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GOE 457 AIRFOIL (goe457-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 457 AIRFOIL (goe457-il)
Reynolds number: 100,000
Max Cl/Cd: 54.53 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe457-il-100000.txt
Download as CSV file: xf-goe457-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 457 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3566   0.09383   0.08913  -0.0216   1.0000   0.0792
  -7.250  -0.3685   0.09250   0.08791  -0.0209   1.0000   0.0810
  -7.000  -0.3787   0.09140   0.08690  -0.0252   1.0000   0.0825
  -6.750  -0.3805   0.08982   0.08530  -0.0327   1.0000   0.0832
  -6.500  -0.3777   0.08431   0.07991  -0.0263   1.0000   0.0845
  -6.250  -0.3724   0.08117   0.07680  -0.0218   1.0000   0.0866
  -6.000  -0.3683   0.07856   0.07422  -0.0207   1.0000   0.0899
  -5.750  -0.3626   0.07583   0.07149  -0.0237   1.0000   0.0951
  -5.500  -0.3515   0.07178   0.06735  -0.0313   1.0000   0.0989
  -5.250  -0.3483   0.06897   0.06464  -0.0263   1.0000   0.1015
  -5.000  -0.3389   0.06622   0.06189  -0.0260   1.0000   0.1059
  -4.750  -0.3163   0.06192   0.05738  -0.0340   1.0000   0.1140
  -4.500  -0.3095   0.05919   0.05474  -0.0309   1.0000   0.1168
  -4.250  -0.2837   0.05569   0.05097  -0.0367   1.0000   0.1287
  -4.000  -0.2760   0.05304   0.04844  -0.0336   1.0000   0.1323
  -3.750  -0.2563   0.05014   0.04543  -0.0355   1.0000   0.1458
  -3.500  -0.2368   0.04757   0.04275  -0.0366   1.0000   0.1599
  -3.250  -0.2174   0.04515   0.04025  -0.0372   1.0000   0.1746
  -3.000  -0.1989   0.04294   0.03799  -0.0373   1.0000   0.1900
  -2.000  -0.0659   0.02855   0.02160  -0.0456   1.0000   0.1176
  -1.750  -0.0223   0.02611   0.01853  -0.0482   0.9954   0.1065
  -1.500   0.0307   0.02407   0.01579  -0.0523   0.9863   0.1009
  -1.250   0.0822   0.02274   0.01406  -0.0564   0.9755   0.1000
  -1.000   0.1324   0.02164   0.01288  -0.0605   0.9634   0.1052
  -0.750   0.1829   0.02070   0.01176  -0.0643   0.9504   0.1111
  -0.500   0.2318   0.01949   0.01067  -0.0679   0.9369   0.1187
  -0.250   0.2809   0.01838   0.00969  -0.0713   0.9226   0.1395
   0.000   0.3480   0.01504   0.00877  -0.0780   0.9166   1.0000
   0.250   0.4028   0.01457   0.00800  -0.0823   0.9009   1.0000
   0.500   0.4481   0.01411   0.00736  -0.0846   0.8785   1.0000
   0.750   0.4957   0.01357   0.00667  -0.0873   0.8561   1.0000
   1.000   0.5323   0.01320   0.00616  -0.0879   0.8230   1.0000
   1.250   0.5704   0.01290   0.00568  -0.0888   0.7870   1.0000
   1.500   0.6080   0.01278   0.00529  -0.0897   0.7513   1.0000
   1.750   0.6401   0.01294   0.00518  -0.0898   0.7168   1.0000
   2.000   0.6690   0.01325   0.00523  -0.0894   0.6872   1.0000
   2.250   0.6962   0.01364   0.00539  -0.0889   0.6616   1.0000
   2.500   0.7221   0.01404   0.00562  -0.0882   0.6386   1.0000
   2.750   0.7481   0.01447   0.00588  -0.0876   0.6186   1.0000
   3.000   0.7731   0.01491   0.00621  -0.0868   0.5994   1.0000
   3.250   0.7985   0.01537   0.00657  -0.0862   0.5822   1.0000
   3.500   0.8238   0.01585   0.00696  -0.0855   0.5660   1.0000
   3.750   0.8489   0.01636   0.00741  -0.0848   0.5505   1.0000
