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GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)
Reynolds number: 100,000
Max Cl/Cd: 61.33 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe346-il-100000.txt
Download as CSV file: xf-goe346-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4343   0.11636   0.11115  -0.0101   1.0000   0.0457
  -9.000  -0.4341   0.11516   0.11002  -0.0137   1.0000   0.0461
  -8.750  -0.4350   0.11387   0.10880  -0.0175   1.0000   0.0464
  -8.500  -0.4313   0.11200   0.10698  -0.0231   1.0000   0.0465
  -8.250  -0.4226   0.10505   0.10005  -0.0195   1.0000   0.0472
  -8.000  -0.4095   0.09935   0.09433  -0.0163   1.0000   0.0485
  -7.750  -0.4031   0.09600   0.09102  -0.0165   1.0000   0.0498
  -7.500  -0.3971   0.09295   0.08800  -0.0177   1.0000   0.0515
  -7.250  -0.3899   0.08993   0.08502  -0.0200   1.0000   0.0535
  -7.000  -0.3812   0.08708   0.08219  -0.0235   1.0000   0.0556
  -6.750  -0.3665   0.08542   0.08050  -0.0318   1.0000   0.0575
  -6.500  -0.3477   0.08459   0.07949  -0.0400   1.0000   0.0582
  -6.250  -0.3466   0.07823   0.07331  -0.0365   1.0000   0.0590
  -6.000  -0.3431   0.07424   0.06940  -0.0333   1.0000   0.0603
  -5.750  -0.3360   0.07120   0.06637  -0.0325   1.0000   0.0621
  -5.500  -0.3265   0.06840   0.06357  -0.0329   1.0000   0.0644
  -5.250  -0.3132   0.06577   0.06089  -0.0345   1.0000   0.0678
  -5.000  -0.2839   0.06409   0.05887  -0.0412   1.0000   0.0719
  -4.750  -0.2820   0.05988   0.05483  -0.0383   1.0000   0.0736
  -4.500  -0.2725   0.05709   0.05205  -0.0373   1.0000   0.0763
  -4.250  -0.2563   0.05462   0.04951  -0.0380   1.0000   0.0807
  -4.000  -0.2260   0.05269   0.04719  -0.0418   1.0000   0.0865
  -3.750  -0.2172   0.04926   0.04387  -0.0405   1.0000   0.0890
  -3.500  -0.1882   0.04901   0.04322  -0.0424   1.0000   0.0995
  -3.250  -0.1764   0.04470   0.03904  -0.0422   1.0000   0.1027
  -3.000  -0.1505   0.04376   0.03776  -0.0434   1.0000   0.1150
  -2.750  -0.1369   0.04033   0.03450  -0.0430   1.0000   0.1194
  -2.500  -0.1132   0.03851   0.03246  -0.0439   1.0000   0.1316
  -2.250  -0.0907   0.03670   0.03052  -0.0446   1.0000   0.1456
  -2.000  -0.0690   0.03479   0.02856  -0.0451   1.0000   0.1617
  -1.750  -0.0458   0.03322   0.02687  -0.0459   1.0000   0.1890
  -1.500  -0.0245   0.03139   0.02508  -0.0464   1.0000   0.2241
  -1.250  -0.0034   0.03016   0.02384  -0.0468   1.0000   0.2903
  -1.000   0.0178   0.02769   0.02156  -0.0469   1.0000   0.3418
  -0.750   0.0584   0.02597   0.01978  -0.0502   0.9961   0.3944
  -0.500   0.1052   0.02413   0.01785  -0.0544   0.9909   0.4169
   0.000   0.2280   0.02427   0.01634  -0.0639   0.9751   0.1972
   0.250   0.2788   0.02359   0.01522  -0.0669   0.9683   0.1490
   0.500   0.3278   0.02286   0.01420  -0.0698   0.9586   0.1237
   0.750   0.3760   0.02210   0.01326  -0.0729   0.9466   0.1120
   1.000   0.4246   0.02106   0.01225  -0.0763   0.9355   0.1070
   1.250   0.4790   0.02007   0.01130  -0.0807   0.9274   0.1057
