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GOE 562 AIRFOIL (goe562-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 562 AIRFOIL (goe562-il)
Reynolds number: 100,000
Max Cl/Cd: 40.89 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe562-il-100000.txt
Download as CSV file: xf-goe562-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 562 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  -0.2195   0.12029   0.11605  -0.0382   1.0000   0.0656
  -9.750  -0.2267   0.11886   0.11476  -0.0372   1.0000   0.0668
  -9.500  -0.2482   0.11937   0.11549  -0.0339   0.9992   0.0676
  -9.250  -0.2369   0.11669   0.11283  -0.0487   0.9873   0.0696
  -9.000  -0.2113   0.10964   0.10578  -0.0534   0.9791   0.0709
  -8.750  -0.1719   0.10382   0.09990  -0.0542   0.9718   0.0759
  -8.500  -0.1510   0.09947   0.09554  -0.0605   0.9552   0.0800
  -8.250  -0.1466   0.09638   0.09246  -0.0718   0.9335   0.0833
  -8.000  -0.1443   0.09172   0.08776  -0.0838   0.9156   0.0844
  -7.750   0.0569   0.06539   0.06129  -0.1000   0.8825   0.1077
  -7.500   0.0532   0.06150   0.05730  -0.1111   0.8659   0.1136
  -7.250  -0.0522   0.07508   0.07088  -0.1015   0.8856   0.1003
  -7.000  -0.0048   0.07056   0.06628  -0.1042   0.8765   0.1095
  -6.750   0.0124   0.06580   0.06127  -0.1154   0.8583   0.1161
  -6.500   0.0521   0.06202   0.05740  -0.1183   0.8451   0.1244
  -6.250   0.0614   0.05868   0.05382  -0.1232   0.8283   0.1325
  -6.000   0.0883   0.05597   0.05099  -0.1246   0.8148   0.1414
  -5.750   0.0996   0.05336   0.04824  -0.1253   0.8015   0.1517
  -5.500   0.1013   0.05173   0.04639  -0.1246   0.7883   0.1642
  -5.000   0.1320   0.04769   0.04218  -0.1227   0.7672   0.1898
  -4.750   0.1395   0.04600   0.04042  -0.1205   0.7566   0.2038
  -4.500   0.1437   0.04493   0.03915  -0.1182   0.7475   0.2287
  -4.250   0.1589   0.04295   0.03717  -0.1164   0.7390   0.2474
  -4.000   0.1653   0.04198   0.03615  -0.1131   0.7302   0.2785
  -3.750   0.1784   0.04042   0.03460  -0.1104   0.7227   0.3122
  -3.500   0.1859   0.03915   0.03339  -0.1065   0.7146   0.3462
  -3.000   0.2035   0.03655   0.03085  -0.0985   0.7010   0.4275
  -2.750   0.2602   0.03141   0.02285  -0.1048   0.6949   0.1294
  -2.500   0.2877   0.02938   0.02060  -0.1046   0.6894   0.1238
  -2.250   0.3035   0.02924   0.01992  -0.1010   0.6818   0.1146
  -2.000   0.3307   0.02757   0.01807  -0.1008   0.6756   0.1113
  -1.750   0.3553   0.02672   0.01701  -0.0998   0.6697   0.1088
  -1.500   0.3766   0.02617   0.01630  -0.0983   0.6631   0.1073
  -1.250   0.4095   0.02551   0.01540  -0.0989   0.6580   0.1092
  -1.000   0.4282   0.02535   0.01519  -0.0970   0.6514   0.1110
  -0.750   0.4544   0.02499   0.01473  -0.0965   0.6453   0.1127
  -0.500   0.4898   0.02453   0.01414  -0.0976   0.6409   0.1146
  -0.250   0.5010   0.02450   0.01429  -0.0946   0.6344   0.1174
   0.000   0.5249   0.02434   0.01414  -0.0938   0.6289   0.1253
