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GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il)
Reynolds number: 50,000
Max Cl/Cd: 37.26 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe116-il-50000-n5.txt
Download as CSV file: xf-goe116-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 116 (MVA MK.3) 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  -0.3784   0.10472   0.09822  -0.0356   1.0000   0.0373
  -9.000  -0.3768   0.10073   0.09431  -0.0372   1.0000   0.0365
  -8.750  -0.3766   0.09662   0.09030  -0.0391   1.0000   0.0356
  -8.500  -0.3785   0.09235   0.08615  -0.0411   1.0000   0.0348
  -8.250  -0.3838   0.08787   0.08181  -0.0432   1.0000   0.0340
  -8.000  -0.3966   0.08242   0.07653  -0.0463   1.0000   0.0329
  -7.750  -0.4004   0.07890   0.07314  -0.0475   1.0000   0.0326
  -7.500  -0.4069   0.07551   0.06990  -0.0484   1.0000   0.0324
  -7.250  -0.4164   0.07234   0.06685  -0.0487   1.0000   0.0322
  -7.000  -0.4279   0.06931   0.06391  -0.0484   1.0000   0.0319
  -6.750  -0.4244   0.06354   0.05810  -0.0535   0.9952   0.0315
  -6.500  -0.3991   0.05324   0.04740  -0.0658   0.9835   0.0308
  -6.250  -0.3698   0.04475   0.03816  -0.0754   0.9736   0.0304
  -6.000  -0.3357   0.03904   0.03163  -0.0815   0.9659   0.0305
  -5.750  -0.3033   0.03545   0.02737  -0.0847   0.9572   0.0310
  -5.500  -0.2681   0.03280   0.02411  -0.0876   0.9499   0.0325
  -5.250  -0.2337   0.03058   0.02155  -0.0904   0.9425   0.0361
  -5.000  -0.1981   0.02883   0.01938  -0.0927   0.9355   0.0400
  -4.750  -0.1621   0.02715   0.01742  -0.0950   0.9286   0.0450
  -4.500  -0.1273   0.02566   0.01604  -0.0969   0.9214   0.0650
  -4.250  -0.0909   0.02757   0.01773  -0.0984   0.9133   0.1646
  -4.000  -0.0615   0.02823   0.01794  -0.0990   0.9046   0.1911
  -3.750  -0.0274   0.02809   0.01747  -0.1004   0.8986   0.2064
  -3.500  -0.0011   0.02827   0.01750  -0.1006   0.8900   0.2299
  -3.250   0.0325   0.02771   0.01665  -0.1020   0.8845   0.2384
  -3.000   0.0606   0.02726   0.01583  -0.1024   0.8765   0.2422
  -2.750   0.0944   0.02672   0.01490  -0.1037   0.8710   0.2449
  -2.500   0.1218   0.02640   0.01430  -0.1039   0.8632   0.2472
  -2.250   0.1531   0.02598   0.01369  -0.1047   0.8577   0.2508
  -2.000   0.1797   0.02580   0.01334  -0.1047   0.8502   0.2554
  -1.750   0.2109   0.02557   0.01286  -0.1054   0.8446   0.2599
  -1.500   0.2382   0.02544   0.01261  -0.1055   0.8378   0.2629
  -1.250   0.2676   0.02527   0.01231  -0.1058   0.8318   0.2663
  -1.000   0.2954   0.02519   0.01213  -0.1060   0.8256   0.2702
  -0.750   0.3230   0.02519   0.01202  -0.1061   0.8191   0.2746
  -0.500   0.3528   0.02504   0.01185  -0.1065   0.8142   0.2798
  -0.250   0.3769   0.02517   0.01199  -0.1063   0.8066   0.2873
   0.000   0.4064   0.02506   0.01193  -0.1067   0.8018   0.2969
   0.250   0.4302   0.02523   0.01217  -0.1064   0.7945   0.3073
   0.500   0.4581   0.02520   0.01225  -0.1066   0.7890   0.3213
   0.750   0.4838   0.02525   0.01249  -0.1066   0.7829   0.3424
