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GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 6K AIRFOIL (goe06k-il)
Reynolds number: 100,000
Max Cl/Cd: 44.57 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe06k-il-100000-n5.txt
Download as CSV file: xf-goe06k-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 6K 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4709   0.10411   0.09956  -0.0290   1.0000   0.0357
  -7.750  -0.4817   0.10213   0.09766  -0.0277   1.0000   0.0358
  -7.500  -0.4934   0.10004   0.09564  -0.0273   1.0000   0.0358
  -7.250  -0.4992   0.09727   0.09291  -0.0280   1.0000   0.0359
  -7.000  -0.5023   0.09419   0.08985  -0.0290   1.0000   0.0360
  -6.750  -0.4883   0.08897   0.08461  -0.0342   0.9966   0.0362
  -6.500  -0.4810   0.08462   0.08028  -0.0320   0.9948   0.0370
  -6.250  -0.4676   0.08042   0.07604  -0.0344   0.9912   0.0380
  -6.000  -0.4501   0.07592   0.07146  -0.0386   0.9876   0.0397
  -5.750  -0.4322   0.07147   0.06690  -0.0430   0.9829   0.0420
  -5.500  -0.3972   0.06729   0.06220  -0.0521   0.9774   0.0445
  -5.250  -0.3870   0.06180   0.05674  -0.0526   0.9737   0.0454
  -5.000  -0.3739   0.05807   0.05304  -0.0526   0.9708   0.0477
  -4.750  -0.3496   0.05385   0.04860  -0.0552   0.9681   0.0489
  -4.500  -0.3228   0.04770   0.04189  -0.0556   0.9634   0.0252
  -4.250  -0.3029   0.04378   0.03774  -0.0561   0.9599   0.0235
  -4.000  -0.2774   0.03999   0.03353  -0.0569   0.9572   0.0222
  -3.750  -0.2523   0.03650   0.02958  -0.0569   0.9548   0.0211
  -3.500  -0.2321   0.03358   0.02620  -0.0554   0.9508   0.0208
  -3.250  -0.2071   0.03115   0.02326  -0.0547   0.9477   0.0222
  -3.000  -0.1791   0.02883   0.02038  -0.0543   0.9453   0.0233
  -2.750  -0.1496   0.02673   0.01774  -0.0541   0.9435   0.0236
  -2.500  -0.1188   0.02498   0.01548  -0.0540   0.9421   0.0255
  -2.250  -0.0962   0.02368   0.01401  -0.0530   0.9390   0.0289
  -2.000  -0.0723   0.02266   0.01284  -0.0520   0.9355   0.0321
  -1.750  -0.0459   0.02181   0.01186  -0.0517   0.9326   0.0390
  -1.500  -0.0184   0.02109   0.01104  -0.0516   0.9301   0.0518
  -1.250   0.0104   0.02043   0.01033  -0.0519   0.9282   0.0800
  -1.000   0.0947   0.01754   0.01015  -0.0649   0.9344   1.0000
  -0.750   0.1228   0.01769   0.00997  -0.0652   0.9313   1.0000
  -0.500   0.1538   0.01785   0.00985  -0.0662   0.9288   1.0000
  -0.250   0.1783   0.01801   0.00981  -0.0658   0.9246   1.0000
   0.000   0.2011   0.01818   0.00982  -0.0651   0.9199   1.0000
   0.250   0.2294   0.01836   0.00985  -0.0655   0.9168   1.0000
   0.500   0.2609   0.01854   0.00991  -0.0666   0.9143   1.0000
   0.750   0.2823   0.01875   0.01004  -0.0657   0.9093   1.0000
   1.000   0.3060   0.01896   0.01019  -0.0652   0.9048   1.0000
   1.250   0.3358   0.01914   0.01033  -0.0659   0.9015   1.0000
   1.500   0.3681   0.01931   0.01049  -0.0672   0.8991   1.0000
   1.750   0.3858   0.01954   0.01074  -0.0655   0.8920   1.0000
   2.000   0.4179   0.01960   0.01083  -0.0665   0.8872   1.0000
   2.250   0.4553   0.01960   0.01089  -0.0686   0.8840   1.0000
   2.500   0.4725   0.01980   0.01116  -0.0666   0.8750   1.0000
   2.750   0.5058   0.01985   0.01133  -0.0679   0.8713   1.0000
   3.000   0.5268   0.02007   0.01165  -0.0668   0.8641   1.0000
   3.250   0.5564   0.02015   0.01190  -0.0672   0.8588   1.0000
   3.500   0.5935   0.02008   0.01204  -0.0690   0.8555   1.0000
   3.750   0.6120   0.02022   0.01238  -0.0672   0.8449   1.0000
   4.000   0.6455   0.01967   0.01210  -0.0675   0.8321   1.0000
   4.250   0.6904   0.01801   0.01079  -0.0684   0.8093   1.0000
   4.500   0.7220   0.01620   0.00919  -0.0659   0.7488   1.0000
   4.750   0.7558   0.01911   0.00826  -0.0657   0.0727   1.0000
   5.000   0.7690   0.02042   0.00939  -0.0628   0.0378   1.0000
   5.250   0.7835   0.02148   0.01052  -0.0601   0.0286   1.0000
   5.500   0.7963   0.02265   0.01186  -0.0571   0.0254   1.0000
   5.750   0.8109   0.02380   0.01317  -0.0545   0.0221   1.0000
   6.000   0.8286   0.02542   0.01488  -0.0526   0.0199   1.0000
   6.250   0.8626   0.02850   0.01805  -0.0540   0.0180   1.0000
   6.500   0.8942   0.03044   0.02036  -0.0542   0.0162   1.0000
   6.750   0.9271   0.03338   0.02370  -0.0547   0.0156   1.0000
   7.000   0.9526   0.03658   0.02738  -0.0536   0.0154   1.0000
   7.250   0.9709   0.03988   0.03118  -0.0514   0.0155   1.0000
   7.500   0.9832   0.04300   0.03478  -0.0484   0.0152   1.0000
   7.750   0.9917   0.04593   0.03810  -0.0450   0.0148   1.0000
   8.000   0.9971   0.04874   0.04126  -0.0415   0.0143   1.0000
   8.250   1.0001   0.05148   0.04425  -0.0382   0.0138   1.0000
   8.500   0.9972   0.05536   0.04861  -0.0332   0.0143   1.0000
   8.750   0.9912   0.05916   0.05277  -0.0285   0.0148   1.0000
   9.000   0.9825   0.06269   0.05658  -0.0239   0.0152   1.0000
   9.250   0.9704   0.06580   0.05990  -0.0193   0.0156   1.0000
   9.500   0.9549   0.06905   0.06334  -0.0148   0.0159   1.0000
   9.750   0.9390   0.07236   0.06681  -0.0111   0.0161   1.0000
  10.000   0.9237   0.07568   0.07027  -0.0084   0.0164   1.0000
  10.250   0.9060   0.07950   0.07423  -0.0065   0.0166   1.0000
  10.500   0.8881   0.08374   0.07858  -0.0057   0.0167   1.0000
  10.750   0.8716   0.08828   0.08322  -0.0061   0.0169   1.0000
  11.000   0.8551   0.09353   0.08855  -0.0077   0.0170   1.0000
  11.250   0.8407   0.09944   0.09452  -0.0106   0.0171   1.0000
  11.500   0.8292   0.10603   0.10114  -0.0144   0.0174   1.0000
  11.750   0.8212   0.11190   0.10699  -0.0171   0.0179   1.0000
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