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GOE 624 AIRFOIL (goe624-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 624 AIRFOIL (goe624-il)
Reynolds number: 100,000
Max Cl/Cd: 39.85 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe624-il-100000.txt
Download as CSV file: xf-goe624-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 624 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3002   0.12481   0.12031  -0.0303   1.0000   0.1181
  -9.750  -0.2876   0.12109   0.11658  -0.0351   0.9957   0.1226
  -9.500  -0.3231   0.11839   0.11396  -0.0506   0.9851   0.1263
  -9.250  -0.2683   0.11188   0.10737  -0.0474   0.9846   0.1283
  -9.000  -0.2361   0.10782   0.10327  -0.0503   0.9813   0.1316
  -8.750  -0.2211   0.10415   0.09960  -0.0548   0.9739   0.1368
  -8.500  -0.2642   0.10034   0.09587  -0.0700   0.9579   0.1415
  -8.250  -0.1943   0.09559   0.09104  -0.0653   0.9605   0.1453
  -8.000  -0.1684   0.09176   0.08718  -0.0703   0.9556   0.1521
  -7.750  -0.1967   0.08661   0.08206  -0.0832   0.9394   0.1582
  -7.500  -0.1422   0.08304   0.07845  -0.0814   0.9392   0.1619
  -7.250  -0.1295   0.08019   0.07559  -0.0832   0.9279   0.1672
  -7.000  -0.1528   0.07522   0.07056  -0.0929   0.9116   0.1756
  -6.750  -0.1154   0.07225   0.06760  -0.0922   0.9074   0.1792
  -6.500  -0.1846   0.05250   0.04638  -0.1068   0.8888   0.1124
  -6.250  -0.1627   0.04989   0.04392  -0.1069   0.8809   0.1140
  -6.000  -0.1447   0.04597   0.03964  -0.1074   0.8728   0.1098
  -5.750  -0.1178   0.04163   0.03486  -0.1092   0.8684   0.1074
  -5.500  -0.1095   0.03926   0.03212  -0.1071   0.8568   0.1064
  -5.250  -0.0795   0.03623   0.02858  -0.1080   0.8519   0.1070
  -5.000  -0.0621   0.03475   0.02670  -0.1066   0.8423   0.1095
  -4.750  -0.0332   0.03280   0.02425  -0.1067   0.8359   0.1132
  -4.500   0.0019   0.03119   0.02260  -0.1077   0.8318   0.1179
  -4.250   0.0189   0.03054   0.02176  -0.1059   0.8205   0.1224
  -4.000   0.0519   0.02912   0.02017  -0.1063   0.8155   0.1308
  -3.750   0.0742   0.02867   0.01953  -0.1052   0.8062   0.1403
  -3.500   0.1036   0.02766   0.01855  -0.1051   0.7994   0.1523
  -3.250   0.1378   0.02664   0.01749  -0.1055   0.7951   0.1677
  -3.000   0.1565   0.02646   0.01733  -0.1041   0.7835   0.1802
  -2.750   0.1890   0.02569   0.01654  -0.1042   0.7783   0.1976
  -2.500   0.2103   0.02558   0.01643  -0.1032   0.7679   0.2127
  -2.250   0.2412   0.02488   0.01572  -0.1030   0.7617   0.2302
  -2.000   0.2659   0.02453   0.01543  -0.1022   0.7529   0.2479
  -1.750   0.2936   0.02387   0.01492  -0.1017   0.7452   0.2717
  -1.500   0.3232   0.02304   0.01429  -0.1013   0.7394   0.3138
  -1.250   0.3431   0.02249   0.01427  -0.1000   0.7289   0.4004
  -1.000   0.3622   0.02078   0.01401  -0.0963   0.7241   0.7420
  -0.750   0.4631   0.02051   0.01381  -0.1082   0.7142   1.0000
  -0.500   0.4888   0.02031   0.01334  -0.1074   0.7074   1.0000
  -0.250   0.5062   0.02064   0.01352  -0.1058   0.6971   1.0000
   0.000   0.5325   0.02053   0.01320  -0.1051   0.6904   1.0000
   0.250   0.5514   0.02089   0.01343  -0.1037   0.6809   1.0000
   0.500   0.5773   0.02088   0.01323  -0.1030   0.6736   1.0000
   0.750   0.5993   0.02115   0.01338  -0.1019   0.6653   1.0000
   1.000   0.6233   0.02131   0.01340  -0.1011   0.6573   1.0000
   1.250   0.6528   0.02129   0.01319  -0.1010   0.6520   1.0000
