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GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il)
Reynolds number: 100,000
Max Cl/Cd: 59.03 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe144-il-100000.txt
Download as CSV file: xf-goe144-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 144 (MVA H.21) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3472   0.10628   0.10150  -0.0268   1.0000   0.0801
  -8.000  -0.3614   0.10601   0.10136  -0.0274   1.0000   0.0804
  -7.750  -0.3675   0.10487   0.10032  -0.0311   1.0000   0.0806
  -7.500  -0.3330   0.09499   0.09034  -0.0239   1.0000   0.0836
  -7.250  -0.3321   0.09255   0.08796  -0.0225   1.0000   0.0853
  -7.000  -0.3356   0.09051   0.08600  -0.0211   1.0000   0.0872
  -6.750  -0.3383   0.08832   0.08389  -0.0208   1.0000   0.0895
  -6.500  -0.3418   0.08638   0.08202  -0.0219   1.0000   0.0919
  -6.250  -0.3438   0.08560   0.08126  -0.0313   1.0000   0.0939
  -6.000  -0.3411   0.08133   0.07706  -0.0294   1.0000   0.0948
  -5.750  -0.3379   0.07795   0.07374  -0.0238   1.0000   0.0968
  -5.500  -0.3328   0.07553   0.07135  -0.0224   1.0000   0.1011
  -5.250  -0.3131   0.07280   0.06848  -0.0349   1.0000   0.1074
  -5.000  -0.3133   0.06917   0.06497  -0.0293   1.0000   0.1089
  -4.750  -0.3070   0.06651   0.06234  -0.0272   1.0000   0.1117
  -4.250  -0.2736   0.06005   0.05575  -0.0341   1.0000   0.1222
  -4.000  -0.2663   0.05771   0.05343  -0.0321   1.0000   0.1259
  -3.750  -0.2425   0.05469   0.05025  -0.0370   1.0000   0.1359
  -3.500  -0.2357   0.05260   0.04822  -0.0350   1.0000   0.1402
  -3.250  -0.1809   0.04810   0.04346  -0.0445   0.9926   0.1518
  -3.000  -0.1021   0.03687   0.03089  -0.0594   0.9880   0.1071
  -2.750  -0.0578   0.03295   0.02682  -0.0640   0.9806   0.1038
  -2.500  -0.0065   0.02796   0.02085  -0.0693   0.9739   0.1064
  -2.250   0.0385   0.02610   0.01879  -0.0731   0.9637   0.1127
  -2.000   0.0864   0.02407   0.01630  -0.0769   0.9546   0.1248
  -1.750   0.1349   0.02295   0.01481  -0.0807   0.9448   0.1500
  -1.500   0.1784   0.02216   0.01394  -0.0837   0.9324   0.1696
  -1.250   0.2218   0.02186   0.01364  -0.0868   0.9200   0.1958
  -1.000   0.2674   0.02096   0.01250  -0.0899   0.9090   0.2077
  -0.750   0.3204   0.01998   0.01136  -0.0942   0.9019   0.2185
  -0.500   0.3622   0.01915   0.01052  -0.0964   0.8890   0.2294
  -0.250   0.4030   0.01835   0.00966  -0.0983   0.8754   0.2425
   0.000   0.4416   0.01765   0.00893  -0.0997   0.8610   0.2609
   0.250   0.4783   0.01696   0.00830  -0.1008   0.8456   0.2817
   0.500   0.5125   0.01638   0.00774  -0.1013   0.8298   0.3040
   0.750   0.5437   0.01588   0.00731  -0.1014   0.8121   0.3291
   1.000   0.5739   0.01539   0.00693  -0.1013   0.7941   0.3647
   1.250   0.6173   0.01356   0.00652  -0.1036   0.7761   1.0000
   1.500   0.6483   0.01358   0.00618  -0.1032   0.7577   1.0000
   1.750   0.6750   0.01377   0.00615  -0.1023   0.7379   1.0000
   2.000   0.7022   0.01401   0.00620  -0.1017   0.7203   1.0000
   2.250   0.7289   0.01431   0.00636  -0.1011   0.7040   1.0000
   2.500   0.7551   0.01465   0.00657  -0.1004   0.6885   1.0000
   2.750   0.7808   0.01501   0.00683  -0.0997   0.6735   1.0000
   3.000   0.8061   0.01537   0.00712  -0.0990   0.6589   1.0000
   3.250   0.8311   0.01574   0.00746  -0.0982   0.6445   1.0000
