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GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il)
Reynolds number: 50,000
Max Cl/Cd: 15.26 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe190-il-50000.txt
Download as CSV file: xf-goe190-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 190 (MVA MK.18) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2630   0.11483   0.10795  -0.0235   1.0000   0.2518
  -8.250  -0.2776   0.11501   0.10825  -0.0228   1.0000   0.2574
  -8.000  -0.2793   0.11245   0.10578  -0.0219   1.0000   0.2598
  -7.750  -0.2634   0.10836   0.10169  -0.0205   1.0000   0.2663
  -7.500  -0.2767   0.10812   0.10158  -0.0190   1.0000   0.2725
  -7.250  -0.3102   0.11018   0.10386  -0.0164   1.0000   0.2741
  -7.000  -0.2747   0.10289   0.09650  -0.0160   1.0000   0.2793
  -6.750  -0.2781   0.10115   0.09486  -0.0141   1.0000   0.2839
  -6.500  -0.2993   0.10134   0.09521  -0.0111   1.0000   0.2882
  -6.250  -0.3373   0.10329   0.09738  -0.0074   1.0000   0.2900
  -6.000  -0.3371   0.10009   0.09427  -0.0054   1.0000   0.2914
  -5.750  -0.3340   0.09714   0.09137  -0.0032   1.0000   0.2936
  -5.500  -0.3381   0.09530   0.08960  -0.0009   1.0000   0.2966
  -5.250  -0.3478   0.09410   0.08849   0.0011   1.0000   0.3006
  -5.000  -0.3642   0.09359   0.08810   0.0014   1.0000   0.3047
  -4.750  -0.3780   0.09300   0.08759  -0.0014   1.0000   0.3065
  -4.250  -0.3009   0.05234   0.04598  -0.0626   1.0000   0.1668
  -4.000  -0.2334   0.03920   0.03148  -0.0835   1.0000   0.1679
  -3.750  -0.2220   0.03955   0.03208  -0.0812   1.0000   0.1723
  -3.500  -0.1951   0.03715   0.02930  -0.0841   1.0000   0.1780
  -3.250  -0.1695   0.03524   0.02698  -0.0863   1.0000   0.1849
  -3.000  -0.1190   0.03566   0.02745  -0.0910   0.9864   0.2022
  -2.750  -0.0693   0.03591   0.02765  -0.0955   0.9725   0.2257
  -2.500  -0.0282   0.03779   0.02977  -0.0973   0.9573   0.2607
  -2.250   0.0041   0.04068   0.03295  -0.0960   0.9418   0.3119
  -2.000   0.0299   0.04320   0.03551  -0.0934   0.9270   0.3752
  -1.750   0.0506   0.04443   0.03677  -0.0907   0.9136   0.4126
  -1.500   0.0734   0.04498   0.03727  -0.0891   0.9009   0.4486
  -1.250   0.0970   0.04525   0.03749  -0.0878   0.8892   0.4900
  -1.000   0.1259   0.04508   0.03726  -0.0871   0.8790   0.5350
  -0.750   0.1434   0.04456   0.03672  -0.0854   0.8670   0.5597
  -0.500   0.1753   0.04420   0.03618  -0.0876   0.8553   0.5708
  -0.250   0.2153   0.04387   0.03562  -0.0911   0.8444   0.5780
   0.000   0.2622   0.04342   0.03495  -0.0955   0.8342   0.5846
   0.250   0.2869   0.04346   0.03487  -0.0964   0.8221   0.5897
   0.500   0.3217   0.04352   0.03476  -0.0989   0.8113   0.5949
   0.750   0.3689   0.04309   0.03417  -0.1026   0.8018   0.6014
   1.000   0.3887   0.04358   0.03458  -0.1027   0.7896   0.6052
   1.250   0.4228   0.04382   0.03469  -0.1048   0.7792   0.6104
   1.500   0.4656   0.04372   0.03446  -0.1077   0.7694   0.6165
   1.750   0.4846   0.04457   0.03524  -0.1078   0.7575   0.6206
   2.000   0.5351   0.04429   0.03482  -0.1114   0.7491   0.6273
   2.250   0.5547   0.04529   0.03575  -0.1116   0.7370   0.6324
   2.500   0.5755   0.04629   0.03671  -0.1118   0.7259   0.6379
   2.750   0.6274   0.04594   0.03626  -0.1152   0.7175   0.6456
   3.000   0.6339   0.04783   0.03814  -0.1142   0.7049   0.6497
   3.250   0.6722   0.04814   0.03841  -0.1160   0.6961   0.6589
   3.500   0.6935   0.04937   0.03963  -0.1163   0.6851   0.6663
   3.750   0.7023   0.05140   0.04168  -0.1157   0.6740   0.6723
   4.000   0.7510   0.05114   0.04144  -0.1181   0.6662   0.6836
   4.250   0.7423   0.05434   0.04467  -0.1163   0.6543   0.6887
   4.500   0.8075   0.05291   0.04335  -0.1195   0.6479   0.7089
   4.750   0.7800   0.05757   0.04804  -0.1169   0.6359   0.7123
   5.000   0.7985   0.05925   0.04987  -0.1171   0.6270   0.7271
   5.250   0.8171   0.06084   0.05166  -0.1173   0.6179   0.7460
   5.500   0.8185   0.06367   0.05471  -0.1167   0.6091   0.7702
   5.750   0.8432   0.06429   0.05550  -0.1163   0.6002   1.0000
   6.000   0.8306   0.06845   0.05964  -0.1154   0.5908   1.0000
   6.250   0.8796   0.06845   0.05961  -0.1168   0.5808   1.0000
   6.500   0.8619   0.07294   0.06410  -0.1157   0.5708   1.0000
   6.750   0.8769   0.07522   0.06636  -0.1156   0.5607   1.0000
   7.000   0.9201   0.07535   0.06647  -0.1161   0.5499   1.0000
   7.250   0.8910   0.08096   0.07209  -0.1151   0.5405   1.0000
   7.500   0.9250   0.08185   0.07299  -0.1151   0.5299   1.0000
   7.750   0.9132   0.08623   0.07740  -0.1147   0.5202   1.0000
   8.000   0.9227   0.08910   0.08029  -0.1144   0.5104   1.0000
   8.250   0.9455   0.09085   0.08206  -0.1141   0.4999   1.0000
   8.500   0.9268   0.09619   0.08742  -0.1140   0.4916   1.0000
   8.750   0.9644   0.09666   0.08794  -0.1133   0.4794   1.0000
   9.000   0.9321   0.10357   0.09487  -0.1141   0.4749   1.0000
   9.250   0.9674   0.10435   0.09570  -0.1132   0.4626   1.0000
   9.500   0.9391   0.11103   0.10242  -0.1144   0.4592   1.0000
   9.750   0.9291   0.11653   0.10797  -0.1156   0.4586   1.0000
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