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GOE 572 AIRFOIL (goe572-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 572 AIRFOIL (goe572-il)
Reynolds number: 200,000
Max Cl/Cd: 55.74 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe572-il-200000.txt
Download as CSV file: xf-goe572-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 572 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.2434   0.09823   0.09331  -0.1403   0.6888   0.0466
 -11.000   0.2392   0.09636   0.09141  -0.1426   0.6787   0.0469
 -10.750   0.2446   0.09279   0.08775  -0.1434   0.6698   0.0474
 -10.500   0.2616   0.09003   0.08492  -0.1424   0.6583   0.0480
 -10.250   0.2734   0.08773   0.08254  -0.1424   0.6489   0.0487
 -10.000   0.2832   0.08569   0.08045  -0.1423   0.6403   0.0506
  -9.750   0.2883   0.08350   0.07820  -0.1430   0.6334   0.0524
  -9.500   0.2831   0.08147   0.07620  -0.1446   0.6273   0.0548
  -9.250   0.2644   0.07944   0.07422  -0.1480   0.6233   0.0556
  -9.000   0.2788   0.07571   0.07042  -0.1464   0.6169   0.0569
  -8.750   0.2874   0.07362   0.06832  -0.1457   0.6100   0.0575
  -8.500   0.2958   0.07164   0.06627  -0.1453   0.6042   0.0586
  -8.250   0.2993   0.06962   0.06426  -0.1450   0.5986   0.0603
  -8.000   0.2963   0.06737   0.06204  -0.1451   0.5933   0.0626
  -7.750   0.2835   0.06485   0.05954  -0.1462   0.5896   0.0643
  -7.500   0.2448   0.06273   0.05739  -0.1455   0.5873   0.0657
  -7.250   0.2195   0.06073   0.05523  -0.1434   0.5844   0.0662
  -7.000   0.2246   0.05666   0.05125  -0.1421   0.5791   0.0671
  -6.750   0.2438   0.05513   0.04976  -0.1404   0.5735   0.0687
  -6.500   0.2538   0.05376   0.04830  -0.1389   0.5688   0.0710
  -6.250   0.2531   0.05184   0.04638  -0.1368   0.5642   0.0736
  -6.000   0.2284   0.05130   0.04527  -0.1321   0.5617   0.0786
  -5.750   0.2378   0.04636   0.04048  -0.1315   0.5571   0.0803
  -5.500   0.2537   0.04472   0.03879  -0.1305   0.5529   0.0820
  -5.250   0.2617   0.04330   0.03738  -0.1279   0.5481   0.0847
  -5.000   0.2586   0.04436   0.03778  -0.1223   0.5443   0.0927
  -4.750   0.2672   0.03937   0.03295  -0.1214   0.5403   0.0952
  -4.500   0.2854   0.03802   0.03152  -0.1205   0.5362   0.0983
  -4.250   0.2853   0.03723   0.03039  -0.1155   0.5322   0.1096
  -4.000   0.2999   0.03522   0.02848  -0.1139   0.5272   0.1123
  -3.750   0.3154   0.03404   0.02718  -0.1120   0.5231   0.1174
  -3.500   0.3180   0.02828   0.02030  -0.1048   0.5212   0.0743
  -3.250   0.3323   0.02641   0.01807  -0.1018   0.5176   0.0714
  -3.000   0.3465   0.02467   0.01583  -0.0983   0.5131   0.0685
  -2.750   0.3680   0.02382   0.01484  -0.0970   0.5087   0.0697
  -2.500   0.3933   0.02321   0.01404  -0.0964   0.5046   0.0718
  -2.250   0.4147   0.02259   0.01327  -0.0949   0.5002   0.0731
  -2.000   0.4363   0.02199   0.01255  -0.0935   0.4954   0.0744
  -1.750   0.4617   0.02154   0.01193  -0.0928   0.4913   0.0765
  -1.500   0.4910   0.02115   0.01133  -0.0930   0.4876   0.0792
  -1.250   0.5125   0.02055   0.01080  -0.0918   0.4831   0.0819
  -1.000   0.5337   0.02023   0.01050  -0.0904   0.4783   0.0852
  -0.750   0.5583   0.02001   0.01019  -0.0897   0.4744   0.0905
  -0.500   0.5867   0.01970   0.00979  -0.0899   0.4707   0.0970
  -0.250   0.6004   0.01955   0.00976  -0.0871   0.4663   0.1038
   0.000   0.6181   0.01931   0.00956  -0.0851   0.4620   0.1163
   0.250   0.6394   0.01901   0.00935  -0.0838   0.4583   0.1520
   0.500   0.9215   0.01803   0.01013  -0.1381   0.4453   1.0000
   0.750   0.9421   0.01816   0.01012  -0.1369   0.4417   1.0000
   1.000   0.9654   0.01840   0.01016  -0.1362   0.4382   1.0000
