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GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 450 AIRFOIL (goe450-il)
Reynolds number: 50,000
Max Cl/Cd: 40.06 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe450-il-50000-n5.txt
Download as CSV file: xf-goe450-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3462   0.10697   0.10052  -0.0290   1.0000   0.1072
  -7.500  -0.3636   0.10656   0.10025  -0.0279   1.0000   0.1084
  -7.250  -0.3772   0.10582   0.09963  -0.0292   1.0000   0.1092
  -7.000  -0.3844   0.10416   0.09808  -0.0311   1.0000   0.1097
  -6.750  -0.3765   0.09924   0.09319  -0.0254   1.0000   0.1117
  -6.500  -0.3759   0.09658   0.09057  -0.0234   1.0000   0.1140
  -6.250  -0.3774   0.09434   0.08838  -0.0226   1.0000   0.1173
  -5.750  -0.3433   0.08689   0.08088  -0.0323   0.9895   0.1295
  -5.250  -0.2913   0.07876   0.07262  -0.0445   0.9757   0.1441
  -4.750  -0.2358   0.07116   0.06484  -0.0552   0.9621   0.1610
  -4.500  -0.2114   0.06791   0.06152  -0.0591   0.9539   0.1756
  -4.000  -0.1003   0.05263   0.04492  -0.0840   0.9413   0.0784
  -3.750  -0.0631   0.04902   0.04104  -0.0885   0.9360   0.0767
  -3.500  -0.0259   0.04576   0.03734  -0.0928   0.9297   0.0776
  -3.250   0.0105   0.04287   0.03403  -0.0962   0.9233   0.0774
  -3.000   0.0526   0.04005   0.03074  -0.1003   0.9191   0.0762
  -2.750   0.0840   0.03798   0.02824  -0.1019   0.9112   0.0756
  -2.500   0.1233   0.03596   0.02575  -0.1047   0.9060   0.0754
  -2.250   0.1596   0.03443   0.02377  -0.1067   0.8999   0.0770
  -2.000   0.1937   0.03327   0.02212  -0.1080   0.8927   0.0795
  -1.750   0.2343   0.03195   0.02049  -0.1104   0.8883   0.0809
  -1.500   0.2611   0.03114   0.01951  -0.1105   0.8792   0.0821
  -1.250   0.2995   0.03020   0.01838  -0.1123   0.8742   0.0842
  -1.000   0.3270   0.02970   0.01771  -0.1121   0.8651   0.0866
  -0.750   0.3657   0.02904   0.01683  -0.1138   0.8598   0.0911
  -0.500   0.3930   0.02871   0.01641  -0.1137   0.8504   0.0979
  -0.250   0.4310   0.02813   0.01573  -0.1153   0.8448   0.1088
   0.000   0.4576   0.02783   0.01545  -0.1152   0.8349   0.1209
   0.250   0.4963   0.02694   0.01491  -0.1170   0.8295   0.1805
   0.500   0.5152   0.02497   0.01490  -0.1151   0.8193   1.0000
   0.750   0.5488   0.02500   0.01457  -0.1157   0.8121   1.0000
   1.000   0.5756   0.02520   0.01454  -0.1154   0.8021   1.0000
   1.250   0.6024   0.02541   0.01457  -0.1151   0.7922   1.0000
   1.500   0.6359   0.02536   0.01437  -0.1156   0.7850   1.0000
   1.750   0.6597   0.02566   0.01456  -0.1149   0.7739   1.0000
   2.000   0.6907   0.02569   0.01448  -0.1151   0.7658   1.0000
   2.250   0.7182   0.02583   0.01456  -0.1148   0.7561   1.0000
   2.500   0.7433   0.02609   0.01477  -0.1142   0.7455   1.0000
   2.750   0.7772   0.02596   0.01459  -0.1147   0.7385   1.0000
   3.000   0.7998   0.02633   0.01497  -0.1138   0.7268   1.0000
   3.250   0.8262   0.02655   0.01518  -0.1133   0.7168   1.0000
   3.500   0.8578   0.02651   0.01514  -0.1135   0.7087   1.0000
   3.750   0.8807   0.02691   0.01559  -0.1126   0.6970   1.0000
   4.000   0.9075   0.02713   0.01585  -0.1122   0.6871   1.0000
