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GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)
Reynolds number: 50,000
Max Cl/Cd: 42.83 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe346-il-50000-n5.txt
Download as CSV file: xf-goe346-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4308   0.12021   0.11296  -0.0138   1.0000   0.0632
  -9.000  -0.4322   0.11894   0.11177  -0.0169   1.0000   0.0637
  -8.750  -0.4336   0.11753   0.11045  -0.0203   1.0000   0.0639
  -8.500  -0.4104   0.10840   0.10126  -0.0152   1.0000   0.0677
  -8.250  -0.4049   0.10532   0.09823  -0.0159   1.0000   0.0710
  -8.000  -0.4029   0.10294   0.09592  -0.0175   1.0000   0.0741
  -7.750  -0.4019   0.10153   0.09460  -0.0222   1.0000   0.0765
  -7.500  -0.3962   0.10051   0.09361  -0.0300   1.0000   0.0774
  -7.250  -0.3885   0.09439   0.08754  -0.0260   1.0000   0.0791
  -7.000  -0.3804   0.09041   0.08360  -0.0245   1.0000   0.0821
  -6.750  -0.3726   0.08732   0.08054  -0.0256   1.0000   0.0855
  -6.500  -0.3638   0.08475   0.07798  -0.0291   1.0000   0.0901
  -6.250  -0.3503   0.08310   0.07627  -0.0367   1.0000   0.0928
  -6.000  -0.3475   0.07822   0.07153  -0.0313   1.0000   0.0969
  -5.750  -0.3362   0.07568   0.06896  -0.0335   1.0000   0.1047
  -5.500  -0.3239   0.07258   0.06583  -0.0361   1.0000   0.1087
  -5.250  -0.3159   0.06935   0.06265  -0.0346   1.0000   0.1136
  -5.000  -0.2966   0.06699   0.06012  -0.0392   1.0000   0.1221
  -4.750  -0.2894   0.06354   0.05673  -0.0370   1.0000   0.1270
  -4.500  -0.2716   0.06087   0.05393  -0.0394   1.0000   0.1373
  -4.000  -0.2438   0.05539   0.04838  -0.0399   1.0000   0.1670
  -3.750  -0.2304   0.05275   0.04573  -0.0395   1.0000   0.1854
  -3.500  -0.2151   0.05023   0.04317  -0.0399   1.0000   0.2125
  -3.250  -0.2025   0.04773   0.04068  -0.0390   1.0000   0.2448
  -3.000  -0.1901   0.04531   0.03829  -0.0380   1.0000   0.2881
  -2.500  -0.1510   0.04058   0.03347  -0.0383   1.0000   0.3411
  -2.000  -0.0385   0.03708   0.02808  -0.0495   1.0000   0.1171
  -1.750  -0.0094   0.03525   0.02590  -0.0500   1.0000   0.0993
  -1.500   0.0331   0.03355   0.02373  -0.0528   0.9949   0.0885
  -1.250   0.0740   0.03187   0.02171  -0.0557   0.9887   0.0838
  -1.000   0.1160   0.03063   0.01998  -0.0583   0.9824   0.0796
  -0.750   0.1557   0.02941   0.01857  -0.0611   0.9761   0.0814
  -0.500   0.1929   0.02846   0.01741  -0.0632   0.9685   0.0834
  -0.250   0.2328   0.02757   0.01626  -0.0656   0.9617   0.0824
   0.000   0.2700   0.02682   0.01530  -0.0673   0.9535   0.0813
   0.250   0.3071   0.02618   0.01449  -0.0689   0.9456   0.0809
   0.500   0.3463   0.02561   0.01375  -0.0709   0.9378   0.0810
   0.750   0.3822   0.02513   0.01320  -0.0723   0.9287   0.0817
   1.000   0.4235   0.02463   0.01266  -0.0748   0.9212   0.0832
   1.250   0.4588   0.02429   0.01233  -0.0762   0.9098   0.0879
   1.500   0.4972   0.02388   0.01193  -0.0779   0.8970   0.0954
