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GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 484 AIRFOIL (goe484-il)
Reynolds number: 100,000
Max Cl/Cd: 65.4 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe484-il-100000-n5.txt
Download as CSV file: xf-goe484-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 484 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3667   0.10203   0.09715  -0.0263   1.0000   0.0557
  -7.500  -0.3852   0.10199   0.09721  -0.0242   1.0000   0.0563
  -7.250  -0.3974   0.10134   0.09666  -0.0257   1.0000   0.0567
  -7.000  -0.3920   0.09894   0.09428  -0.0317   0.9984   0.0570
  -6.750  -0.3876   0.09384   0.08921  -0.0242   0.9983   0.0583
  -6.500  -0.3711   0.09024   0.08560  -0.0251   0.9954   0.0600
  -6.250  -0.3523   0.08672   0.08206  -0.0288   0.9912   0.0623
  -6.000  -0.3267   0.08286   0.07814  -0.0363   0.9862   0.0662
  -5.750  -0.2837   0.07732   0.07247  -0.0547   0.9781   0.0700
  -5.500  -0.2713   0.07402   0.06920  -0.0513   0.9739   0.0721
  -5.250  -0.2437   0.07037   0.06551  -0.0555   0.9684   0.0749
  -5.000  -0.2127   0.06650   0.06155  -0.0622   0.9618   0.0785
  -4.750  -0.1423   0.06045   0.05503  -0.0844   0.9566   0.0835
  -4.500  -0.1336   0.05700   0.05169  -0.0818   0.9513   0.0848
  -4.000  -0.0489   0.04455   0.03863  -0.0971   0.9448   0.0555
  -3.750  -0.0218   0.04140   0.03533  -0.0996   0.9390   0.0536
  -3.500   0.0178   0.03726   0.03087  -0.1047   0.9355   0.0514
  -3.000   0.0911   0.03072   0.02352  -0.1117   0.9276   0.0521
  -2.750   0.1272   0.02794   0.02027  -0.1142   0.9238   0.0515
  -2.500   0.1654   0.02551   0.01733  -0.1168   0.9210   0.0507
  -2.250   0.1986   0.02377   0.01516  -0.1180   0.9169   0.0505
  -2.000   0.2285   0.02252   0.01359  -0.1185   0.9113   0.0506
  -1.750   0.2639   0.02140   0.01221  -0.1199   0.9078   0.0511
  -1.500   0.3005   0.02045   0.01107  -0.1215   0.9048   0.0519
  -1.250   0.3253   0.01994   0.01047  -0.1209   0.8970   0.0539
  -1.000   0.3604   0.01933   0.00975  -0.1221   0.8931   0.0566
  -0.750   0.3966   0.01862   0.00903  -0.1236   0.8899   0.0582
  -0.500   0.4215   0.01825   0.00869  -0.1229   0.8814   0.0598
  -0.250   0.4576   0.01778   0.00822  -0.1243   0.8772   0.0625
   0.000   0.4867   0.01750   0.00792  -0.1244   0.8702   0.0663
   0.250   0.5184   0.01717   0.00765  -0.1249   0.8640   0.0739
   0.500   0.5566   0.01675   0.00738  -0.1266   0.8601   0.1101
   0.750   0.5829   0.01655   0.00741  -0.1262   0.8504   0.1899
   1.000   0.6186   0.01535   0.00742  -0.1280   0.8458   0.5793
   1.500   0.6825   0.01464   0.00715  -0.1287   0.8305   1.0000
   1.750   0.7092   0.01472   0.00718  -0.1283   0.8200   1.0000
   2.000   0.7439   0.01464   0.00706  -0.1292   0.8133   1.0000
   2.250   0.7699   0.01476   0.00718  -0.1286   0.8020   1.0000
   2.500   0.7982   0.01480   0.00722  -0.1283   0.7903   1.0000
