000
  13.250   1.3753   0.05770   0.04833  -0.0560   0.3429   1.0000
  13.500   1.3941   0.05831   0.04894  -0.0556   0.3391   1.0000
  13.750   1.4270   0.05764   0.04818  -0.0558   0.3359   1.0000
  14.000   1.3928   0.06337   0.05420  -0.0533   0.3297   1.0000
  14.250   1.3880   0.06638   0.05732  -0.0522   0.3243   1.0000
  14.500   1.4089   0.06669   0.05762  -0.0519   0.3203   1.0000
  14.750   1.4411   0.06587   0.05673  -0.0519   0.3170   1.0000
  15.000   1.3744   0.07571   0.06695  -0.0495   0.3084   1.0000
  15.250   1.3843   0.07722   0.06850  -0.0490   0.3037   1.0000
  15.500   1.4166   0.07613   0.06736  -0.0489   0.3004   1.0000
  15.750   1.3322   0.08917   0.08076  -0.0477   0.2888   1.0000
  16.000   1.3557   0.08896   0.08055  -0.0475   0.2849   1.0000
  16.250   1.3942   0.08684   0.07838  -0.0473   0.2822   1.0000
  16.500   1.3059   0.10145   0.09331  -0.0477   0.2680   1.0000
  16.750   1.3415   0.09947   0.09129  -0.0473   0.2659   1.0000
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