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GOE 363 AIRFOIL (goe363-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 363 AIRFOIL (goe363-il)
Reynolds number: 500,000
Max Cl/Cd: 89.5 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe363-il-500000.txt
Download as CSV file: xf-goe363-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 363 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1700   0.08609   0.08398  -0.0590   0.9749   0.0253
  -8.250  -0.1650   0.07972   0.07760  -0.0682   0.9586   0.0268
  -8.000  -0.1610   0.07553   0.07340  -0.0718   0.9431   0.0269
  -7.750  -0.1600   0.07102   0.06887  -0.0737   0.9310   0.0274
  -7.500  -0.1483   0.06912   0.06695  -0.0740   0.9221   0.0278
  -7.250  -0.1355   0.06674   0.06453  -0.0757   0.9126   0.0284
  -7.000  -0.1211   0.06363   0.06139  -0.0790   0.9032   0.0291
  -6.750  -0.1048   0.05963   0.05732  -0.0840   0.8946   0.0304
  -6.500  -0.0933   0.02602   0.02216  -0.1158   0.8825   0.0271
  -6.250  -0.0718   0.02367   0.01975  -0.1163   0.8771   0.0283
  -6.000  -0.0441   0.02534   0.02170  -0.1156   0.8709   0.0302
  -5.750  -0.0229   0.02020   0.01576  -0.1165   0.8650   0.0299
  -5.500   0.0022   0.01842   0.01363  -0.1164   0.8580   0.0308
  -5.250   0.0287   0.01738   0.01229  -0.1161   0.8515   0.0321
  -5.000   0.0562   0.01703   0.01167  -0.1158   0.8449   0.0332
  -4.750   0.0810   0.01475   0.00909  -0.1155   0.8379   0.0342
  -4.500   0.1075   0.01388   0.00811  -0.1152   0.8305   0.0352
  -4.250   0.1345   0.01335   0.00751  -0.1149   0.8223   0.0367
  -4.000   0.1618   0.01284   0.00689  -0.1146   0.8152   0.0380
  -3.750   0.1892   0.01229   0.00623  -0.1143   0.8076   0.0389
  -3.500   0.2168   0.01184   0.00566  -0.1139   0.8005   0.0398
  -3.250   0.2444   0.01156   0.00531  -0.1136   0.7918   0.0407
  -3.000   0.2712   0.01082   0.00448  -0.1132   0.7836   0.0420
  -2.750   0.2984   0.01037   0.00398  -0.1128   0.7743   0.0433
  -2.500   0.3259   0.01005   0.00364  -0.1126   0.7654   0.0448
  -2.250   0.3534   0.00981   0.00334  -0.1122   0.7558   0.0465
  -2.000   0.3810   0.00960   0.00310  -0.1120   0.7445   0.0486
  -1.750   0.4086   0.00942   0.00286  -0.1116   0.7317   0.0503
  -1.500   0.4358   0.00920   0.00259  -0.1113   0.7155   0.0547
  -1.250   0.4627   0.00906   0.00239  -0.1108   0.6951   0.0632
  -1.000   0.4890   0.00889   0.00237  -0.1104   0.6694   0.1284
  -0.750   0.5150   0.00898   0.00236  -0.1098   0.6395   0.1488
  -0.500   0.5406   0.00913   0.00235  -0.1092   0.6078   0.1601
  -0.250   0.5661   0.00928   0.00236  -0.1087   0.5799   0.1702
   0.500   0.6442   0.00963   0.00247  -0.1074   0.5208   0.2030
   0.750   0.6705   0.00969   0.00254  -0.1071   0.5035   0.2272
   1.000   0.6965   0.00969   0.00264  -0.1068   0.4843   0.2918
   1.250   0.7147   0.00858   0.00287  -0.1052   0.4640   0.8115
   1.500   0.7472   0.00854   0.00292  -0.1059   0.4330   1.0000
   1.750   0.7716   0.00887   0.00301  -0.1053   0.3947   1.0000
   2.000   0.7949   0.00930   0.00317  -0.1045   0.3555   1.0000
   2.250   0.8191   0.00969   0.00336  -0.1038   0.3288   1.0000
   2.500   0.8439   0.01002   0.00354  -0.1033   0.3112   1.0000