   2.750   0.8269   0.01475   0.00717  -0.1280   0.7758   1.0000
   3.000   0.8562   0.01455   0.00694  -0.1274   0.7539   1.0000
   3.250   0.8804   0.01438   0.00669  -0.1257   0.7181   1.0000
   3.500   0.9080   0.01426   0.00637  -0.1246   0.6746   1.0000
   3.750   0.9354   0.01437   0.00625  -0.1236   0.6306   1.0000
   4.000   0.9601   0.01468   0.00640  -0.1225   0.5957   1.0000
   4.250   0.9823   0.01510   0.00665  -0.1210   0.5545   1.0000
   4.500   1.0015   0.01560   0.00697  -0.1190   0.4984   1.0000
   4.750   1.0122   0.01667   0.00734  -0.1156   0.3596   1.0000
   5.000   1.0172   0.01873   0.00833  -0.1121   0.1977   1.0000
   5.250   1.0249   0.02073   0.00948  -0.1091   0.0886   1.0000
   5.500   1.0429   0.02164   0.01034  -0.1074   0.0774   1.0000
   5.750   1.0614   0.02245   0.01121  -0.1057   0.0724   1.0000
   6.000   1.0796   0.02326   0.01214  -0.1040   0.0688   1.0000
   6.250   1.0964   0.02416   0.01313  -0.1022   0.0659   1.0000
   6.500   1.1109   0.02526   0.01427  -0.1000   0.0631   1.0000
   6.750   1.1258   0.02633   0.01541  -0.0979   0.0605   1.0000
   7.000   1.1424   0.02731   0.01652  -0.0961   0.0578   1.0000
   7.250   1.1588   0.02845   0.01775  -0.0942   0.0559   1.0000
   7.500   1.1765   0.02969   0.01904  -0.0927   0.0538   1.0000
   7.750   1.1951   0.03109   0.02041  -0.0914   0.0510   1.0000
   8.000   1.2192   0.03305   0.02235  -0.0911   0.0482   1.0000
   8.250   1.2432   0.03447   0.02399  -0.0904   0.0463   1.0000
   8.500   1.2655   0.03592   0.02563  -0.0896   0.0434   1.0000
   8.750   1.2869   0.03753   0.02738  -0.0888   0.0408   1.0000
   9.000   1.3100   0.03960   0.02952  -0.0884   0.0388   1.0000
   9.250   1.3323   0.04234   0.03244  -0.0880   0.0366   1.0000
   9.500   1.3467   0.04415   0.03469  -0.0860   0.0345   1.0000
   9.750   1.3615   0.04669   0.03761  -0.0842   0.0330   1.0000
  10.000   1.3729   0.04912   0.04035  -0.0822   0.0316   1.0000
  10.250   1.3824   0.05119   0.04261  -0.0802   0.0302   1.0000
  10.500   1.3900   0.05329   0.04483  -0.0782   0.0289   1.0000
  10.750   1.3930   0.05657   0.04833  -0.0759   0.0279   1.0000
  11.000   1.3848   0.05937   0.05159  -0.0716   0.0274   1.0000
  11.250   1.3740   0.06256   0.05516  -0.0676   0.0270   1.0000
  11.500   1.3602   0.06598   0.05895  -0.0640   0.0267   1.0000
  11.750   1.3441   0.06970   0.06300  -0.0609   0.0265   1.0000
  12.000   1.3262   0.07376   0.06737  -0.0586   0.0263   1.0000
  12.250   1.3064   0.07825   0.07214  -0.0572   0.0262   1.0000
  12.500   1.2856   0.08321   0.07736  -0.0567   0.0262   1.0000
  12.750   1.2632   0.08878   0.08317  -0.0573   0.0262   1.0000
  13.000   1.2403   0.09498   0.08959  -0.0590   0.0262   1.0000
  13.250   1.2169   0.10197   0.09678  -0.0620   0.0264   1.0000
  13.500   1.1931   0.10982   0.10480  -0.0663   0.0266   1.0000
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