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GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 207 (AVIATIK V8) AIRFOIL (goe207-il)
Reynolds number: 100,000
Max Cl/Cd: 51.99 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe207-il-100000-n5.txt
Download as CSV file: xf-goe207-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 207 (AVIATIK V8) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2644   0.11492   0.11030  -0.0112   1.0000   0.0372
  -8.750  -0.2596   0.11324   0.10868  -0.0139   1.0000   0.0375
  -8.500  -0.2555   0.11149   0.10700  -0.0164   1.0000   0.0376
  -8.250  -0.2447   0.10732   0.10289  -0.0166   1.0000   0.0378
  -8.000  -0.2346   0.10357   0.09919  -0.0168   1.0000   0.0382
  -7.750  -0.2267   0.10066   0.09634  -0.0175   1.0000   0.0387
  -7.500  -0.2203   0.09810   0.09387  -0.0183   1.0000   0.0392
  -7.250  -0.2029   0.09480   0.09057  -0.0223   0.9529   0.0399
  -7.000  -0.1817   0.09132   0.08705  -0.0272   0.9154   0.0409
  -6.750  -0.1638   0.08835   0.08399  -0.0312   0.8827   0.0423
  -6.500  -0.1451   0.08616   0.08169  -0.0370   0.8523   0.0434
  -6.000  -0.1094   0.08073   0.07603  -0.0447   0.8014   0.0440
  -5.750  -0.0984   0.07729   0.07250  -0.0438   0.7793   0.0445
  -5.500  -0.0833   0.07437   0.06948  -0.0447   0.7585   0.0452
  -5.250  -0.0650   0.07163   0.06662  -0.0468   0.7390   0.0461
  -5.000  -0.0440   0.06894   0.06380  -0.0495   0.7202   0.0472
  -4.750  -0.0200   0.06631   0.06103  -0.0530   0.7026   0.0487
  -4.500   0.0239   0.06481   0.05918  -0.0621   0.6852   0.0505
  -4.250   0.0399   0.06129   0.05561  -0.0622   0.6697   0.0511
  -4.000   0.0580   0.05834   0.05259  -0.0627   0.6544   0.0521
  -3.750   0.0829   0.05585   0.04997  -0.0648   0.6395   0.0535
  -3.500   0.1115   0.05353   0.04747  -0.0676   0.6251   0.0554
  -3.250   0.1535   0.05213   0.04572  -0.0727   0.6112   0.0577
  -3.000   0.1843   0.04978   0.04315  -0.0753   0.5987   0.0583
  -2.750   0.2045   0.04687   0.04017  -0.0758   0.5866   0.0593
  -2.500   0.2311   0.04472   0.03789  -0.0772   0.5742   0.0611
  -2.250   0.2641   0.04317   0.03609  -0.0794   0.5626   0.0648
  -2.000   0.2993   0.04159   0.03418  -0.0817   0.5516   0.0671
  -1.750   0.3243   0.03935   0.03188  -0.0826   0.5401   0.0690
  -1.500   0.3546   0.03781   0.03013  -0.0840   0.5296   0.0720
  -1.250   0.3955   0.03789   0.02968  -0.0857   0.5188   0.0758
  -1.000   0.4200   0.03506   0.02687  -0.0868   0.5084   0.0772
  -0.750   0.4480   0.03349   0.02513  -0.0876   0.4988   0.0798
  -0.500   0.4853   0.03404   0.02522  -0.0883   0.4879   0.0864
  -0.250   0.5124   0.03149   0.02263  -0.0894   0.4787   0.0881
   0.250   0.5717   0.02927   0.02008  -0.0908   0.4594   0.1020
   0.500   0.6011   0.02851   0.01911  -0.0914   0.4503   0.1165
   0.750   0.6295   0.02729   0.01783  -0.0920   0.4411   0.1223
   1.000   0.6585   0.02651   0.01686  -0.0924   0.4326   0.1385
   1.250   0.6975   0.02511   0.01484  -0.0914   0.4245   0.0555
   1.500   0.7269   0.02440   0.01389  -0.0914   0.4165   0.0538