   1.000   0.5088   0.02507   0.01282  -0.1066   0.7766   0.4104
   1.500   0.5569   0.02457   0.01344  -0.1050   0.7643   1.0000
   1.750   0.5853   0.02488   0.01369  -0.1050   0.7595   1.0000
   2.000   0.6073   0.02552   0.01431  -0.1046   0.7523   1.0000
   2.250   0.6337   0.02594   0.01473  -0.1045   0.7467   1.0000
   2.500   0.6582   0.02649   0.01530  -0.1042   0.7408   1.0000
   2.750   0.6812   0.02712   0.01602  -0.1038   0.7341   1.0000
   3.000   0.7102   0.02743   0.01641  -0.1039   0.7299   1.0000
   3.250   0.7279   0.02839   0.01748  -0.1031   0.7216   1.0000
   3.500   0.7554   0.02880   0.01807  -0.1031   0.7169   1.0000
   3.750   0.7742   0.02975   0.01917  -0.1023   0.7093   1.0000
   4.000   0.7994   0.03032   0.01993  -0.1021   0.7038   1.0000
   4.250   0.8204   0.03117   0.02099  -0.1015   0.6971   1.0000
   4.500   0.8425   0.03197   0.02207  -0.1010   0.6905   1.0000
   4.750   0.8680   0.03258   0.02296  -0.1007   0.6852   1.0000
   5.000   0.8847   0.03372   0.02441  -0.0997   0.6768   1.0000
   5.250   0.9293   0.02808   0.01893  -0.0930   0.6221   1.0000
   5.500   0.9476   0.02600   0.01698  -0.0874   0.5624   1.0000
   5.750   0.9478   0.02544   0.01507  -0.0795   0.3075   1.0000
   6.000   0.9233   0.02983   0.01761  -0.0742   0.0878   1.0000
   6.250   0.9217   0.03239   0.01985  -0.0711   0.0555   1.0000
   6.500   0.9264   0.03418   0.02173  -0.0684   0.0484   1.0000
   6.750   0.9305   0.03614   0.02380  -0.0659   0.0440   1.0000
   7.000   0.9349   0.03817   0.02597  -0.0637   0.0404   1.0000
   7.250   0.9401   0.04020   0.02817  -0.0618   0.0370   1.0000
   7.500   0.9436   0.04246   0.03053  -0.0599   0.0346   1.0000
   7.750   0.9485   0.04465   0.03285  -0.0580   0.0334   1.0000
   8.000   0.9585   0.04646   0.03486  -0.0559   0.0325   1.0000
   8.250   0.9757   0.04787   0.03646  -0.0535   0.0315   1.0000
   8.500   1.0125   0.04865   0.03743  -0.0513   0.0290   1.0000
   8.750   1.0828   0.05095   0.03988  -0.0526   0.0259   1.0000
   9.000   1.1336   0.05513   0.04436  -0.0544   0.0256   1.0000
   9.250   1.1577   0.05871   0.04832  -0.0537   0.0256   1.0000
   9.500   1.1722   0.06200   0.05202  -0.0521   0.0257   1.0000
   9.750   1.1802   0.06521   0.05565  -0.0500   0.0260   1.0000
  10.000   1.1832   0.06858   0.05941  -0.0477   0.0261   1.0000
  10.250   1.1789   0.07180   0.06301  -0.0449   0.0262   1.0000
  10.500   1.1702   0.07505   0.06659  -0.0422   0.0263   1.0000
  10.750   1.1581   0.07843   0.07030  -0.0398   0.0264   1.0000
  11.000   1.1432   0.08209   0.07427  -0.0381   0.0266   1.0000
  11.250   1.1264   0.08613   0.07861  -0.0371   0.0269   1.0000
  11.500   1.1082   0.09063   0.08339  -0.0369   0.0271   1.0000
  11.750   1.0886   0.09563   0.08864  -0.0376   0.0275   1.0000
  12.000   1.0683   0.10117   0.09440  -0.0391   0.0279   1.0000
  12.250   1.0478   0.10728   0.10071  -0.0416   0.0283   1.0000
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