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GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 574 AIRFOIL (goe574-il)
Reynolds number: 50,000
Max Cl/Cd: 35.71 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe574-il-50000-n5.txt
Download as CSV file: xf-goe574-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 574 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3390   0.10366   0.09781  -0.0314   1.0000   0.1002
  -7.250  -0.3539   0.10254   0.09685  -0.0313   1.0000   0.1010
  -7.000  -0.3676   0.10131   0.09577  -0.0325   1.0000   0.1015
  -6.750  -0.3576   0.09622   0.09070  -0.0281   1.0000   0.1043
  -6.500  -0.3603   0.09372   0.08829  -0.0261   1.0000   0.1069
  -6.250  -0.3674   0.09174   0.08641  -0.0247   1.0000   0.1092
  -6.000  -0.3766   0.08995   0.08471  -0.0237   1.0000   0.1118
  -5.750  -0.3466   0.08471   0.07938  -0.0349   0.9877   0.1174
  -5.500  -0.3209   0.07993   0.07455  -0.0380   0.9779   0.1216
  -5.250  -0.2952   0.07550   0.06997  -0.0463   0.9625   0.1315
  -5.000  -0.2704   0.07167   0.06596  -0.0516   0.9483   0.1450
  -4.750  -0.2329   0.06254   0.05641  -0.0573   0.9369   0.0699
  -4.500  -0.2079   0.05779   0.05147  -0.0601   0.9243   0.0650
  -4.250  -0.1743   0.05203   0.04498  -0.0643   0.9118   0.0579
  -4.000  -0.1454   0.04786   0.04038  -0.0664   0.9011   0.0579
  -3.750  -0.1181   0.04470   0.03714  -0.0680   0.8910   0.0625
  -3.500  -0.0899   0.04127   0.03318  -0.0689   0.8793   0.0631
  -3.250  -0.0596   0.03802   0.02937  -0.0697   0.8684   0.0631
  -3.000  -0.0252   0.03540   0.02618  -0.0709   0.8594   0.0682
  -2.750   0.0093   0.03287   0.02297  -0.0716   0.8495   0.0707
  -2.500   0.0438   0.03071   0.02020  -0.0722   0.8386   0.0719
  -2.250   0.0821   0.02878   0.01788  -0.0739   0.8292   0.0754
  -2.000   0.1239   0.02741   0.01617  -0.0763   0.8196   0.0834
  -1.750   0.1663   0.02609   0.01440  -0.0784   0.8081   0.0859
  -1.500   0.2134   0.02495   0.01292  -0.0816   0.7968   0.0894
  -1.250   0.2550   0.02411   0.01184  -0.0839   0.7849   0.0948
  -1.000   0.2938   0.02343   0.01093  -0.0857   0.7727   0.1034
  -0.500   0.4398   0.01995   0.00949  -0.1043   0.7481   1.0000
  -0.250   0.4696   0.02011   0.00924  -0.1045   0.7337   1.0000
   0.000   0.4980   0.02031   0.00910  -0.1046   0.7197   1.0000
   0.250   0.5251   0.02053   0.00903  -0.1044   0.7064   1.0000
   0.500   0.5518   0.02078   0.00903  -0.1042   0.6939   1.0000
   0.750   0.5788   0.02103   0.00906  -0.1041   0.6825   1.0000
   1.000   0.6078   0.02126   0.00907  -0.1043   0.6725   1.0000
   1.250   0.6310   0.02161   0.00928  -0.1036   0.6617   1.0000
   1.500   0.6557   0.02194   0.00949  -0.1031   0.6520   1.0000
   1.750   0.6844   0.02221   0.00961  -0.1033   0.6439   1.0000
   2.000   0.7056   0.02263   0.00998  -0.1023   0.6345   1.0000
   2.250   0.7326   0.02297   0.01022  -0.1022   0.6273   1.0000
   2.500   0.7546   0.02341   0.01065  -0.1014   0.6194   1.0000
   2.750   0.7817   0.02378   0.01098  -0.1014   0.6132   1.0000
   3.000   0.8014   0.02430   0.01153  -0.1001   0.6058   1.0000
   3.250   0.8293   0.02465   0.01185  -0.1003   0.6003   1.0000
   3.500   0.8463   0.02527   0.01255  -0.0986   0.5933   1.0000
   3.750   0.8706   0.02575   0.01308  -0.0982   0.5880   1.0000
