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GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 574 AIRFOIL (goe574-il)
Reynolds number: 500,000
Max Cl/Cd: 99.96 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe574-il-500000.txt
Download as CSV file: xf-goe574-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3423   0.10399   0.10193  -0.0292   1.0000   0.0158
  -8.500  -0.3437   0.10106   0.09904  -0.0294   1.0000   0.0158
  -8.250  -0.3463   0.09834   0.09635  -0.0293   1.0000   0.0158
  -8.000  -0.3314   0.09355   0.09157  -0.0353   0.9972   0.0159
  -7.750  -0.3232   0.08741   0.08544  -0.0398   0.9944   0.0162
  -7.500  -0.3070   0.08395   0.08199  -0.0423   0.9909   0.0166
  -7.250  -0.2889   0.07982   0.07784  -0.0479   0.9867   0.0170
  -7.000  -0.2681   0.07539   0.07340  -0.0538   0.9816   0.0175
  -6.750  -0.2437   0.07034   0.06832  -0.0611   0.9760   0.0183
  -6.500  -0.2246   0.06557   0.06350  -0.0667   0.9678   0.0194
  -6.250  -0.1961   0.05977   0.05758  -0.0749   0.9559   0.0213
  -5.750  -0.1632   0.05072   0.04829  -0.0786   0.9181   0.0216
  -5.500  -0.1366   0.04518   0.04254  -0.0821   0.9056   0.0217
  -5.250  -0.1160   0.03712   0.03423  -0.0865   0.8942   0.0227
  -5.000  -0.0721   0.03391   0.03084  -0.0925   0.8825   0.0237
  -4.750  -0.0180   0.02999   0.02658  -0.1001   0.8673   0.0272
  -4.500   0.0423   0.02697   0.02285  -0.1065   0.8473   0.0299
  -4.250   0.0690   0.02111   0.01647  -0.1091   0.8257   0.0325
  -4.000   0.0963   0.01993   0.01504  -0.1096   0.8042   0.0348
  -3.750   0.1193   0.01881   0.01357  -0.1084   0.7854   0.0384
  -3.000   0.1782   0.01423   0.00794  -0.1023   0.7351   0.0377
  -2.750   0.1997   0.01321   0.00665  -0.1006   0.7179   0.0373
  -2.500   0.2219   0.01270   0.00595  -0.0992   0.7006   0.0388
  -2.250   0.2441   0.01219   0.00526  -0.0978   0.6835   0.0395
  -2.000   0.2661   0.01173   0.00465  -0.0964   0.6662   0.0399
  -1.750   0.2879   0.01132   0.00412  -0.0950   0.6487   0.0401
  -1.500   0.3096   0.01108   0.00375  -0.0936   0.6311   0.0406
  -1.250   0.3306   0.01078   0.00334  -0.0920   0.6139   0.0414
  -1.000   0.3509   0.01047   0.00291  -0.0903   0.5975   0.0420
  -0.750   0.3715   0.01025   0.00257  -0.0887   0.5816   0.0433
  -0.500   0.3931   0.01014   0.00237  -0.0874   0.5663   0.0444
  -0.250   0.4153   0.01009   0.00223  -0.0861   0.5521   0.0462
   0.000   0.4382   0.01008   0.00213  -0.0851   0.5394   0.0478
   0.250   0.4617   0.01007   0.00205  -0.0841   0.5285   0.0509
   0.500   0.4853   0.01008   0.00201  -0.0832   0.5195   0.0574
   0.750   0.5066   0.00988   0.00204  -0.0820   0.5116   0.1568
   1.000   0.5009   0.00835   0.00217  -0.0752   0.5063   0.7419
   1.250   0.7347   0.00902   0.00302  -0.1221   0.4908   1.0000
   1.500   0.7576   0.00912   0.00307  -0.1211   0.4858   1.0000
   1.750   0.7802   0.00927   0.00314  -0.1201   0.4812   1.0000
   2.000   0.8035   0.00936   0.00322  -0.1192   0.4770   1.0000
   2.250   0.8266   0.00946   0.00331  -0.1183   0.4732   1.0000
   2.500   0.8496   0.00959   0.00340  -0.1174   0.4694   1.0000
   2.750   0.8731   0.00976   0.00352  -0.1166   0.4660   1.0000
   3.000   0.8957   0.00983   0.00362  -0.1156   0.4621   1.0000
   3.250   0.9179   0.00993   0.00373  -0.1145   0.4572   1.0000
   3.500   0.9405   0.01011   0.00386  -0.1135   0.4525   1.0000
   3.750   0.9610   0.01016   0.00395  -0.1120   0.4456   1.0000
   4.000   0.9809   0.01031   0.00405  -0.1104   0.4370   1.0000
   4.250   1.0016   0.01036   0.00415  -0.1090   0.4307   1.0000
   4.500   1.0218   0.01052   0.00429  -0.1075   0.4239   1.0000
   4.750   1.0413   0.01057   0.00439  -0.1058   0.4148   1.0000
   5.000   1.0602   0.01068   0.00451  -0.1040   0.4048   1.0000
   5.250   1.0776   0.01078   0.00459  -0.1018   0.3882   1.0000
   5.500   1.0932   0.01095   0.00470  -0.0993   0.3587   1.0000
   5.750   1.0890   0.01222   0.00523  -0.0932   0.2283   1.0000
   6.000   1.0708   0.01430   0.00648  -0.0846   0.0783   1.0000
   6.250   1.0696   0.01523   0.00720  -0.0789   0.0253   1.0000
   6.500   1.0804   0.01565   0.00768  -0.0754   0.0213   1.0000
   6.750   1.0907   0.01611   0.00824  -0.0720   0.0196   1.0000
   7.000   1.1018   0.01655   0.00876  -0.0687   0.0187   1.0000
   7.250   1.1113   0.01710   0.00940  -0.0653   0.0176   1.0000
   7.500   1.1203   0.01768   0.01005  -0.0618   0.0165   1.0000
   7.750   1.1273   0.01837   0.01083  -0.0580   0.0158   1.0000
   8.000   1.1321   0.01918   0.01173  -0.0540   0.0152   1.0000
   8.250   1.1345   0.02014   0.01278  -0.0497   0.0147   1.0000
   8.500   1.1315   0.02140   0.01414  -0.0448   0.0142   1.0000
   8.750   1.1314   0.02260   0.01544  -0.0406   0.0141   1.0000
   9.000   1.1270   0.02415   0.01709  -0.0362   0.0140   1.0000
   9.250   1.1120   0.02659   0.01965  -0.0309   0.0135   1.0000
   9.500   1.1139   0.02818   0.02130  -0.0282   0.0135   1.0000
   9.750   1.1145   0.03010   0.02329  -0.0254   0.0134   1.0000
  10.000   1.1310   0.03059   0.02389  -0.0247   0.0125   1.0000
  10.250   1.1357   0.03227   0.02564  -0.0226   0.0123   1.0000
  10.500   1.1412   0.03408   0.02751  -0.0204   0.0125   1.0000
  10.750   1.1513   0.03555   0.02904  -0.0187   0.0122   1.0000
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