   1.750   0.7564   0.02377   0.01305  -0.0914   0.4080   0.0526
   2.000   0.7846   0.02336   0.01246  -0.0913   0.4006   0.0540
   2.250   0.8129   0.02300   0.01195  -0.0912   0.3932   0.0557
   2.500   0.8410   0.02262   0.01143  -0.0911   0.3864   0.0558
   2.750   0.8683   0.02233   0.01099  -0.0908   0.3805   0.0560
   3.000   0.8959   0.02209   0.01069  -0.0906   0.3740   0.0567
   3.250   0.9226   0.02192   0.01039  -0.0902   0.3686   0.0577
   3.500   0.9487   0.02185   0.01032  -0.0899   0.3633   0.0611
   3.750   0.9754   0.02188   0.01028  -0.0896   0.3577   0.0653
   4.000   1.0020   0.02191   0.01021  -0.0894   0.3529   0.0682
   4.250   1.0289   0.02206   0.01026  -0.0892   0.3485   0.0731
   4.500   1.0559   0.02224   0.01043  -0.0892   0.3434   0.0836
   4.750   1.0829   0.02243   0.01059  -0.0891   0.3390   0.1047
   5.000   1.1040   0.02133   0.01078  -0.0879   0.3357   1.0000
   5.250   1.1301   0.02179   0.01112  -0.0877   0.3321   1.0000
   5.500   1.1561   0.02227   0.01156  -0.0875   0.3283   1.0000
   5.750   1.1819   0.02275   0.01202  -0.0873   0.3250   1.0000
   6.000   1.2077   0.02323   0.01245  -0.0871   0.3221   1.0000
   6.250   1.2334   0.02374   0.01289  -0.0869   0.3197   1.0000
   6.500   1.2588   0.02430   0.01346  -0.0867   0.3171   1.0000
   6.750   1.2836   0.02487   0.01415  -0.0865   0.3137   1.0000
   7.000   1.3082   0.02542   0.01476  -0.0862   0.3103   1.0000
   7.250   1.3328   0.02593   0.01529  -0.0860   0.3071   1.0000
   7.500   1.3575   0.02637   0.01569  -0.0856   0.3035   1.0000
   7.750   1.3797   0.02689   0.01637  -0.0851   0.2978   1.0000
   8.000   1.4019   0.02725   0.01679  -0.0845   0.2913   1.0000
   8.250   1.4241   0.02759   0.01713  -0.0839   0.2852   1.0000
   8.500   1.4443   0.02807   0.01780  -0.0832   0.2779   1.0000
   8.750   1.4651   0.02839   0.01809  -0.0824   0.2711   1.0000
   9.000   1.4845   0.02898   0.01888  -0.0816   0.2646   1.0000
   9.250   1.5034   0.02947   0.01950  -0.0807   0.2577   1.0000
   9.500   1.5214   0.03003   0.02015  -0.0797   0.2511   1.0000
   9.750   1.5369   0.03064   0.02091  -0.0784   0.2411   1.0000
  10.000   1.5514   0.03137   0.02176  -0.0771   0.2311   1.0000
  10.250   1.5631   0.03221   0.02267  -0.0755   0.2210   1.0000
  10.500   1.5741   0.03321   0.02383  -0.0739   0.2096   1.0000
  11.000   1.5720   0.03653   0.02713  -0.0690   0.1474   1.0000
  11.250   1.5480   0.04070   0.03103  -0.0669   0.1230   1.0000
  11.500   1.5285   0.04540   0.03573  -0.0664   0.1113   1.0000
  12.000   1.4939   0.05588   0.04648  -0.0677   0.0962   1.0000
  12.250   1.4740   0.06204   0.05282  -0.0692   0.0905   1.0000
  12.500   1.4541   0.06842   0.05939  -0.0709   0.0697   1.0000
  12.750   1.4302   0.07552   0.06669  -0.0728   0.0621   1.0000
  13.000   1.4061   0.08278   0.07414  -0.0748   0.0595   1.0000
  13.250   1.3827   0.09005   0.08158  -0.0768   0.0571   1.0000
  13.500   1.3597   0.09748   0.08917  -0.0790   0.0543   1.0000
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