   1.500   0.6696   0.02194   0.01382  -0.0995   0.6419   1.0000
   1.750   0.7002   0.02188   0.01357  -0.0995   0.6365   1.0000
   2.000   0.7179   0.02256   0.01424  -0.0982   0.6274   1.0000
   2.250   0.7452   0.02272   0.01428  -0.0979   0.6212   1.0000
   2.500   0.7732   0.02293   0.01437  -0.0978   0.6158   1.0000
   2.750   0.7903   0.02368   0.01515  -0.0964   0.6071   1.0000
   3.000   0.8208   0.02372   0.01505  -0.0966   0.6020   1.0000
   3.250   0.8405   0.02445   0.01578  -0.0956   0.5950   1.0000
   3.500   0.8628   0.02497   0.01628  -0.0949   0.5882   1.0000
   3.750   0.8950   0.02496   0.01615  -0.0953   0.5837   1.0000
   4.000   0.9098   0.02597   0.01723  -0.0938   0.5761   1.0000
   4.250   0.9338   0.02641   0.01764  -0.0933   0.5700   1.0000
   4.500   0.9674   0.02635   0.01747  -0.0939   0.5659   1.0000
   4.750   0.9781   0.02760   0.01883  -0.0919   0.5580   1.0000
   5.000   1.0035   0.02796   0.01916  -0.0916   0.5522   1.0000
   5.250   1.0396   0.02774   0.01883  -0.0924   0.5482   1.0000
   5.500   1.0454   0.02922   0.02047  -0.0899   0.5397   1.0000
   5.750   1.0750   0.02923   0.02042  -0.0900   0.5341   1.0000
   6.000   1.1071   0.02918   0.02029  -0.0903   0.5288   1.0000
   6.250   1.1158   0.03033   0.02158  -0.0880   0.5203   1.0000
   6.500   1.1532   0.02988   0.02101  -0.0890   0.5152   1.0000
   6.750   1.1645   0.03099   0.02224  -0.0870   0.5078   1.0000
   7.000   1.1876   0.03134   0.02261  -0.0864   0.5013   1.0000
   7.250   1.2289   0.03084   0.02198  -0.0879   0.4970   1.0000
   7.500   1.2266   0.03265   0.02401  -0.0844   0.4886   1.0000
   7.750   1.2578   0.03259   0.02393  -0.0847   0.4830   1.0000
   8.000   1.2866   0.03279   0.02411  -0.0847   0.4774   1.0000
   8.250   1.2900   0.03417   0.02565  -0.0818   0.4692   1.0000
   8.500   1.3335   0.03352   0.02490  -0.0836   0.4641   1.0000
   8.750   1.3316   0.03525   0.02681  -0.0801   0.4561   1.0000
   9.000   1.3581   0.03546   0.02704  -0.0799   0.4497   1.0000
   9.250   1.3940   0.03535   0.02688  -0.0808   0.4439   1.0000
   9.500   1.3851   0.03722   0.02895  -0.0765   0.4353   1.0000
   9.750   1.4390   0.03614   0.02773  -0.0795   0.4294   1.0000
  10.000   1.4179   0.03857   0.03042  -0.0738   0.4207   1.0000
  10.250   1.4594   0.03804   0.02982  -0.0752   0.4141   1.0000
  10.500   1.4576   0.03966   0.03159  -0.0719   0.4066   1.0000
  10.750   1.4680   0.04049   0.03248  -0.0697   0.3992   1.0000
  11.000   1.5042   0.04032   0.03229  -0.0707   0.3920   1.0000
  11.250   1.4717   0.04300   0.03517  -0.0639   0.3842   1.0000
  11.500   1.5409   0.04096   0.03296  -0.0681   0.3763   1.0000
  11.750   1.4807   0.04531   0.03761  -0.0593   0.3689   1.0000
  12.000   1.5723   0.04170   0.03374  -0.0650   0.3606   1.0000
  12.250   1.4909   0.04764   0.04007  -0.0554   0.3539   1.0000
  12.500   1.5710   0.04399   0.03621  -0.0590   0.3459   1.0000
  12.750   1.3687   0.06263   0.05539  -0.0479   0.3369   1.0000
  13.000   1.5255   0.04998   0.04253  -0.0513   0.3324   1.0000
  13.250   1.5446   0.05048   0.04306  -0.0506   0.3261   1.0000
  13.500   1.3759   0.06896   0.06191  -0.0453   0.3165   1.0000
  13.750   1.5974   0.05023   0.04278  -0.0499   0.3127   1.0000
  14.250   1.4164   0.07179   0.06492  -0.0432   0.2995   1.0000
  14.500   0.9838   0.14731   0.14041  -0.0657   0.2593   1.0000
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