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GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 450 AIRFOIL (goe450-il)
Reynolds number: 100,000
Max Cl/Cd: 64.36 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe450-il-100000-n5.txt
Download as CSV file: xf-goe450-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 450 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3202   0.10578   0.10100  -0.0328   1.0000   0.0486
  -8.250  -0.3274   0.10422   0.09950  -0.0310   1.0000   0.0500
  -8.000  -0.3373   0.10285   0.09822  -0.0290   1.0000   0.0512
  -7.750  -0.3303   0.10007   0.09545  -0.0363   0.9923   0.0537
  -7.500  -0.3087   0.09572   0.09109  -0.0511   0.9818   0.0545
  -7.250  -0.2938   0.09048   0.08586  -0.0527   0.9778   0.0552
  -7.000  -0.2771   0.08671   0.08207  -0.0507   0.9756   0.0570
  -6.750  -0.2597   0.08349   0.07884  -0.0531   0.9696   0.0606
  -6.500  -0.2182   0.07865   0.07378  -0.0759   0.9576   0.0665
  -6.250  -0.2065   0.07377   0.06896  -0.0744   0.9536   0.0676
  -6.000  -0.1861   0.07020   0.06538  -0.0750   0.9503   0.0694
  -5.750  -0.1662   0.06695   0.06209  -0.0775   0.9433   0.0717
  -5.500  -0.1120   0.06156   0.05621  -0.0958   0.9357   0.0804
  -5.000  -0.0566   0.04861   0.04280  -0.1035   0.9238   0.0544
  -4.750  -0.0281   0.04533   0.03948  -0.1060   0.9202   0.0527
  -4.500   0.0026   0.04136   0.03517  -0.1095   0.9135   0.0531
  -4.250   0.0342   0.03785   0.03134  -0.1124   0.9077   0.0525
  -4.000   0.0705   0.03438   0.02750  -0.1157   0.9042   0.0512
  -3.750   0.0986   0.03165   0.02438  -0.1168   0.8967   0.0505
  -3.500   0.1325   0.02916   0.02143  -0.1187   0.8917   0.0507
  -3.250   0.1694   0.02708   0.01887  -0.1207   0.8883   0.0524
  -3.000   0.1954   0.02560   0.01705  -0.1206   0.8797   0.0524
  -2.750   0.2298   0.02403   0.01513  -0.1218   0.8751   0.0524
  -2.500   0.2588   0.02287   0.01368  -0.1220   0.8680   0.0526
  -2.250   0.2902   0.02179   0.01237  -0.1224   0.8618   0.0530
  -2.000   0.3217   0.02087   0.01125  -0.1229   0.8560   0.0536
  -1.500   0.3811   0.01941   0.00969  -0.1234   0.8421   0.0580
  -1.250   0.4081   0.01888   0.00913  -0.1230   0.8331   0.0595
  -1.000   0.4377   0.01832   0.00852  -0.1231   0.8258   0.0610
  -0.750   0.4659   0.01787   0.00803  -0.1229   0.8171   0.0630
  -0.500   0.4941   0.01752   0.00761  -0.1227   0.8083   0.0655
  -0.250   0.5239   0.01712   0.00717  -0.1228   0.8004   0.0696
   0.000   0.5506   0.01690   0.00693  -0.1224   0.7903   0.0778
   0.500   0.6077   0.01540   0.00663  -0.1228   0.7725   0.4917
   1.000   0.6638   0.01433   0.00627  -0.1217   0.7543   1.0000
   1.250   0.6902   0.01445   0.00626  -0.1212   0.7435   1.0000
   1.500   0.7182   0.01451   0.00620  -0.1210   0.7341   1.0000
   1.750   0.7461   0.01459   0.00617  -0.1208   0.7244   1.0000
   2.000   0.7725   0.01474   0.00625  -0.1205   0.7139   1.0000
   2.250   0.8002   0.01485   0.00627  -0.1203   0.7044   1.0000
   2.500   0.8273   0.01499   0.00635  -0.1200   0.6942   1.0000
   2.750   0.8534   0.01517   0.00650  -0.1196   0.6836   1.0000
   3.000   0.8806   0.01532   0.00660  -0.1193   0.6738   1.0000
   3.250   0.9073   0.01550   0.00675  -0.1190   0.6635   1.0000
   3.500   0.9330   0.01572   0.00698  -0.1185   0.6524   1.0000
   3.750   0.9593   0.01593   0.00717  -0.1181   0.6419   1.0000
   4.000   0.9859   0.01612   0.00733  -0.1177   0.6311   1.0000
   4.250   1.0106   0.01637   0.00763  -0.1171   0.6184   1.0000