   0.250   0.5594   0.02405   0.01375  -0.0949   0.6247   0.1385
   0.500   0.5711   0.02441   0.01423  -0.0921   0.6179   0.1529
   0.750   0.7910   0.02210   0.01333  -0.1318   0.6082   1.0000
   1.000   0.7993   0.02266   0.01391  -0.1282   0.6004   1.0000
   1.250   0.8270   0.02273   0.01376  -0.1279   0.5940   1.0000
   1.500   0.8403   0.02317   0.01416  -0.1252   0.5863   1.0000
   1.750   0.8644   0.02329   0.01412  -0.1244   0.5795   1.0000
   2.000   0.8853   0.02362   0.01435  -0.1231   0.5736   1.0000
   2.250   0.8992   0.02414   0.01488  -0.1206   0.5672   1.0000
   2.500   0.9256   0.02433   0.01494  -0.1203   0.5624   1.0000
   2.750   0.9413   0.02488   0.01548  -0.1181   0.5569   1.0000
   3.000   0.9564   0.02538   0.01598  -0.1159   0.5506   1.0000
   3.250   0.9854   0.02547   0.01594  -0.1160   0.5459   1.0000
   3.500   0.9956   0.02617   0.01670  -0.1130   0.5397   1.0000
   3.750   1.0145   0.02650   0.01701  -0.1113   0.5336   1.0000
   4.000   1.0481   0.02645   0.01681  -0.1122   0.5291   1.0000
   4.250   1.0497   0.02737   0.01788  -0.1078   0.5218   1.0000
   4.500   1.0740   0.02753   0.01799  -0.1071   0.5164   1.0000
   4.750   1.0997   0.02774   0.01814  -0.1067   0.5114   1.0000
   5.000   1.1044   0.02855   0.01907  -0.1028   0.5041   1.0000
   5.250   1.1362   0.02845   0.01889  -0.1033   0.4991   1.0000
   5.500   1.1426   0.02925   0.01979  -0.0997   0.4921   1.0000
   5.750   1.1633   0.02947   0.02001  -0.0984   0.4858   1.0000
   6.000   1.1948   0.02946   0.01992  -0.0990   0.4807   1.0000
   6.250   1.1934   0.03042   0.02104  -0.0941   0.4726   1.0000
   6.500   1.2312   0.03011   0.02062  -0.0957   0.4674   1.0000
   6.750   1.2270   0.03121   0.02189  -0.0904   0.4593   1.0000
   7.000   1.2574   0.03110   0.02174  -0.0907   0.4533   1.0000
   7.250   1.2642   0.03187   0.02260  -0.0873   0.4462   1.0000
   7.500   1.2818   0.03221   0.02297  -0.0856   0.4395   1.0000
   7.750   1.3110   0.03231   0.02303  -0.0859   0.4340   1.0000
   8.000   1.3026   0.03358   0.02448  -0.0801   0.4265   1.0000
   8.250   1.3401   0.03344   0.02428  -0.0818   0.4217   1.0000
   8.500   1.3286   0.03502   0.02603  -0.0758   0.4153   1.0000
   8.750   1.3364   0.03594   0.02704  -0.0729   0.4099   1.0000
   9.000   1.3771   0.03585   0.02693  -0.0751   0.4061   1.0000
   9.250   1.3461   0.03819   0.02945  -0.0664   0.4009   1.0000
   9.500   1.3240   0.04014   0.03153  -0.0595   0.3959   1.0000
   9.750   1.3477   0.04072   0.03219  -0.0592   0.3927   1.0000
  10.000   1.4021   0.04054   0.03202  -0.0634   0.3901   1.0000
  10.250   1.1008   0.06394   0.05566  -0.0388   0.3743   1.0000
  10.500   1.1498   0.06131   0.05310  -0.0384   0.3747   1.0000
  11.500   1.4028   0.04633   0.03835  -0.0430   0.3604   1.0000
  11.750   0.7248   0.14072   0.13267  -0.0535   0.4079   1.0000
  12.000   0.7419   0.14323   0.13523  -0.0537   0.4067   1.0000
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