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GOE 573 AIRFOIL (goe573-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 573 AIRFOIL (goe573-il)
Reynolds number: 100,000
Max Cl/Cd: 34.35 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe573-il-100000.txt
Download as CSV file: xf-goe573-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 573 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2060   0.12195   0.11773  -0.0398   1.0000   0.0636
 -10.000  -0.2166   0.12110   0.11705  -0.0374   1.0000   0.0644
  -9.750  -0.2180   0.11943   0.11548  -0.0389   0.9961   0.0665
  -9.500  -0.2014   0.11631   0.11237  -0.0502   0.9855   0.0688
  -9.250  -0.1960   0.11404   0.11012  -0.0631   0.9665   0.0695
  -9.000  -0.1490   0.10458   0.10061  -0.0591   0.9642   0.0731
  -8.750  -0.1248   0.10011   0.09613  -0.0640   0.9503   0.0768
  -8.500  -0.1069   0.09614   0.09214  -0.0713   0.9356   0.0811
  -8.250  -0.1065   0.09377   0.08973  -0.0865   0.9147   0.0831
  -8.000  -0.0645   0.08603   0.08197  -0.0872   0.9100   0.0856
  -7.750  -0.0250   0.08103   0.07686  -0.0922   0.8988   0.0909
  -7.500  -0.0081   0.07722   0.07287  -0.1068   0.8785   0.0974
  -7.250   0.0191   0.07171   0.06725  -0.1118   0.8624   0.1006
  -7.000   0.0514   0.06800   0.06340  -0.1144   0.8451   0.1067
  -6.750   0.0485   0.06673   0.06185  -0.1204   0.8236   0.1132
  -6.500   0.0628   0.06240   0.05746  -0.1209   0.8084   0.1159
  -6.250   0.0823   0.05965   0.05464  -0.1202   0.7936   0.1203
  -6.000   0.0732   0.06045   0.05486  -0.1217   0.7793   0.1296
  -5.750   0.0948   0.05510   0.04977  -0.1203   0.7662   0.1331
  -5.500   0.1045   0.05350   0.04803  -0.1191   0.7532   0.1424
  -5.250   0.1121   0.05107   0.04547  -0.1181   0.7419   0.1489
  -5.000   0.1213   0.04962   0.04368  -0.1175   0.7323   0.1621
  -4.750   0.1344   0.04721   0.04135  -0.1153   0.7206   0.1674
  -4.500   0.1443   0.04546   0.03941  -0.1139   0.7110   0.1809
  -4.250   0.1569   0.04377   0.03756  -0.1124   0.7023   0.1966
  -4.000   0.1677   0.04231   0.03606  -0.1101   0.6930   0.2141
  -3.750   0.1807   0.04100   0.03461  -0.1083   0.6855   0.2446
  -3.500   0.1915   0.03972   0.03338  -0.1054   0.6766   0.2681
  -2.750   0.2227   0.03597   0.02957  -0.0960   0.6552   0.3867
  -2.500   0.2318   0.03434   0.02800  -0.0922   0.6491   0.4253
  -2.250   0.3069   0.03117   0.02201  -0.0990   0.6430   0.1291
  -2.000   0.3338   0.02905   0.01968  -0.0987   0.6380   0.1199
  -1.750   0.3557   0.02856   0.01878  -0.0967   0.6320   0.1123
  -1.500   0.3790   0.02763   0.01768  -0.0957   0.6260   0.1102
  -1.250   0.4090   0.02687   0.01661  -0.0956   0.6214   0.1106
  -1.000   0.4285   0.02666   0.01627  -0.0939   0.6153   0.1123
  -0.750   0.4534   0.02626   0.01573  -0.0931   0.6098   0.1132
  -0.500   0.4851   0.02563   0.01495  -0.0936   0.6058   0.1147
  -0.250   0.5071   0.02534   0.01477  -0.0927   0.6011   0.1178
   0.000   0.5272   0.02532   0.01480  -0.0914   0.5962   0.1240
   0.250   0.5531   0.02509   0.01458  -0.0910   0.5922   0.1331
   0.500   0.5853   0.02479   0.01421  -0.0916   0.5889   0.1471
   0.750   0.6026   0.02501   0.01460  -0.0901   0.5838   0.1728
   1.000   0.7897   0.02333   0.01438  -0.1230   0.5764   1.0000
   1.250   0.8145   0.02371   0.01459  -0.1225   0.5735   1.0000
   1.500   0.8278   0.02451   0.01539  -0.1202   0.5698   1.0000
   1.750   0.8393   0.02533   0.01624  -0.1177   0.5655   1.0000
   2.000   0.8587   0.02587   0.01669  -0.1163   0.5618   1.0000
   2.250   0.8824   0.02629   0.01700  -0.1157   0.5588   1.0000
   2.500   0.9056   0.02683   0.01745  -0.1150   0.5563   1.0000
   2.750   0.9030   0.02831   0.01910  -0.1104   0.5519   1.0000
   3.000   0.9124   0.02934   0.02015  -0.1076   0.5480   1.0000
   3.250   0.9326   0.02989   0.02066  -0.1065   0.5449   1.0000
   3.500   0.9603   0.03021   0.02088  -0.1065   0.5423   1.0000
   3.750   0.9650   0.03158   0.02232  -0.1032   0.5390   1.0000
   4.000   0.9447   0.03399   0.02491  -0.0963   0.5337   1.0000
   4.250   0.9547   0.03504   0.02597  -0.0939   0.5301   1.0000
   4.500   0.9834   0.03527   0.02613  -0.0940   0.5275   1.0000
   4.750   1.0230   0.03511   0.02588  -0.0957   0.5255   1.0000
   5.000   0.8400   0.04590   0.03710  -0.0696   0.5135   1.0000
   5.250   0.9046   0.04411   0.03522  -0.0734   0.5122   1.0000
   5.500   0.9792   0.04188   0.03291  -0.0788   0.5109   1.0000
   5.750   0.7672   0.05869   0.04995  -0.0590   0.4948   1.0000
   6.000   0.8274   0.05569   0.04689  -0.0595   0.4941   1.0000
   7.250   0.6849   0.08171   0.07308  -0.0499   0.4569   1.0000
   7.500   0.6928   0.08382   0.07520  -0.0492   0.4522   1.0000
   7.750   0.6342   0.09436   0.08589  -0.0502   0.4686   1.0000
   8.000   0.6491   0.09645   0.08798  -0.0500   0.4661   1.0000
   8.250   0.6673   0.09865   0.09018  -0.0499   0.4646   1.0000
   8.500   0.6867   0.10114   0.09270  -0.0500   0.4636   1.0000
   8.750   0.6953   0.09927   0.09078  -0.0470   0.4357   1.0000
   9.000   0.7120   0.10136   0.09288  -0.0468   0.4340   1.0000
   9.250   0.7309   0.10354   0.09508  -0.0468   0.4328   1.0000
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