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GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 372 AIRFOIL (goe372-il)
Reynolds number: 500,000
Max Cl/Cd: 92.95 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe372-il-500000-n5.txt
Download as CSV file: xf-goe372-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 372 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3587   0.09616   0.09395  -0.0275   1.0000   0.0040
  -8.500  -0.3592   0.09268   0.09051  -0.0281   1.0000   0.0040
  -8.250  -0.3604   0.08946   0.08733  -0.0284   1.0000   0.0039
  -8.000  -0.3632   0.08645   0.08436  -0.0283   1.0000   0.0039
  -7.750  -0.3690   0.08384   0.08181  -0.0275   1.0000   0.0039
  -7.500  -0.3627   0.07956   0.07755  -0.0313   0.9961   0.0038
  -7.250  -0.3444   0.07362   0.07162  -0.0394   0.9882   0.0038
  -7.000  -0.3246   0.06689   0.06488  -0.0490   0.9794   0.0038
  -6.750  -0.2995   0.05797   0.05592  -0.0620   0.9695   0.0038
  -6.500  -0.2612   0.01921   0.01562  -0.1004   0.9519   0.0033
  -6.250  -0.2346   0.01555   0.01126  -0.1016   0.9425   0.0034
  -6.000  -0.2051   0.01366   0.00891  -0.1025   0.9334   0.0035
  -5.750  -0.1750   0.01239   0.00727  -0.1031   0.9239   0.0038
  -5.500  -0.1455   0.01138   0.00593  -0.1035   0.9131   0.0048
  -5.250  -0.1171   0.01073   0.00514  -0.1036   0.9009   0.0100
  -5.000  -0.0892   0.01035   0.00461  -0.1036   0.8878   0.0147
  -4.750  -0.0617   0.01009   0.00418  -0.1035   0.8739   0.0167
  -4.500  -0.0346   0.00995   0.00393  -0.1033   0.8607   0.0193
  -4.250  -0.0079   0.00978   0.00373  -0.1031   0.8485   0.0248
  -4.000   0.0188   0.00959   0.00342  -0.1028   0.8380   0.0267
  -3.750   0.0456   0.00936   0.00306  -0.1025   0.8283   0.0278
  -3.500   0.0721   0.00909   0.00268  -0.1021   0.8194   0.0305
  -3.250   0.0988   0.00889   0.00245  -0.1018   0.8103   0.0349
  -3.000   0.1256   0.00875   0.00224  -0.1015   0.8017   0.0405
  -2.750   0.1524   0.00866   0.00208  -0.1013   0.7932   0.0484
  -2.500   0.1793   0.00855   0.00192  -0.1010   0.7852   0.0536
  -2.250   0.2062   0.00848   0.00181  -0.1007   0.7773   0.0593
  -2.000   0.2331   0.00842   0.00169  -0.1005   0.7688   0.0630
  -1.750   0.2599   0.00833   0.00158  -0.1002   0.7610   0.0685
  -1.500   0.2868   0.00830   0.00150  -0.1000   0.7530   0.0743
  -1.250   0.3137   0.00822   0.00138  -0.0997   0.7447   0.0802
  -1.000   0.3404   0.00816   0.00129  -0.0995   0.7363   0.0847
  -0.750   0.3673   0.00812   0.00121  -0.0992   0.7275   0.0885
  -0.500   0.3940   0.00806   0.00116  -0.0989   0.7188   0.0956
  -0.250   0.4206   0.00803   0.00111  -0.0986   0.7087   0.1034
   0.000   0.4470   0.00801   0.00108  -0.0983   0.6958   0.1142
   0.250   0.4733   0.00799   0.00107  -0.0979   0.6819   0.1290
   0.500   0.4996   0.00796   0.00107  -0.0976   0.6680   0.1489
   0.750   0.5256   0.00794   0.00108  -0.0972   0.6517   0.1746
   1.000   0.5511   0.00791   0.00111  -0.0968   0.6307   0.2209
   1.250   0.5749   0.00789   0.00118  -0.0960   0.5956   0.3064
   1.500   0.5964   0.00797   0.00128  -0.0949   0.5462   0.4223
   1.750   0.6366   0.00700   0.00145  -0.0980   0.5149   1.0000
   2.000   0.6612   0.00724   0.00155  -0.0974   0.4917   1.0000
   2.250   0.6863   0.00743   0.00169  -0.0968   0.4692   1.0000
   2.500   0.7111   0.00765   0.00180  -0.0963   0.4438   1.0000
   2.750   0.7354   0.00792   0.00193  -0.0956   0.4103   1.0000
   3.000   0.7504   0.00914   0.00236  -0.0936   0.2480   1.0000
   3.250   0.7695   0.01005   0.00281  -0.0922   0.1521   1.0000
   3.500   0.7865   0.01121   0.00341  -0.0906   0.0252   1.0000
   3.750   0.8111   0.01152   0.00373  -0.0899   0.0181   1.0000
   4.000   0.8352   0.01187   0.00418  -0.0891   0.0148   1.0000
   4.250   0.8598   0.01216   0.00450  -0.0885   0.0120   1.0000
   4.500   0.8833   0.01258   0.00508  -0.0877   0.0094   1.0000
   4.750   0.9042   0.01332   0.00591  -0.0863   0.0076   1.0000
   5.000   0.9281   0.01366   0.00628  -0.0856   0.0062   1.0000
   5.250   0.9514   0.01407   0.00671  -0.0848   0.0046   1.0000
   5.500   0.9726   0.01472   0.00742  -0.0836   0.0039   1.0000
   5.750   0.9932   0.01541   0.00816  -0.0823   0.0033   1.0000
   6.000   1.0074   0.01682   0.00970  -0.0799   0.0027   1.0000
   6.250   1.0178   0.01898   0.01198  -0.0767   0.0025   1.0000
   6.500   1.0347   0.02087   0.01395  -0.0747   0.0024   1.0000
   6.750   1.0553   0.02256   0.01575  -0.0734   0.0024   1.0000
   7.000   1.0771   0.02457   0.01788  -0.0722   0.0024   1.0000
   7.250   1.0989   0.02703   0.02053  -0.0710   0.0024   1.0000
   9.250   1.2113   0.04801   0.04373  -0.0533   0.0044   1.0000
   9.500   1.2071   0.05212   0.04815  -0.0496   0.0051   1.0000
   9.750   1.1981   0.05580   0.05208  -0.0460   0.0057   1.0000
  10.000   1.1537   0.06471   0.06113  -0.0418   0.0077   1.0000
  10.250   1.1386   0.06737   0.06394  -0.0386   0.0077   1.0000
  10.500   1.1215   0.07064   0.06736  -0.0365   0.0077   1.0000
  10.750   1.1047   0.07422   0.07110  -0.0354   0.0077   1.0000
  11.000   1.0865   0.07848   0.07550  -0.0355   0.0077   1.0000
  11.250   1.0691   0.08307   0.08022  -0.0365   0.0077   1.0000
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