   2.750   0.8692   0.01030   0.00371  -0.1029   0.2987   1.0000
   3.000   0.8947   0.01057   0.00389  -0.1024   0.2892   1.0000
   3.250   0.9202   0.01082   0.00407  -0.1020   0.2812   1.0000
   3.500   0.9458   0.01107   0.00425  -0.1016   0.2750   1.0000
   3.750   0.9716   0.01129   0.00443  -0.1013   0.2694   1.0000
   4.000   0.9967   0.01157   0.00465  -0.1008   0.2639   1.0000
   4.250   1.0225   0.01178   0.00484  -0.1005   0.2594   1.0000
   4.500   1.0482   0.01200   0.00503  -0.1002   0.2555   1.0000
   4.750   1.0733   0.01225   0.00526  -0.0997   0.2516   1.0000
   5.000   1.0976   0.01257   0.00552  -0.0992   0.2475   1.0000
   5.250   1.1235   0.01275   0.00572  -0.0989   0.2444   1.0000
   5.500   1.1489   0.01296   0.00594  -0.0985   0.2410   1.0000
   5.750   1.1736   0.01322   0.00618  -0.0981   0.2374   1.0000
   6.000   1.1975   0.01353   0.00647  -0.0975   0.2339   1.0000
   6.250   1.2221   0.01378   0.00673  -0.0970   0.2304   1.0000
   6.500   1.2473   0.01396   0.00694  -0.0967   0.2256   1.0000
   6.750   1.2708   0.01426   0.00720  -0.0961   0.2197   1.0000
   7.000   1.2948   0.01452   0.00747  -0.0955   0.2148   1.0000
   7.250   1.3192   0.01474   0.00772  -0.0951   0.2095   1.0000
   7.500   1.3416   0.01508   0.00802  -0.0943   0.2038   1.0000
   7.750   1.3656   0.01530   0.00828  -0.0938   0.1974   1.0000
   8.000   1.3874   0.01566   0.00859  -0.0930   0.1878   1.0000
   8.250   1.4102   0.01594   0.00887  -0.0924   0.1774   1.0000
   8.500   1.4301   0.01639   0.00923  -0.0913   0.1616   1.0000
   8.750   1.4455   0.01705   0.00974  -0.0895   0.1404   1.0000
   9.000   1.4593   0.01782   0.01041  -0.0876   0.1274   1.0000
   9.250   1.4743   0.01851   0.01106  -0.0859   0.1188   1.0000
   9.500   1.4876   0.01932   0.01182  -0.0839   0.1099   1.0000
   9.750   1.5017   0.02009   0.01255  -0.0822   0.1006   1.0000
  10.000   1.5148   0.02093   0.01331  -0.0804   0.0858   1.0000
  10.750   1.5196   0.02609   0.01824  -0.0716   0.0171   1.0000
  11.000   1.5297   0.02727   0.01953  -0.0700   0.0163   1.0000
  11.250   1.5379   0.02864   0.02101  -0.0682   0.0155   1.0000
  11.500   1.5436   0.03025   0.02275  -0.0664   0.0148   1.0000
  11.750   1.5473   0.03209   0.02473  -0.0646   0.0143   1.0000
  12.000   1.5533   0.03377   0.02652  -0.0632   0.0140   1.0000
  12.250   1.5570   0.03571   0.02857  -0.0618   0.0135   1.0000
  12.500   1.5588   0.03790   0.03088  -0.0604   0.0132   1.0000
  12.750   1.5581   0.04039   0.03349  -0.0592   0.0128   1.0000
  13.000   1.5552   0.04322   0.03645  -0.0581   0.0126   1.0000
  13.250   1.5502   0.04641   0.03977  -0.0573   0.0124   1.0000
  13.500   1.5428   0.05005   0.04354  -0.0568   0.0122   1.0000
  13.750   1.5329   0.05426   0.04790  -0.0567   0.0120   1.0000
  14.000   1.5208   0.05904   0.05282  -0.0571   0.0119   1.0000
  14.250   1.5066   0.06440   0.05833  -0.0580   0.0118   1.0000
  14.500   1.4903   0.07033   0.06442  -0.0594   0.0117   1.0000
  14.750   1.4733   0.07653   0.07077  -0.0609   0.0117   1.0000
  15.000   1.4543   0.08315   0.07754  -0.0627   0.0116   1.0000
  15.250   1.4352   0.08995   0.08449  -0.0648   0.0116   1.0000
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