   4.000   0.8924   0.02631   0.01371  -0.0973   0.5828   1.0000
   4.250   0.9100   0.02698   0.01449  -0.0958   0.5769   1.0000
   4.500   0.9352   0.02746   0.01507  -0.0955   0.5722   1.0000
   4.750   0.9509   0.02822   0.01597  -0.0936   0.5667   1.0000
   5.000   0.9686   0.02895   0.01684  -0.0922   0.5614   1.0000
   5.250   0.9942   0.02946   0.01747  -0.0919   0.5572   1.0000
   5.500   1.0047   0.03044   0.01868  -0.0893   0.5515   1.0000
   5.750   1.0217   0.03123   0.01965  -0.0877   0.5462   1.0000
   6.000   1.0493   0.03170   0.02028  -0.0877   0.5420   1.0000
   6.250   1.0515   0.03297   0.02178  -0.0839   0.5352   1.0000
   6.500   1.0754   0.03343   0.02245  -0.0832   0.5292   1.0000
   6.750   1.0830   0.03442   0.02366  -0.0800   0.5214   1.0000
   7.000   1.1074   0.03427   0.02375  -0.0787   0.5095   1.0000
   7.250   1.1244   0.03225   0.02163  -0.0740   0.4744   1.0000
   7.500   1.1394   0.03191   0.02141  -0.0708   0.4561   1.0000
   7.750   1.1379   0.03194   0.02154  -0.0651   0.4335   1.0000
   8.000   1.1334   0.03196   0.02157  -0.0588   0.4077   1.0000
   8.250   1.1205   0.03248   0.02213  -0.0518   0.3797   1.0000
   8.500   1.1079   0.03356   0.02336  -0.0459   0.3466   1.0000
   8.750   1.0974   0.03463   0.02414  -0.0405   0.2643   1.0000
   9.250   1.0495   0.04102   0.02918  -0.0313   0.0969   1.0000
   9.500   1.0294   0.04499   0.03288  -0.0290   0.0757   1.0000
   9.750   1.0135   0.04899   0.03683  -0.0273   0.0630   1.0000
  10.000   1.0029   0.05270   0.04061  -0.0262   0.0568   1.0000
  10.250   0.9940   0.05641   0.04447  -0.0255   0.0518   1.0000
  10.500   0.9875   0.05995   0.04817  -0.0249   0.0486   1.0000
  10.750   0.9799   0.06372   0.05205  -0.0245   0.0455   1.0000
  11.000   0.9711   0.06770   0.05609  -0.0243   0.0430   1.0000
  11.250   0.9675   0.07112   0.05968  -0.0240   0.0411   1.0000
  11.500   0.9635   0.07461   0.06333  -0.0238   0.0397   1.0000
  11.750   0.9599   0.07806   0.06692  -0.0236   0.0383   1.0000
  12.000   0.9567   0.08148   0.07045  -0.0234   0.0371   1.0000
  12.250   0.9549   0.08468   0.07373  -0.0231   0.0360   1.0000
  12.500   0.9544   0.08760   0.07671  -0.0226   0.0350   1.0000
  12.750   0.9591   0.08982   0.07905  -0.0217   0.0336   1.0000
  13.000   0.9674   0.09154   0.08092  -0.0205   0.0319   1.0000
  13.250   0.9786   0.09283   0.08236  -0.0190   0.0304   1.0000
  13.500   0.9973   0.09305   0.08271  -0.0164   0.0291   1.0000
  13.750   1.0378   0.09096   0.08086  -0.0114   0.0279   1.0000
  14.000   1.0918   0.08992   0.08000  -0.0066   0.0265   1.0000
  14.250   1.0939   0.09338   0.08380  -0.0064   0.0262   1.0000
  14.500   1.0919   0.09729   0.08803  -0.0067   0.0259   1.0000
  14.750   1.0876   0.10148   0.09250  -0.0074   0.0258   1.0000
  15.000   1.0786   0.10619   0.09749  -0.0086   0.0255   1.0000
  15.250   1.0687   0.11118   0.10274  -0.0103   0.0254   1.0000
  15.500   1.0594   0.11628   0.10805  -0.0121   0.0255   1.0000
  15.750   1.0495   0.12157   0.11354  -0.0143   0.0256   1.0000
  16.000   1.0371   0.12750   0.11966  -0.0171   0.0257   1.0000
  16.250   1.0248   0.13366   0.12599  -0.0203   0.0258   1.0000
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