   4.500   1.0355   0.01663   0.00791  -0.1165   0.6057   1.0000
   4.750   1.0603   0.01688   0.00818  -0.1159   0.5926   1.0000
   5.000   1.0849   0.01714   0.00849  -0.1152   0.5794   1.0000
   5.250   1.1090   0.01741   0.00879  -0.1144   0.5652   1.0000
   5.500   1.1323   0.01769   0.00911  -0.1135   0.5495   1.0000
   5.750   1.1544   0.01797   0.00944  -0.1123   0.5303   1.0000
   6.000   1.1753   0.01826   0.00967  -0.1109   0.5077   1.0000
   6.250   1.1946   0.01861   0.01000  -0.1093   0.4809   1.0000
   6.500   1.2137   0.01903   0.01037  -0.1077   0.4550   1.0000
   6.750   1.2337   0.01948   0.01084  -0.1063   0.4346   1.0000
   7.000   1.2533   0.01997   0.01136  -0.1049   0.4147   1.0000
   7.250   1.2711   0.02053   0.01192  -0.1032   0.3906   1.0000
   7.500   1.2862   0.02120   0.01253  -0.1011   0.3600   1.0000
   7.750   1.2989   0.02201   0.01323  -0.0988   0.3245   1.0000
   8.000   1.3087   0.02298   0.01407  -0.0960   0.2785   1.0000
   8.250   1.3147   0.02422   0.01505  -0.0929   0.2213   1.0000
   8.500   1.3133   0.02588   0.01633  -0.0888   0.1714   1.0000
   8.750   1.3150   0.02757   0.01781  -0.0854   0.1287   1.0000
   9.000   1.3137   0.02954   0.01948  -0.0819   0.0901   1.0000
   9.250   1.3146   0.03139   0.02123  -0.0788   0.0749   1.0000
   9.500   1.3186   0.03305   0.02297  -0.0761   0.0656   1.0000
   9.750   1.3213   0.03484   0.02483  -0.0735   0.0591   1.0000
  10.000   1.3260   0.03653   0.02664  -0.0713   0.0539   1.0000
  10.250   1.3273   0.03854   0.02870  -0.0690   0.0505   1.0000
  10.500   1.3298   0.04053   0.03082  -0.0670   0.0477   1.0000
  10.750   1.3320   0.04261   0.03303  -0.0651   0.0449   1.0000
  11.000   1.3323   0.04493   0.03543  -0.0634   0.0425   1.0000
  11.250   1.3293   0.04764   0.03820  -0.0615   0.0408   1.0000
  11.500   1.3313   0.04998   0.04068  -0.0599   0.0393   1.0000
  11.750   1.3341   0.05230   0.04319  -0.0585   0.0374   1.0000
  12.000   1.3365   0.05471   0.04571  -0.0572   0.0355   1.0000
  12.250   1.3386   0.05719   0.04826  -0.0560   0.0338   1.0000
  12.500   1.3417   0.05967   0.05076  -0.0545   0.0325   1.0000
  12.750   1.3491   0.06190   0.05306  -0.0529   0.0312   1.0000
  13.000   1.3551   0.06424   0.05564  -0.0518   0.0299   1.0000
  13.250   1.3594   0.06681   0.05842  -0.0508   0.0284   1.0000
  13.500   1.3628   0.06951   0.06133  -0.0499   0.0272   1.0000
  13.750   1.3661   0.07230   0.06428  -0.0491   0.0262   1.0000
  14.000   1.3688   0.07522   0.06734  -0.0483   0.0255   1.0000
  14.250   1.3712   0.07827   0.07051  -0.0476   0.0247   1.0000
  14.500   1.3747   0.08166   0.07397  -0.0467   0.0239   1.0000
  14.750   1.3659   0.08588   0.07851  -0.0470   0.0235   1.0000
  15.000   1.3555   0.09052   0.08347  -0.0476   0.0231   1.0000
  15.250   1.3440   0.09556   0.08881  -0.0487   0.0227   1.0000
  15.500   1.3313   0.10099   0.09453  -0.0504   0.0223   1.0000
  15.750   1.3175   0.10685   0.10066  -0.0525   0.0220   1.0000
  16.000   1.3025   0.11321   0.10727  -0.0553   0.0218   1.0000
  16.250   1.2864   0.12014   0.11446  -0.0587   0.0217   1.0000
  16.500   1.2690   0.12778   0.12233  -0.0630   0.0216   1.0000
  16.750   1.2502   0.13627   0.13105  -0.0682   0.0217   1.0000
  17.000   1.2298   0.14580   0.14079  -0.0744   0.0219   1.0000
  17.250   1.2076   0.15667   0.15184  -0.0818   0.0222   1.0000
  17.500   1.1840   0.16918   0.16449  -0.0903   0.0226   1.0000
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