   1.500   0.5233   0.01926   0.01059  -0.0831   0.9145   0.1118
   1.750   0.5653   0.01849   0.00985  -0.0846   0.9007   0.1142
   2.000   0.6034   0.01779   0.00918  -0.0855   0.8863   0.1205
   2.250   0.6375   0.01729   0.00871  -0.0856   0.8715   0.1333
   2.500   0.6677   0.01513   0.00841  -0.0849   0.8570   1.0000
   2.750   0.6967   0.01496   0.00804  -0.0837   0.8405   1.0000
   3.000   0.7245   0.01475   0.00773  -0.0824   0.8231   1.0000
   3.250   0.7488   0.01464   0.00759  -0.0806   0.8010   1.0000
   3.500   0.7748   0.01442   0.00735  -0.0789   0.7795   1.0000
   3.750   0.7992   0.01432   0.00724  -0.0772   0.7532   1.0000
   4.000   0.8238   0.01426   0.00714  -0.0754   0.7240   1.0000
   4.250   0.8478   0.01423   0.00703  -0.0735   0.6877   1.0000
   4.500   0.8701   0.01430   0.00701  -0.0714   0.6376   1.0000
   4.750   0.8918   0.01454   0.00700  -0.0693   0.5769   1.0000
   5.000   0.9124   0.01510   0.00717  -0.0673   0.5112   1.0000
   5.250   0.9326   0.01582   0.00755  -0.0656   0.4458   1.0000
   5.500   0.9530   0.01659   0.00801  -0.0642   0.3929   1.0000
   5.750   0.9747   0.01735   0.00858  -0.0631   0.3541   1.0000
   6.000   0.9964   0.01811   0.00920  -0.0621   0.3220   1.0000
   6.250   1.0180   0.01882   0.00983  -0.0611   0.2909   1.0000
   6.500   1.0392   0.01944   0.01045  -0.0601   0.2534   1.0000
   6.750   1.0578   0.02034   0.01121  -0.0588   0.1912   1.0000
   7.000   1.0717   0.02234   0.01258  -0.0567   0.1144   1.0000
   7.250   1.0891   0.02385   0.01391  -0.0551   0.0944   1.0000
   7.500   1.1072   0.02544   0.01548  -0.0535   0.0854   1.0000
   7.750   1.1249   0.02731   0.01722  -0.0520   0.0784   1.0000
   8.000   1.1463   0.02878   0.01887  -0.0508   0.0722   1.0000
   8.250   1.1682   0.03081   0.02085  -0.0498   0.0683   1.0000
   8.500   1.1917   0.03332   0.02349  -0.0490   0.0652   1.0000
   8.750   1.2131   0.03525   0.02573  -0.0479   0.0615   1.0000
   9.000   1.2344   0.03777   0.02850  -0.0468   0.0594   1.0000
   9.250   1.2539   0.04072   0.03178  -0.0456   0.0582   1.0000
   9.500   1.2706   0.04393   0.03525  -0.0443   0.0568   1.0000
   9.750   1.2824   0.04900   0.04059  -0.0431   0.0552   1.0000
  10.000   1.2871   0.05211   0.04425  -0.0405   0.0546   1.0000
  10.250   1.2902   0.05656   0.04913  -0.0383   0.0548   1.0000
  10.500   1.2922   0.06145   0.05439  -0.0363   0.0553   1.0000
  10.750   1.2848   0.06419   0.05770  -0.0329   0.0565   1.0000
  11.000   1.2429   0.06926   0.06349  -0.0281   0.0585   1.0000
  11.250   1.2088   0.07433   0.06889  -0.0257   0.0597   1.0000
  11.500   1.1767   0.08015   0.07496  -0.0259   0.0607   1.0000
  11.750   1.1442   0.08721   0.08221  -0.0287   0.0616   1.0000
  12.000   1.1106   0.09615   0.09129  -0.0342   0.0626   1.0000
  12.250   1.0802   0.10681   0.10202  -0.0414   0.0641   1.0000
  12.500   1.0661   0.11505   0.11023  -0.0453   0.0656   1.0000
  12.750   1.0378   0.13291   0.12809  -0.0536   0.0790   1.0000
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