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GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il)
Reynolds number: 50,000
Max Cl/Cd: 40.68 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe118-il-50000-n5.txt
Download as CSV file: xf-goe118-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 118 (MVA MK.7) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2777   0.10752   0.10181  -0.0363   1.0000   0.0882
  -7.500  -0.2923   0.10713   0.10158  -0.0335   1.0000   0.0893
  -7.250  -0.3118   0.10728   0.10189  -0.0299   1.0000   0.0900
  -7.000  -0.3029   0.10550   0.10017  -0.0374   0.9891   0.0917
  -6.750  -0.2778   0.10227   0.09685  -0.0494   0.9753   0.0924
  -6.250  -0.2322   0.09214   0.08669  -0.0591   0.9576   0.0929
  -6.000  -0.2061   0.08787   0.08236  -0.0665   0.9468   0.0928
  -5.750  -0.1763   0.08349   0.07785  -0.0742   0.9374   0.0923
  -5.250  -0.1216   0.07037   0.06453  -0.0838   0.9212   0.0495
  -5.000  -0.0908   0.06566   0.05972  -0.0890   0.9149   0.0479
  -4.750  -0.0637   0.06138   0.05533  -0.0940   0.9046   0.0459
  -4.500  -0.0281   0.05619   0.04993  -0.1011   0.8961   0.0429
  -4.250   0.0184   0.04966   0.04295  -0.1104   0.8889   0.0392
  -4.000   0.0507   0.04559   0.03859  -0.1144   0.8803   0.0383
  -3.750   0.0916   0.04092   0.03342  -0.1196   0.8743   0.0375
  -3.500   0.1268   0.03685   0.02878  -0.1230   0.8659   0.0371
  -3.250   0.1690   0.03266   0.02374  -0.1266   0.8605   0.0384
  -3.000   0.2005   0.03027   0.02081  -0.1279   0.8520   0.0419
  -2.750   0.2376   0.02816   0.01816  -0.1294   0.8464   0.0457
  -2.500   0.2665   0.02666   0.01616  -0.1292   0.8376   0.0498
  -2.250   0.3009   0.02591   0.01520  -0.1301   0.8313   0.0668
  -2.000   0.3306   0.02519   0.01419  -0.1300   0.8226   0.1027
  -1.750   0.3604   0.02517   0.01396  -0.1305   0.8148   0.1767
  -1.500   0.3890   0.02502   0.01360  -0.1309   0.8069   0.2186
  -1.250   0.4169   0.02480   0.01307  -0.1308   0.7988   0.2238
  -1.000   0.4470   0.02450   0.01253  -0.1310   0.7919   0.2314
  -0.750   0.4733   0.02440   0.01228  -0.1309   0.7833   0.2418
  -0.500   0.5037   0.02409   0.01185  -0.1312   0.7769   0.2619
  -0.250   0.5289   0.02388   0.01187  -0.1311   0.7680   0.3171
   0.000   0.5542   0.02223   0.01154  -0.1299   0.7621   1.0000
   0.250   0.5784   0.02265   0.01160  -0.1294   0.7527   1.0000
   0.500   0.6073   0.02283   0.01146  -0.1294   0.7460   1.0000
   0.750   0.6322   0.02320   0.01162  -0.1291   0.7372   1.0000
   1.000   0.6586   0.02350   0.01174  -0.1288   0.7295   1.0000
   1.250   0.6853   0.02377   0.01185  -0.1286   0.7218   1.0000
   1.500   0.7098   0.02417   0.01215  -0.1282   0.7133   1.0000
   1.750   0.7378   0.02436   0.01223  -0.1281   0.7064   1.0000
   2.000   0.7607   0.02486   0.01273  -0.1276   0.6972   1.0000
   2.250   0.7898   0.02499   0.01278  -0.1275   0.6910   1.0000
   2.500   0.8113   0.02558   0.01340  -0.1269   0.6814   1.0000
   2.750   0.8384   0.02584   0.01365  -0.1267   0.6746   1.0000
   3.250   0.8856   0.02681   0.01481  -0.1257   0.6581   1.0000
   3.500   0.9106   0.02722   0.01531  -0.1253   0.6506   1.0000
   3.750   0.9328   0.02783   0.01607  -0.1247   0.6423   1.0000
   4.000   0.9592   0.02817   0.01660  -0.1243   0.6356   1.0000
   4.250   0.9795   0.02895   0.01759  -0.1236   0.6269   1.0000
   4.500   1.0066   0.02927   0.01812  -0.1233   0.6208   1.0000
   4.750   1.0251   0.03021   0.01934  -0.1223   0.6119   1.0000
   5.000   1.0508   0.03028   0.01974  -0.1214   0.6018   1.0000
   5.250   1.0730   0.02756   0.01699  -0.1163   0.5548   1.0000
   5.500   1.0837   0.02664   0.01595  -0.1114   0.4973   1.0000
   5.750   1.0914   0.02688   0.01599  -0.1072   0.4258   1.0000
   6.000   1.0861   0.02861   0.01660  -0.1020   0.2684   1.0000
   6.250   1.0615   0.03280   0.01947  -0.0967   0.0803   1.0000
   6.500   1.0584   0.03540   0.02189  -0.0935   0.0482   1.0000
   6.750   1.0617   0.03754   0.02417  -0.0912   0.0431   1.0000
   7.000   1.0614   0.04007   0.02692  -0.0889   0.0394   1.0000
   7.250   1.0627   0.04255   0.02966  -0.0871   0.0363   1.0000
   7.500   1.0608   0.04545   0.03278  -0.0855   0.0341   1.0000
   7.750   1.0570   0.04865   0.03619  -0.0841   0.0329   1.0000
   8.000   1.0519   0.05210   0.03984  -0.0829   0.0322   1.0000
   8.250   1.0505   0.05520   0.04314  -0.0817   0.0317   1.0000
   8.500   1.0497   0.05823   0.04639  -0.0805   0.0312   1.0000
   8.750   1.0503   0.06107   0.04942  -0.0792   0.0304   1.0000
   9.000   1.0532   0.06354   0.05207  -0.0775   0.0293   1.0000
   9.250   1.0603   0.06541   0.05408  -0.0753   0.0276   1.0000
   9.500   1.0822   0.06557   0.05428  -0.0715   0.0258   1.0000
   9.750   1.2536   0.06262   0.05170  -0.0684   0.0254   1.0000
  10.000   1.3175   0.06927   0.05862  -0.0720   0.0242   1.0000
  10.250   1.3338   0.07380   0.06350  -0.0710   0.0240   1.0000
  10.500   1.3328   0.07623   0.06631  -0.0679   0.0243   1.0000
  10.750   1.3186   0.07800   0.06851  -0.0637   0.0247   1.0000
  11.000   1.3057   0.08045   0.07139  -0.0604   0.0253   1.0000
  11.250   1.2947   0.08366   0.07498  -0.0580   0.0260   1.0000
  11.500   1.2820   0.08729   0.07895  -0.0562   0.0266   1.0000
  11.750   1.2684   0.09126   0.08323  -0.0550   0.0272   1.0000
  12.000   1.2539   0.09552   0.08777  -0.0544   0.0277   1.0000
  12.250   1.2384   0.10006   0.09257  -0.0543   0.0281   1.0000
  12.500   1.2222   0.10488   0.09762  -0.0549   0.0285   1.0000
  12.750   1.2055   0.10999   0.10295  -0.0560   0.0288   1.0000
  13.000   1.1886   0.11541   0.10857  -0.0578   0.0291   1.0000
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