   4.000   0.8737   0.01687   0.00787  -0.0841   0.5355   1.0000
   4.250   0.8980   0.01736   0.00831  -0.0832   0.5196   1.0000
   4.500   0.9218   0.01782   0.00873  -0.0823   0.5030   1.0000
   4.750   0.9452   0.01823   0.00908  -0.0812   0.4862   1.0000
   5.000   0.9685   0.01861   0.00940  -0.0801   0.4697   1.0000
   5.250   0.9908   0.01894   0.00975  -0.0789   0.4533   1.0000
   5.500   1.0135   0.01926   0.01013  -0.0778   0.4377   1.0000
   5.750   1.0358   0.01956   0.01047  -0.0766   0.4221   1.0000
   6.000   1.0578   0.01985   0.01081  -0.0753   0.4064   1.0000
   6.250   1.0792   0.02011   0.01114  -0.0740   0.3899   1.0000
   6.500   1.1001   0.02035   0.01147  -0.0725   0.3723   1.0000
   6.750   1.1206   0.02061   0.01177  -0.0710   0.3538   1.0000
   7.000   1.1397   0.02090   0.01211  -0.0693   0.3320   1.0000
   7.250   1.1567   0.02124   0.01245  -0.0672   0.3047   1.0000
   7.500   1.1713   0.02181   0.01299  -0.0648   0.2691   1.0000
   7.750   1.1853   0.02274   0.01370  -0.0624   0.2357   1.0000
   8.000   1.2011   0.02377   0.01463  -0.0605   0.2102   1.0000
   8.250   1.2177   0.02476   0.01548  -0.0587   0.1928   1.0000
   8.500   1.2345   0.02570   0.01636  -0.0571   0.1782   1.0000
   8.750   1.2521   0.02657   0.01734  -0.0556   0.1666   1.0000
   9.000   1.2698   0.02752   0.01838  -0.0542   0.1571   1.0000
   9.250   1.2861   0.02847   0.01935  -0.0527   0.1481   1.0000
   9.500   1.3025   0.02939   0.02035  -0.0511   0.1404   1.0000
   9.750   1.3200   0.03050   0.02158  -0.0498   0.1345   1.0000
  10.000   1.3347   0.03145   0.02268  -0.0481   0.1274   1.0000
  10.250   1.3457   0.03247   0.02387  -0.0460   0.1188   1.0000
  10.500   1.3538   0.03358   0.02500  -0.0436   0.1096   1.0000
  10.750   1.3562   0.03452   0.02615  -0.0403   0.1000   1.0000
  11.000   1.3570   0.03586   0.02771  -0.0370   0.0898   1.0000
  11.250   1.3536   0.03758   0.02956  -0.0336   0.0784   1.0000
  11.500   1.3487   0.03973   0.03177  -0.0304   0.0684   1.0000
  11.750   1.3444   0.04194   0.03398  -0.0279   0.0612   1.0000
  12.000   1.3429   0.04445   0.03667  -0.0257   0.0551   1.0000
  12.250   1.3407   0.04678   0.03908  -0.0241   0.0514   1.0000
  12.500   1.3390   0.04959   0.04198  -0.0226   0.0483   1.0000
  12.750   1.3388   0.05248   0.04511  -0.0215   0.0457   1.0000
  13.000   1.3383   0.05548   0.04827  -0.0206   0.0439   1.0000
  13.250   1.3369   0.05857   0.05148  -0.0200   0.0423   1.0000
  13.500   1.3368   0.06176   0.05473  -0.0196   0.0411   1.0000
  13.750   1.3355   0.06564   0.05872  -0.0192   0.0401   1.0000
  14.000   1.3275   0.07013   0.06350  -0.0196   0.0396   1.0000
  14.250   1.3163   0.07515   0.06881  -0.0207   0.0393   1.0000
  14.500   1.3023   0.08075   0.07467  -0.0225   0.0392   1.0000
  14.750   1.2857   0.08694   0.08111  -0.0250   0.0392   1.0000
  15.000   1.2664   0.09383   0.08824  -0.0284   0.0393   1.0000
  15.250   1.2453   0.10139   0.09602  -0.0325   0.0394   1.0000
  15.500   1.2227   0.10965   0.10448  -0.0373   0.0397   1.0000
  15.750   1.1992   0.11860   0.11360  -0.0428   0.0400   1.0000
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