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GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 413 AIRFOIL (goe413-il)
Reynolds number: 100,000
Max Cl/Cd: 47.3 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe413-il-100000.txt
Download as CSV file: xf-goe413-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 413 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2213   0.12256   0.11751  -0.0387   1.0000   0.1518
 -10.000  -0.2507   0.12379   0.11887  -0.0354   1.0000   0.1545
  -9.750  -0.3034   0.12533   0.12056  -0.0386   0.9964   0.1564
  -9.500  -0.2532   0.11860   0.11377  -0.0391   0.9936   0.1579
  -9.250  -0.2177   0.11408   0.10923  -0.0423   0.9884   0.1605
  -9.000  -0.1916   0.11008   0.10520  -0.0472   0.9825   0.1647
  -8.750  -0.2138   0.10710   0.10226  -0.0607   0.9710   0.1714
  -8.500  -0.1615   0.10137   0.09647  -0.0608   0.9689   0.1734
  -8.250  -0.1236   0.09730   0.09238  -0.0643   0.9646   0.1772
  -8.000  -0.1061   0.09394   0.08900  -0.0690   0.9537   0.1830
  -7.750  -0.1205   0.09013   0.08522  -0.0783   0.9378   0.1880
  -7.500  -0.2219   0.05690   0.05150  -0.1124   0.9144   0.1191
  -7.250  -0.2128   0.05299   0.04748  -0.1144   0.9011   0.1169
  -7.000  -0.2155   0.04538   0.03938  -0.1203   0.8892   0.1137
  -6.750  -0.2074   0.03985   0.03323  -0.1236   0.8779   0.1126
  -6.500  -0.1908   0.03681   0.02974  -0.1246   0.8674   0.1128
  -6.250  -0.1677   0.03429   0.02679  -0.1255   0.8586   0.1132
  -6.000  -0.1443   0.03246   0.02461  -0.1257   0.8497   0.1137
  -5.750  -0.1200   0.03100   0.02286  -0.1257   0.8405   0.1147
  -5.500  -0.0906   0.02959   0.02115  -0.1259   0.8351   0.1163
  -5.250  -0.0689   0.02887   0.02016  -0.1255   0.8242   0.1183
  -5.000  -0.0410   0.02799   0.01932  -0.1253   0.8176   0.1210
  -4.750  -0.0158   0.02751   0.01881  -0.1249   0.8096   0.1240
  -4.500   0.0100   0.02693   0.01812  -0.1245   0.8014   0.1272
  -4.250   0.0391   0.02615   0.01723  -0.1242   0.7962   0.1309
  -4.000   0.0627   0.02593   0.01712  -0.1238   0.7876   0.1353
  -3.750   0.0900   0.02551   0.01659  -0.1235   0.7804   0.1425
  -3.500   0.1190   0.02498   0.01615  -0.1233   0.7757   0.1528
  -3.250   0.1427   0.02491   0.01619  -0.1230   0.7672   0.1672
  -3.000   0.1701   0.02446   0.01590  -0.1229   0.7605   0.1997
  -2.750   0.2000   0.02415   0.01568  -0.1228   0.7559   0.2443
  -2.500   0.2238   0.02460   0.01618  -0.1226   0.7478   0.2707
  -2.250   0.2508   0.02476   0.01634  -0.1223   0.7411   0.2925
  -2.000   0.2805   0.02468   0.01623  -0.1220   0.7365   0.3129
  -1.750   0.3049   0.02499   0.01656  -0.1217   0.7291   0.3276
  -1.500   0.3315   0.02510   0.01663  -0.1215   0.7222   0.3436
  -1.250   0.3618   0.02486   0.01633  -0.1212   0.7175   0.3614
  -1.000   0.3869   0.02501   0.01658  -0.1208   0.7109   0.3783
  -0.750   0.4123   0.02511   0.01675  -0.1205   0.7034   0.3961
  -0.500   0.4423   0.02475   0.01642  -0.1202   0.6987   0.4190
  -0.250   0.4699   0.02472   0.01643  -0.1198   0.6933   0.4466
   0.000   0.4924   0.02503   0.01695  -0.1192   0.6849   0.4744
   0.250   0.5217   0.02476   0.01674  -0.1187   0.6800   0.5114
   0.500   0.5526   0.02433   0.01637  -0.1180   0.6765   0.5502
   0.750   0.5702   0.02507   0.01734  -0.1172   0.6663   0.5845
   1.000   0.5980   0.02471   0.01710  -0.1163   0.6612   0.6300
   1.250   0.6265   0.02415   0.01667  -0.1150   0.6575   0.6821
   1.500   0.6398   0.02492   0.01775  -0.1130   0.6477   0.7374
   1.750   0.6580   0.02457   0.01760  -0.1098   0.6423   0.8193
   2.000   0.6890   0.02379   0.01688  -0.1085   0.6383   1.0000
   2.250   0.7115   0.02489   0.01790  -0.1092   0.6282   1.0000
   2.500   0.7446   0.02488   0.01770  -0.1098   0.6224   1.0000
   2.750   0.7807   0.02464   0.01725  -0.1104   0.6183   1.0000
   3.000   0.7977   0.02586   0.01850  -0.1099   0.6076   1.0000
   3.250   0.8298   0.02580   0.01830  -0.1100   0.6019   1.0000
