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GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il)
Reynolds number: 100,000
Max Cl/Cd: 58.38 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe117-il-100000.txt
Download as CSV file: xf-goe117-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 117 (MVA MK.4) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2539   0.09320   0.08885  -0.0380   1.0000   0.1012
  -8.500  -0.2638   0.09140   0.08715  -0.0376   1.0000   0.1047
  -8.250  -0.2859   0.09090   0.08678  -0.0368   1.0000   0.1060
  -8.000  -0.3107   0.09072   0.08674  -0.0349   1.0000   0.1064
  -7.750  -0.2899   0.08522   0.08123  -0.0318   1.0000   0.1098
  -7.500  -0.2952   0.08349   0.07956  -0.0291   1.0000   0.1129
  -7.250  -0.3091   0.08231   0.07847  -0.0266   1.0000   0.1154
  -7.000  -0.3295   0.08163   0.07790  -0.0241   1.0000   0.1172
  -6.750  -0.3552   0.08137   0.07776  -0.0211   1.0000   0.1181
  -6.500  -0.3625   0.07746   0.07391  -0.0306   0.9935   0.1205
  -6.250  -0.3322   0.07252   0.06894  -0.0269   0.9898   0.1266
  -6.000  -0.4202   0.08101   0.07718  -0.0277   1.0000   0.1214
  -5.750  -0.4098   0.07833   0.07452  -0.0251   0.9982   0.1254
  -5.500  -0.3710   0.07234   0.06842  -0.0380   0.9885   0.1362
  -5.250  -0.3332   0.06736   0.06330  -0.0471   0.9796   0.1499
  -5.000  -0.2077   0.04468   0.04064  -0.0672   0.9441   0.1773
  -4.750  -0.1845   0.04032   0.03626  -0.0679   0.9345   0.1803
  -4.500  -0.1918   0.03460   0.02804  -0.0839   0.9569   0.0806
  -4.250  -0.1576   0.03034   0.02325  -0.0867   0.9472   0.0819
  -4.000  -0.1163   0.02711   0.01940  -0.0897   0.9397   0.0828
  -3.750  -0.0737   0.02477   0.01662  -0.0926   0.9318   0.0852
  -3.500  -0.0335   0.02330   0.01477  -0.0948   0.9222   0.0920
  -3.250   0.0136   0.02151   0.01279  -0.0981   0.9165   0.0967
  -3.000   0.0524   0.02055   0.01173  -0.1000   0.9063   0.1054
  -2.750   0.1010   0.01951   0.01075  -0.1036   0.9013   0.1229
  -2.500   0.1359   0.01855   0.00994  -0.1046   0.8899   0.1655
  -2.250   0.1718   0.01847   0.01004  -0.1059   0.8790   0.2684
  -2.000   0.2135   0.01837   0.00982  -0.1083   0.8722   0.3150
  -1.750   0.2428   0.01820   0.00962  -0.1084   0.8599   0.3479
  -1.500   0.2723   0.01791   0.00934  -0.1086   0.8484   0.3753
  -1.250   0.3026   0.01752   0.00904  -0.1089   0.8382   0.4064
  -1.000   0.3360   0.01700   0.00862  -0.1096   0.8300   0.4421
  -0.750   0.3621   0.01670   0.00846  -0.1091   0.8188   0.4885
  -0.500   0.4199   0.01495   0.00797  -0.1143   0.8126   1.0000
  -0.250   0.4478   0.01511   0.00783  -0.1141   0.8027   1.0000
   0.000   0.4724   0.01536   0.00789  -0.1135   0.7925   1.0000
   0.250   0.5016   0.01546   0.00780  -0.1135   0.7853   1.0000
   0.500   0.5252   0.01574   0.00797  -0.1128   0.7756   1.0000
   0.750   0.5506   0.01600   0.00811  -0.1123   0.7676   1.0000
   1.000   0.5772   0.01619   0.00821  -0.1120   0.7602   1.0000
   1.250   0.6011   0.01652   0.00849  -0.1114   0.7521   1.0000
   1.500   0.6285   0.01669   0.00858  -0.1111   0.7455   1.0000
   1.750   0.6516   0.01707   0.00895  -0.1104   0.7376   1.0000
   2.000   0.6792   0.01725   0.00910  -0.1102   0.7313   1.0000
   2.250   0.7020   0.01766   0.00953  -0.1095   0.7235   1.0000
   2.500   0.7296   0.01784   0.00968  -0.1093   0.7173   1.0000
   2.750   0.7522   0.01829   0.01018  -0.1085   0.7097   1.0000
   3.000   0.7795   0.01850   0.01043  -0.1083   0.7035   1.0000
   3.250   0.8023   0.01898   0.01098  -0.1076   0.6962   1.0000
   3.500   0.8288   0.01927   0.01131  -0.1073   0.6899   1.0000
   3.750   0.8522   0.01976   0.01190  -0.1066   0.6831   1.0000
   4.000   0.8774   0.02014   0.01241  -0.1062   0.6765   1.0000
   4.250   0.9013   0.02051   0.01289  -0.1054   0.6680   1.0000
   4.500   0.9299   0.01988   0.01225  -0.1039   0.6500   1.0000
   4.750   0.9579   0.01917   0.01147  -0.1021   0.6273   1.0000
   5.000   0.9819   0.01855   0.01081  -0.0998   0.5985   1.0000
   5.250   1.0015   0.01807   0.01032  -0.0968   0.5651   1.0000
   5.500   1.0105   0.01731   0.00945  -0.0914   0.5003   1.0000
   5.750   0.9944   0.01866   0.00941  -0.0830   0.2526   1.0000
   6.000   0.9815   0.02197   0.01163  -0.0773   0.1046   1.0000
   6.250   0.9859   0.02367   0.01338  -0.0736   0.0893   1.0000
   6.500   0.9933   0.02498   0.01484  -0.0703   0.0806   1.0000
   6.750   0.9938   0.02654   0.01647  -0.0663   0.0745   1.0000
   7.000   0.9998   0.02778   0.01778  -0.0629   0.0690   1.0000
   7.250   1.0074   0.02936   0.01928  -0.0598   0.0655   1.0000
   7.500   1.0422   0.03175   0.02145  -0.0604   0.0619   1.0000
   7.750   1.0751   0.03345   0.02326  -0.0607   0.0572   1.0000
   8.000   1.1203   0.03614   0.02599  -0.0626   0.0552   1.0000
   8.250   1.1613   0.03928   0.02943  -0.0636   0.0561   1.0000
   8.500   1.1927   0.04247   0.03295  -0.0633   0.0573   1.0000
   8.750   1.2158   0.04548   0.03629  -0.0621   0.0572   1.0000
   9.000   1.2433   0.05044   0.04153  -0.0617   0.0614   1.0000
  12.500   0.7754   0.14363   0.13941  -0.0654   0.2247   1.0000
  12.750   0.7720   0.14619   0.14198  -0.0659   0.2116   1.0000
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