   1.750   0.5351   0.02343   0.01151  -0.0794   0.8821   0.1017
   2.000   0.5713   0.02302   0.01113  -0.0802   0.8661   0.1088
   2.250   0.6058   0.02261   0.01082  -0.0807   0.8498   0.1231
   2.500   0.6351   0.02048   0.01057  -0.0801   0.8334   1.0000
   2.750   0.6624   0.02047   0.01038  -0.0790   0.8124   1.0000
   3.000   0.6916   0.02033   0.01014  -0.0781   0.7914   1.0000
   3.250   0.7186   0.02025   0.01000  -0.0769   0.7684   1.0000
   3.500   0.7466   0.02013   0.00987  -0.0758   0.7450   1.0000
   3.750   0.7722   0.02015   0.00988  -0.0744   0.7185   1.0000
   4.000   0.7980   0.02018   0.00992  -0.0731   0.6903   1.0000
   4.250   0.8233   0.02027   0.01003  -0.0718   0.6587   1.0000
   4.500   0.8482   0.02039   0.01013  -0.0703   0.6238   1.0000
   4.750   0.8721   0.02062   0.01032  -0.0688   0.5842   1.0000
   5.000   0.8957   0.02095   0.01054  -0.0672   0.5422   1.0000
   5.250   0.9186   0.02145   0.01094  -0.0657   0.4997   1.0000
   5.500   0.9407   0.02210   0.01146  -0.0643   0.4586   1.0000
   5.750   0.9623   0.02285   0.01211  -0.0630   0.4194   1.0000
   6.000   0.9828   0.02368   0.01279  -0.0617   0.3819   1.0000
   6.250   1.0023   0.02457   0.01358  -0.0603   0.3456   1.0000
   6.500   1.0211   0.02552   0.01438  -0.0590   0.3119   1.0000
   6.750   1.0401   0.02645   0.01529  -0.0577   0.2804   1.0000
   7.000   1.0589   0.02739   0.01626  -0.0565   0.2504   1.0000
   7.250   1.0755   0.02839   0.01729  -0.0552   0.2127   1.0000
   7.500   1.0919   0.02954   0.01843  -0.0538   0.1754   1.0000
   7.750   1.1070   0.03103   0.01986  -0.0523   0.1364   1.0000
   8.000   1.1216   0.03281   0.02152  -0.0507   0.1071   1.0000
   8.250   1.1358   0.03464   0.02328  -0.0491   0.0904   1.0000
   8.500   1.1496   0.03656   0.02519  -0.0474   0.0804   1.0000
   8.750   1.1646   0.03849   0.02730  -0.0458   0.0735   1.0000
   9.000   1.1790   0.04054   0.02950  -0.0442   0.0671   1.0000
   9.250   1.1936   0.04257   0.03172  -0.0427   0.0617   1.0000
   9.500   1.2078   0.04496   0.03411  -0.0412   0.0584   1.0000
   9.750   1.2226   0.04745   0.03705  -0.0397   0.0545   1.0000
  10.000   1.2333   0.04989   0.03975  -0.0381   0.0510   1.0000
  10.250   1.2440   0.05264   0.04269  -0.0367   0.0488   1.0000
  10.500   1.2528   0.05605   0.04632  -0.0351   0.0473   1.0000
  10.750   1.2522   0.05953   0.05032  -0.0329   0.0460   1.0000
  11.000   1.2449   0.06301   0.05420  -0.0305   0.0449   1.0000
  11.250   1.2343   0.06675   0.05829  -0.0285   0.0440   1.0000
  11.500   1.2206   0.07087   0.06272  -0.0273   0.0434   1.0000
  11.750   1.2042   0.07553   0.06768  -0.0270   0.0431   1.0000
  12.000   1.1846   0.08096   0.07337  -0.0279   0.0430   1.0000
  12.250   1.1621   0.08741   0.08007  -0.0303   0.0433   1.0000
  12.500   1.1370   0.09513   0.08801  -0.0343   0.0440   1.0000
  12.750   1.1113   0.10415   0.09719  -0.0399   0.0449   1.0000
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