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GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il)
Reynolds number: 500,000
Max Cl/Cd: 81.42 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe116-il-500000-n5.txt
Download as CSV file: xf-goe116-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4008   0.09408   0.09201  -0.0315   0.9601   0.0051
  -9.250  -0.3939   0.09087   0.08870  -0.0329   0.9063   0.0047
  -9.000  -0.3959   0.08697   0.08466  -0.0340   0.8668   0.0046
  -8.500  -0.3984   0.07780   0.07533  -0.0386   0.8260   0.0043
  -8.250  -0.4018   0.07218   0.06967  -0.0421   0.8121   0.0042
  -8.000  -0.4064   0.06499   0.06243  -0.0487   0.8004   0.0041
  -7.750  -0.4046   0.05368   0.05100  -0.0632   0.7903   0.0040
  -7.500  -0.3884   0.03738   0.03418  -0.0830   0.7823   0.0038
  -7.250  -0.3700   0.03108   0.02731  -0.0882   0.7743   0.0037
  -7.000  -0.3493   0.02704   0.02277  -0.0902   0.7673   0.0036
  -6.750  -0.3265   0.02398   0.01925  -0.0911   0.7605   0.0037
  -6.500  -0.3021   0.02157   0.01644  -0.0916   0.7543   0.0037
  -6.250  -0.2766   0.01962   0.01414  -0.0918   0.7478   0.0039
  -6.000  -0.2505   0.01799   0.01220  -0.0919   0.7419   0.0041
  -5.750  -0.2237   0.01666   0.01060  -0.0920   0.7356   0.0044
  -5.500  -0.1961   0.01590   0.00961  -0.0920   0.7300   0.0048
  -5.250  -0.1696   0.01471   0.00829  -0.0923   0.7247   0.0054
  -5.000  -0.1421   0.01393   0.00738  -0.0924   0.7193   0.0058
  -4.750  -0.1144   0.01317   0.00647  -0.0925   0.7142   0.0060
  -4.500  -0.0863   0.01250   0.00568  -0.0927   0.7089   0.0064
  -4.250  -0.0581   0.01194   0.00499  -0.0929   0.7039   0.0069
  -4.000  -0.0297   0.01150   0.00440  -0.0930   0.6993   0.0076
  -3.750  -0.0013   0.01093   0.00368  -0.0932   0.6944   0.0090
  -3.500   0.0272   0.01056   0.00314  -0.0934   0.6897   0.0106
  -3.250   0.0557   0.01032   0.00275  -0.0935   0.6854   0.0124
  -3.000   0.0844   0.01014   0.00246  -0.0937   0.6808   0.0150
  -2.750   0.1129   0.00993   0.00221  -0.0938   0.6761   0.0243
  -2.500   0.1406   0.00952   0.00214  -0.0941   0.6721   0.1320
  -2.250   0.1693   0.00956   0.00219  -0.0944   0.6676   0.1395
  -2.000   0.1981   0.00976   0.00232  -0.0945   0.6631   0.1465
  -1.750   0.2264   0.00968   0.00223  -0.0947   0.6590   0.1508
  -1.500   0.2549   0.00960   0.00212  -0.0949   0.6547   0.1518
  -1.250   0.2834   0.00954   0.00203  -0.0952   0.6502   0.1528
  -1.000   0.3118   0.00949   0.00195  -0.0953   0.6462   0.1538
  -0.750   0.3402   0.00945   0.00188  -0.0955   0.6424   0.1549
  -0.500   0.3687   0.00940   0.00183  -0.0958   0.6384   0.1560
  -0.250   0.3972   0.00937   0.00179  -0.0960   0.6343   0.1572
   0.000   0.4255   0.00936   0.00176  -0.0962   0.6308   0.1585
   0.250   0.4540   0.00934   0.00175  -0.0964   0.6271   0.1597
   0.500   0.4825   0.00932   0.00175  -0.0966   0.6231   0.1605
   0.750   0.5109   0.00929   0.00174  -0.0968   0.6193   0.1621
   1.000   0.5392   0.00927   0.00174  -0.0970   0.6158   0.1638
