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GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il)
Reynolds number: 200,000
Max Cl/Cd: 77.3 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe190-il-200000.txt
Download as CSV file: xf-goe190-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2566   0.09965   0.09657  -0.0284   1.0000   0.0750
  -8.750  -0.2634   0.09748   0.09444  -0.0275   1.0000   0.0778
  -8.500  -0.2909   0.08977   0.08678  -0.0400   0.9949   0.0817
  -8.250  -0.2515   0.08626   0.08323  -0.0373   0.9936   0.0842
  -8.000  -0.2277   0.08326   0.08022  -0.0392   0.9893   0.0873
  -7.750  -0.3844   0.08962   0.08655  -0.0321   0.9975   0.0828
  -7.500  -0.3470   0.08810   0.08498  -0.0313   0.9957   0.0850
  -7.250  -0.3484   0.03696   0.03207  -0.1094   0.9719   0.0592
  -7.000  -0.3119   0.03353   0.02857  -0.1138   0.9693   0.0611
  -6.750  -0.2803   0.03036   0.02498  -0.1170   0.9611   0.0615
  -6.500  -0.2408   0.02795   0.02223  -0.1208   0.9572   0.0625
  -6.250  -0.2039   0.02627   0.02032  -0.1233   0.9519   0.0647
  -6.000  -0.1693   0.02467   0.01841  -0.1252   0.9449   0.0662
  -5.750  -0.1286   0.02323   0.01669  -0.1278   0.9414   0.0676
  -5.500  -0.0960   0.02254   0.01575  -0.1287   0.9334   0.0693
  -5.250  -0.0614   0.02050   0.01365  -0.1303   0.9283   0.0715
  -5.000  -0.0212   0.01932   0.01248  -0.1326   0.9252   0.0737
  -4.750   0.0065   0.01850   0.01163  -0.1323   0.9148   0.0764
  -4.500   0.0465   0.01764   0.01072  -0.1344   0.9107   0.0799
  -4.250   0.0749   0.01691   0.00995  -0.1341   0.9003   0.0822
  -4.000   0.1127   0.01585   0.00897  -0.1358   0.8956   0.0870
  -3.750   0.1416   0.01521   0.00830  -0.1357   0.8847   0.0928
  -3.500   0.1813   0.01431   0.00741  -0.1376   0.8796   0.1024
  -3.000   0.2502   0.01292   0.00657  -0.1398   0.8567   0.2798
  -2.750   0.2959   0.01320   0.00676  -0.1424   0.8466   0.3094
  -2.500   0.3414   0.01344   0.00694  -0.1451   0.8335   0.3262
  -2.250   0.3848   0.01362   0.00700  -0.1474   0.8161   0.3384
  -2.000   0.4221   0.01395   0.00729  -0.1486   0.7952   0.3474
  -1.750   0.4556   0.01411   0.00718  -0.1493   0.7742   0.3565
  -1.500   0.4848   0.01444   0.00748  -0.1490   0.7546   0.3625
  -1.250   0.5126   0.01477   0.00766  -0.1485   0.7364   0.3710
  -1.000   0.5388   0.01500   0.00781  -0.1478   0.7192   0.3779
  -0.750   0.5644   0.01527   0.00802  -0.1469   0.7032   0.3839
  -0.500   0.5907   0.01525   0.00782  -0.1465   0.6882   0.3897
  -0.250   0.6165   0.01521   0.00767  -0.1459   0.6748   0.3930
   0.000   0.6426   0.01525   0.00764  -0.1453   0.6628   0.3961
   0.250   0.6681   0.01523   0.00756  -0.1447   0.6504   0.3993
   0.500   0.6939   0.01520   0.00744  -0.1441   0.6387   0.4031
   0.750   0.7208   0.01520   0.00727  -0.1438   0.6287   0.4078
   1.000   0.7462   0.01516   0.00722  -0.1431   0.6184   0.4105
   1.250   0.7721   0.01518   0.00721  -0.1426   0.6088   0.4136
   1.500   0.7985   0.01523   0.00717  -0.1421   0.5997   0.4171
   1.750   0.8244   0.01527   0.00716  -0.1416   0.5901   0.4212
   2.000   0.8517   0.01536   0.00711  -0.1413   0.5821   0.4255
   2.250   0.8768   0.01542   0.00723  -0.1407   0.5732   0.4289