   4.250   0.9379   0.02716   0.01593  -0.1122   0.6782   1.0000
   4.500   0.9604   0.02761   0.01648  -0.1112   0.6664   1.0000
   4.750   0.9862   0.02792   0.01687  -0.1107   0.6559   1.0000
   5.000   1.0172   0.02795   0.01698  -0.1107   0.6470   1.0000
   5.250   1.0385   0.02851   0.01765  -0.1097   0.6347   1.0000
   5.500   1.0621   0.02897   0.01826  -0.1089   0.6235   1.0000
   5.750   1.0911   0.02912   0.01852  -0.1086   0.6134   1.0000
   6.000   1.1163   0.02941   0.01894  -0.1079   0.6012   1.0000
   6.250   1.1377   0.02985   0.01956  -0.1066   0.5874   1.0000
   6.500   1.1599   0.03017   0.02003  -0.1053   0.5729   1.0000
   6.750   1.1820   0.03043   0.02042  -0.1039   0.5575   1.0000
   7.000   1.2032   0.03076   0.02092  -0.1025   0.5423   1.0000
   7.250   1.2238   0.03114   0.02150  -0.1010   0.5272   1.0000
   7.500   1.2458   0.03110   0.02156  -0.0992   0.5081   1.0000
   7.750   1.2562   0.03148   0.02206  -0.0960   0.4832   1.0000
   8.000   1.2676   0.03171   0.02231  -0.0928   0.4551   1.0000
   8.250   1.2770   0.03215   0.02280  -0.0895   0.4256   1.0000
   8.500   1.2831   0.03284   0.02348  -0.0860   0.3954   1.0000
   8.750   1.2862   0.03381   0.02444  -0.0823   0.3636   1.0000
   9.000   1.2886   0.03504   0.02567  -0.0790   0.3307   1.0000
   9.250   1.2887   0.03659   0.02718  -0.0757   0.2926   1.0000
   9.500   1.2850   0.03859   0.02905  -0.0726   0.2425   1.0000
   9.750   1.2754   0.04132   0.03138  -0.0694   0.1935   1.0000
  10.000   1.2645   0.04458   0.03431  -0.0667   0.1598   1.0000
  10.250   1.2562   0.04792   0.03752  -0.0646   0.1331   1.0000
  10.500   1.2496   0.05126   0.04083  -0.0628   0.1139   1.0000
  10.750   1.2439   0.05462   0.04414  -0.0613   0.1019   1.0000
  11.000   1.2392   0.05796   0.04744  -0.0601   0.0934   1.0000
  11.250   1.2345   0.06135   0.05081  -0.0590   0.0869   1.0000
  11.500   1.2340   0.06434   0.05388  -0.0578   0.0811   1.0000
  11.750   1.2351   0.06716   0.05679  -0.0566   0.0763   1.0000
  12.000   1.2361   0.06995   0.05953  -0.0553   0.0719   1.0000
  12.250   1.2427   0.07231   0.06218  -0.0541   0.0669   1.0000
  12.500   1.2496   0.07459   0.06458  -0.0528   0.0630   1.0000
  12.750   1.2606   0.07649   0.06653  -0.0512   0.0596   1.0000
  13.000   1.2693   0.07894   0.06933  -0.0501   0.0560   1.0000
  13.250   1.2762   0.08151   0.07209  -0.0492   0.0530   1.0000
  13.500   1.2889   0.08355   0.07418  -0.0478   0.0507   1.0000
  13.750   1.2943   0.08682   0.07772  -0.0470   0.0489   1.0000
  14.000   1.2908   0.09104   0.08231  -0.0471   0.0475   1.0000
  14.250   1.2845   0.09561   0.08718  -0.0476   0.0462   1.0000
  14.500   1.2762   0.10050   0.09235  -0.0485   0.0452   1.0000
  14.750   1.2660   0.10585   0.09796  -0.0500   0.0445   1.0000
  15.000   1.2534   0.11180   0.10417  -0.0521   0.0440   1.0000
  15.250   1.2377   0.11863   0.11125  -0.0552   0.0438   1.0000
  15.500   1.2183   0.12664   0.11950  -0.0595   0.0439   1.0000
  15.750   1.1928   0.13684   0.12995  -0.0658   0.0445   1.0000
  16.000   1.1625   0.14980   0.14311  -0.0745   0.0455   1.0000
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