   1.250   0.9787   0.01860   0.01040  -0.1336   0.4341   1.0000
   1.500   0.9960   0.01879   0.01053  -0.1317   0.4300   1.0000
   1.750   1.0163   0.01895   0.01058  -0.1304   0.4265   1.0000
   2.000   1.0403   0.01918   0.01064  -0.1300   0.4233   1.0000
   2.250   1.0545   0.01947   0.01096  -0.1275   0.4196   1.0000
   2.500   1.0698   0.01971   0.01118  -0.1253   0.4156   1.0000
   2.750   1.0885   0.01989   0.01130  -0.1238   0.4119   1.0000
   3.000   1.1104   0.02011   0.01139  -0.1229   0.4089   1.0000
   3.250   1.1300   0.02046   0.01167  -0.1217   0.4057   1.0000
   3.500   1.1425   0.02078   0.01205  -0.1190   0.4022   1.0000
   3.750   1.1583   0.02104   0.01230  -0.1170   0.3985   1.0000
   4.000   1.1776   0.02128   0.01246  -0.1156   0.3954   1.0000
   4.250   1.2017   0.02156   0.01260  -0.1153   0.3924   1.0000
   4.500   1.2140   0.02195   0.01304  -0.1127   0.3892   1.0000
   4.750   1.2249   0.02231   0.01345  -0.1098   0.3858   1.0000
   5.000   1.2396   0.02261   0.01373  -0.1077   0.3825   1.0000
   5.250   1.2583   0.02287   0.01393  -0.1063   0.3795   1.0000
   5.500   1.2844   0.02322   0.01416  -0.1065   0.3767   1.0000
   5.750   1.2920   0.02369   0.01470  -0.1031   0.3740   1.0000
   6.000   1.2957   0.02409   0.01518  -0.0990   0.3711   1.0000
   6.250   1.3052   0.02445   0.01556  -0.0960   0.3681   1.0000
   6.500   1.3206   0.02478   0.01588  -0.0942   0.3655   1.0000
   6.750   1.3416   0.02511   0.01613  -0.0935   0.3630   1.0000
   7.000   1.3650   0.02563   0.01659  -0.0934   0.3603   1.0000
   7.250   1.3616   0.02622   0.01733  -0.0884   0.3576   1.0000
   7.500   1.3676   0.02681   0.01801  -0.0852   0.3549   1.0000
   7.750   1.3786   0.02732   0.01854  -0.0830   0.3522   1.0000
   8.000   1.3954   0.02775   0.01896  -0.0817   0.3498   1.0000
   8.250   1.4187   0.02813   0.01927  -0.0816   0.3474   1.0000
   8.500   1.4402   0.02876   0.01989  -0.0813   0.3451   1.0000
   8.750   1.4325   0.02976   0.02106  -0.0765   0.3427   1.0000
   9.000   1.4330   0.03073   0.02214  -0.0732   0.3400   1.0000
   9.250   1.4403   0.03151   0.02298  -0.0709   0.3375   1.0000
   9.500   1.4545   0.03215   0.02364  -0.0697   0.3353   1.0000
   9.750   1.4760   0.03253   0.02398  -0.0695   0.3331   1.0000
  10.000   1.4962   0.03302   0.02443  -0.0691   0.3300   1.0000
  10.250   1.4804   0.03481   0.02642  -0.0645   0.3276   1.0000
  10.500   1.4718   0.03643   0.02817  -0.0612   0.3245   1.0000
  10.750   1.4771   0.03741   0.02921  -0.0595   0.3215   1.0000
  11.000   1.4988   0.03738   0.02907  -0.0592   0.3180   1.0000
  11.250   1.5141   0.03809   0.02977  -0.0586   0.3151   1.0000
  11.500   1.4934   0.04089   0.03279  -0.0551   0.3127   1.0000
  11.750   1.4802   0.04352   0.03559  -0.0527   0.3100   1.0000
  12.000   1.4805   0.04517   0.03729  -0.0514   0.3068   1.0000
  12.250   1.4984   0.04550   0.03759  -0.0511   0.3039   1.0000
  12.500   1.5114   0.04623   0.03828  -0.0505   0.3001   1.0000
  12.750   1.4883   0.05024   0.04252  -0.0484   0.2982   1.0000
  13.000   1.4610   0.05490   0.04738  -0.0467   0.2957   1.0000
  13.250   1.4508   0.05809   0.05067  -0.0458   0.2924   1.0000
  13.500   1.5032   0.05472   0.04704  -0.0465   0.2870   1.0000
  13.750   1.4807   0.05933   0.05186  -0.0454   0.2851   1.0000
  14.000   1.4374   0.06653   0.05933  -0.0442   0.2834   1.0000
  14.750   1.4427   0.07319   0.06609  -0.0439   0.2712   1.0000
  15.000   1.3788   0.08393   0.07714  -0.0435   0.2708   1.0000
  15.250   0.7799   0.19123   0.18518  -0.0653   0.2912   1.0000
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