   1.250   0.5676   0.00924   0.00177  -0.0972   0.6106   0.1655
   1.500   0.5958   0.00924   0.00180  -0.0974   0.6044   0.1674
   1.750   0.6240   0.00925   0.00184  -0.0976   0.5988   0.1694
   2.000   0.6523   0.00926   0.00190  -0.0977   0.5933   0.1716
   2.250   0.6803   0.00930   0.00196  -0.0979   0.5868   0.1737
   2.500   0.7085   0.00930   0.00204  -0.0980   0.5789   0.1763
   2.750   0.7364   0.00932   0.00212  -0.0981   0.5712   0.1801
   3.000   0.7637   0.00938   0.00220  -0.0981   0.5492   0.1845
   3.500   0.8133   0.01005   0.00251  -0.0974   0.4375   0.1979
   3.750   0.8234   0.01237   0.00363  -0.0954   0.1874   0.2072
   4.000   0.8384   0.01401   0.00460  -0.0938   0.0193   0.2280
   4.250   0.8591   0.01272   0.00511  -0.0928   0.0140   1.0000
   4.500   0.8837   0.01317   0.00561  -0.0923   0.0100   1.0000
   4.750   0.9074   0.01373   0.00627  -0.0916   0.0085   1.0000
   5.000   0.9308   0.01427   0.00688  -0.0910   0.0077   1.0000
   5.250   0.9539   0.01481   0.00746  -0.0903   0.0067   1.0000
   5.500   0.9761   0.01540   0.00809  -0.0896   0.0057   1.0000
   5.750   0.9944   0.01639   0.00917  -0.0881   0.0052   1.0000
   6.000   1.0136   0.01723   0.01009  -0.0868   0.0049   1.0000
   6.250   1.0308   0.01823   0.01117  -0.0851   0.0046   1.0000
   6.500   1.0464   0.01934   0.01236  -0.0832   0.0044   1.0000
   6.750   1.0612   0.02055   0.01364  -0.0812   0.0042   1.0000
   7.000   1.0760   0.02185   0.01502  -0.0791   0.0041   1.0000
   7.250   1.0928   0.02297   0.01620  -0.0776   0.0038   1.0000
   7.500   1.1105   0.02380   0.01711  -0.0763   0.0035   1.0000
   7.750   1.1260   0.02536   0.01874  -0.0747   0.0032   1.0000
   8.000   1.1460   0.02683   0.02038  -0.0733   0.0030   1.0000
   8.250   1.1692   0.02916   0.02292  -0.0723   0.0028   1.0000
   8.500   1.1930   0.03200   0.02600  -0.0713   0.0026   1.0000
   8.750   1.2127   0.03501   0.02929  -0.0699   0.0025   1.0000
   9.000   1.2282   0.03827   0.03285  -0.0679   0.0024   1.0000
   9.250   1.2385   0.04169   0.03658  -0.0655   0.0025   1.0000
   9.500   1.2444   0.04522   0.04041  -0.0626   0.0025   1.0000
   9.750   1.2452   0.04871   0.04420  -0.0594   0.0025   1.0000
  10.000   1.2403   0.05198   0.04772  -0.0557   0.0026   1.0000
  10.250   1.2306   0.05503   0.05099  -0.0518   0.0026   1.0000
  10.500   1.2183   0.05823   0.05440  -0.0484   0.0027   1.0000
  10.750   1.2043   0.06166   0.05802  -0.0457   0.0027   1.0000
  11.000   1.1890   0.06541   0.06197  -0.0437   0.0027   1.0000
  11.250   1.1730   0.06945   0.06618  -0.0425   0.0028   1.0000
  11.500   1.1556   0.07389   0.07079  -0.0419   0.0028   1.0000
  11.750   1.1378   0.07866   0.07572  -0.0420   0.0028   1.0000
  12.000   1.1190   0.08393   0.08115  -0.0429   0.0029   1.0000
  12.250   1.1001   0.08952   0.08688  -0.0444   0.0029   1.0000
  12.500   1.0808   0.09568   0.09317  -0.0466   0.0029   1.0000
  12.750   1.0611   0.10242   0.10004  -0.0497   0.0029   1.0000
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