   3.500   0.8659   0.02555   0.01787  -0.1104   0.5978   1.0000
   3.750   0.8798   0.02691   0.01932  -0.1095   0.5865   1.0000
   4.000   0.9129   0.02674   0.01903  -0.1096   0.5810   1.0000
   4.250   0.9368   0.02738   0.01965  -0.1092   0.5735   1.0000
   4.500   0.9601   0.02797   0.02023  -0.1087   0.5650   1.0000
   4.750   0.9951   0.02768   0.01981  -0.1089   0.5601   1.0000
   5.000   1.0109   0.02886   0.02107  -0.1079   0.5504   1.0000
   5.250   1.0398   0.02897   0.02113  -0.1077   0.5437   1.0000
   5.500   1.0770   0.02859   0.02060  -0.1081   0.5393   1.0000
   5.750   1.0868   0.03007   0.02224  -0.1066   0.5283   1.0000
   6.000   1.1219   0.02959   0.02165  -0.1067   0.5224   1.0000
   6.250   1.1419   0.03026   0.02236  -0.1057   0.5136   1.0000
   6.500   1.1702   0.03009   0.02215  -0.1053   0.5054   1.0000
   6.750   1.2052   0.02950   0.02143  -0.1053   0.4986   1.0000
   7.000   1.2217   0.03012   0.02215  -0.1039   0.4882   1.0000
   7.250   1.2618   0.02924   0.02107  -0.1045   0.4825   1.0000
   7.500   1.2712   0.03038   0.02240  -0.1026   0.4721   1.0000
   7.750   1.3068   0.02974   0.02163  -0.1028   0.4654   1.0000
   8.000   1.3216   0.03055   0.02255  -0.1013   0.4564   1.0000
   8.250   1.3496   0.03043   0.02239  -0.1008   0.4490   1.0000
   8.500   1.3738   0.03063   0.02259  -0.1001   0.4414   1.0000
   8.750   1.3925   0.03097   0.02299  -0.0988   0.4325   1.0000
   9.000   1.4239   0.03068   0.02260  -0.0988   0.4253   1.0000
   9.250   1.4333   0.03165   0.02375  -0.0967   0.4166   1.0000
   9.500   1.4700   0.03108   0.02301  -0.0971   0.4098   1.0000
   9.750   1.4724   0.03230   0.02445  -0.0943   0.4007   1.0000
  10.000   1.5039   0.03194   0.02398  -0.0942   0.3930   1.0000
  10.250   1.5078   0.03303   0.02524  -0.0915   0.3845   1.0000
  10.500   1.5341   0.03279   0.02490  -0.0908   0.3756   1.0000
  10.750   1.5326   0.03391   0.02617  -0.0874   0.3668   1.0000
  11.000   1.5562   0.03369   0.02583  -0.0863   0.3570   1.0000
  11.250   1.5470   0.03537   0.02772  -0.0827   0.3485   1.0000
  11.500   1.5684   0.03538   0.02760  -0.0816   0.3391   1.0000
  11.750   1.5553   0.03757   0.03002  -0.0783   0.3302   1.0000
  12.000   1.5658   0.03827   0.03068  -0.0767   0.3203   1.0000
  12.250   1.5558   0.04058   0.03315  -0.0743   0.3101   1.0000
  12.500   1.5519   0.04258   0.03522  -0.0724   0.2990   1.0000
  12.750   1.5487   0.04455   0.03718  -0.0707   0.2864   1.0000
  13.000   1.5353   0.04769   0.04041  -0.0692   0.2727   1.0000
  13.250   1.5184   0.05147   0.04426  -0.0680   0.2572   1.0000
  13.500   1.5013   0.05548   0.04824  -0.0672   0.2394   1.0000
  13.750   1.4793   0.06049   0.05325  -0.0668   0.2197   1.0000
  14.000   1.4600   0.06546   0.05812  -0.0666   0.2001   1.0000
  14.250   1.4457   0.06994   0.06245  -0.0664   0.1841   1.0000
  14.500   1.4372   0.07383   0.06622  -0.0661   0.1720   1.0000
  14.750   1.4349   0.07689   0.06911  -0.0656   0.1633   1.0000
  15.000   1.4348   0.07982   0.07203  -0.0653   0.1562   1.0000
  15.250   1.4420   0.08162   0.07370  -0.0645   0.1508   1.0000
  15.500   1.4477   0.08389   0.07601  -0.0640   0.1462   1.0000
  15.750   1.4584   0.08533   0.07739  -0.0631   0.1425   1.0000
  16.000   1.4772   0.08558   0.07750  -0.0617   0.1392   1.0000
  16.250   1.4839   0.08781   0.07987  -0.0613   0.1368   1.0000
  16.500   1.4935   0.08962   0.08175  -0.0607   0.1344   1.0000
  16.750   1.5060   0.09102   0.08318  -0.0600   0.1322   1.0000
  17.000   1.5242   0.09159   0.08370  -0.0589   0.1301   1.0000
  17.250   1.5532   0.09082   0.08278  -0.0571   0.1279   1.0000
  17.500   1.5520   0.09424   0.08642  -0.0574   0.1267   1.0000
  17.750   1.5510   0.09767   0.09005  -0.0577   0.1255   1.0000
  18.000   1.5492   0.10126   0.09384  -0.0582   0.1245   1.0000
  18.250   1.5450   0.10526   0.09804  -0.0589   0.1236   1.0000
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