   3.500   0.8559   0.01610   0.00778  -0.0973   0.6302   1.0000
   3.750   0.8806   0.01646   0.00812  -0.0965   0.6159   1.0000
   4.000   0.9050   0.01681   0.00844  -0.0956   0.6012   1.0000
   4.250   0.9293   0.01712   0.00875  -0.0945   0.5855   1.0000
   4.500   0.9535   0.01739   0.00899  -0.0934   0.5691   1.0000
   4.750   0.9774   0.01765   0.00920  -0.0923   0.5520   1.0000
   5.000   1.0000   0.01795   0.00954  -0.0910   0.5341   1.0000
   5.250   1.0229   0.01823   0.00988  -0.0898   0.5163   1.0000
   5.500   1.0460   0.01851   0.01017  -0.0886   0.4985   1.0000
   5.750   1.0692   0.01881   0.01047  -0.0874   0.4812   1.0000
   6.000   1.0916   0.01910   0.01080  -0.0861   0.4629   1.0000
   6.250   1.1119   0.01928   0.01106  -0.0844   0.4404   1.0000
   6.500   1.1306   0.01934   0.01114  -0.0824   0.4141   1.0000
   6.750   1.1493   0.01951   0.01132  -0.0805   0.3883   1.0000
   7.000   1.1683   0.01979   0.01162  -0.0787   0.3639   1.0000
   7.250   1.1857   0.02011   0.01195  -0.0768   0.3344   1.0000
   7.500   1.2028   0.02054   0.01243  -0.0748   0.3023   1.0000
   7.750   1.2177   0.02118   0.01294  -0.0727   0.2642   1.0000
   8.000   1.2334   0.02197   0.01366  -0.0707   0.2271   1.0000
   8.250   1.2449   0.02317   0.01460  -0.0682   0.1638   1.0000
   8.500   1.2474   0.02535   0.01614  -0.0649   0.0958   1.0000
   8.750   1.2540   0.02719   0.01779  -0.0619   0.0643   1.0000
   9.000   1.2624   0.02874   0.01931  -0.0591   0.0542   1.0000
   9.250   1.2681   0.03033   0.02096  -0.0560   0.0501   1.0000
   9.500   1.2719   0.03182   0.02260  -0.0526   0.0477   1.0000
   9.750   1.2739   0.03343   0.02435  -0.0493   0.0460   1.0000
  10.000   1.2746   0.03521   0.02623  -0.0461   0.0445   1.0000
  10.250   1.2742   0.03722   0.02831  -0.0432   0.0431   1.0000
  10.500   1.2735   0.03963   0.03072  -0.0405   0.0415   1.0000
  10.750   1.2811   0.04157   0.03282  -0.0385   0.0403   1.0000
  11.000   1.2926   0.04367   0.03504  -0.0368   0.0393   1.0000
  11.250   1.3099   0.04599   0.03750  -0.0354   0.0388   1.0000
  11.500   1.3300   0.04870   0.04045  -0.0343   0.0385   1.0000
  11.750   1.3477   0.05187   0.04389  -0.0332   0.0386   1.0000
  12.000   1.3566   0.05544   0.04779  -0.0317   0.0389   1.0000
  12.250   1.3572   0.05915   0.05183  -0.0301   0.0393   1.0000
  12.500   1.3517   0.06306   0.05606  -0.0285   0.0397   1.0000
  12.750   1.3419   0.06717   0.06047  -0.0273   0.0400   1.0000
  13.000   1.3290   0.07158   0.06515  -0.0266   0.0403   1.0000
  13.250   1.3137   0.07636   0.07019  -0.0267   0.0405   1.0000
  13.500   1.2969   0.08151   0.07558  -0.0275   0.0408   1.0000
  13.750   1.2784   0.08713   0.08142  -0.0291   0.0410   1.0000
  14.000   1.2594   0.09333   0.08782  -0.0313   0.0413   1.0000
  14.250   1.2420   0.09993   0.09459  -0.0340   0.0416   1.0000
  14.500   1.2215   0.10647   0.10135  -0.0377   0.0419   1.0000
  14.750   1.1931   0.11454   0.10968  -0.0438   0.0425   1.0000
  15.000   1.1500   0.12745   0.12284  -0.0539   0.0433   1.0000
  15.250   1.0554   0.16175   0.15715  -0.0779   0.0475   1.0000
  15.500   1.0492   0.17006   0.16542  -0.0819   0.0494   1.0000
  15.750   1.0527   0.17477   0.17013  -0.0833   0.0507   1.0000
  16.000   1.0372   0.19059   0.18587  -0.0916   0.0631   1.0000
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