   2.500   0.9043   0.01559   0.00729  -0.1405   0.5655   0.4330
   2.750   0.9294   0.01568   0.00740  -0.1398   0.5563   0.4374
   3.000   0.9572   0.01587   0.00747  -0.1397   0.5485   0.4418
   3.250   0.9818   0.01598   0.00765  -0.1389   0.5398   0.4454
   3.500   1.0096   0.01623   0.00782  -0.1388   0.5324   0.4505
   3.750   1.0338   0.01640   0.00802  -0.1380   0.5234   0.4563
   4.250   1.0836   0.01673   0.00839  -0.1367   0.5050   0.4660
   4.500   1.1098   0.01699   0.00855  -0.1362   0.4963   0.4721
   4.750   1.1324   0.01706   0.00874  -0.1351   0.4866   0.4768
   5.000   1.1580   0.01729   0.00895  -0.1346   0.4787   0.4831
   5.250   1.1811   0.01742   0.00916  -0.1336   0.4700   0.4897
   5.500   1.2067   0.01762   0.00936  -0.1331   0.4626   0.4966
   5.750   1.2288   0.01775   0.00959  -0.1319   0.4537   0.5042
   6.000   1.2548   0.01794   0.00977  -0.1315   0.4469   0.5113
   6.250   1.2763   0.01808   0.01006  -0.1302   0.4383   0.5193
   6.500   1.3006   0.01822   0.01023  -0.1294   0.4312   0.5273
   6.750   1.3216   0.01837   0.01052  -0.1281   0.4226   0.5367
   7.000   1.3456   0.01852   0.01068  -0.1273   0.4148   0.5473
   7.250   1.3670   0.01865   0.01098  -0.1261   0.4052   0.5580
   7.500   1.3902   0.01880   0.01116  -0.1252   0.3963   0.5705
   7.750   1.4104   0.01891   0.01139  -0.1237   0.3857   0.5848
   8.000   1.4307   0.01907   0.01169  -0.1223   0.3751   0.6053
   8.250   1.4609   0.01890   0.01202  -0.1232   0.3640   1.0000
   8.500   1.4793   0.01924   0.01239  -0.1214   0.3537   1.0000
   8.750   1.4971   0.01964   0.01281  -0.1196   0.3434   1.0000
   9.000   1.5145   0.02010   0.01321  -0.1177   0.3332   1.0000
   9.250   1.5292   0.02051   0.01368  -0.1154   0.3221   1.0000
   9.500   1.5422   0.02097   0.01418  -0.1127   0.3109   1.0000
   9.750   1.5542   0.02151   0.01469  -0.1100   0.3001   1.0000
  10.000   1.5640   0.02205   0.01525  -0.1069   0.2881   1.0000
  10.250   1.5729   0.02261   0.01587  -0.1038   0.2748   1.0000
  10.500   1.5806   0.02325   0.01654  -0.1006   0.2608   1.0000
  10.750   1.5871   0.02400   0.01729  -0.0974   0.2460   1.0000
  11.000   1.5929   0.02486   0.01815  -0.0943   0.2313   1.0000
  11.250   1.5980   0.02585   0.01915  -0.0913   0.2168   1.0000
  11.500   1.6023   0.02699   0.02028  -0.0883   0.2036   1.0000
  11.750   1.6048   0.02830   0.02158  -0.0854   0.1911   1.0000
  12.000   1.6052   0.02985   0.02310  -0.0825   0.1794   1.0000
  12.250   1.6048   0.03157   0.02482  -0.0797   0.1680   1.0000
  12.500   1.6053   0.03336   0.02665  -0.0774   0.1567   1.0000
  12.750   1.6040   0.03541   0.02874  -0.0752   0.1463   1.0000
  13.000   1.6000   0.03782   0.03117  -0.0732   0.1366   1.0000
  13.250   1.5973   0.04031   0.03370  -0.0716   0.1260   1.0000
  13.500   1.5948   0.04293   0.03638  -0.0703   0.1160   1.0000
  13.750   1.5893   0.04598   0.03947  -0.0693   0.1073   1.0000
  14.000   1.5807   0.04952   0.04300  -0.0685   0.0995   1.0000
  14.250   1.5743   0.05297   0.04652  -0.0679   0.0915   1.0000
  14.500   1.5627   0.05717   0.05074  -0.0676   0.0852   1.0000
  14.750   1.5532   0.06131   0.05494  -0.0676   0.0787   1.0000
  15.000   1.5406   0.06599   0.05966  -0.0678   0.0734   1.0000
  15.250   1.5299   0.07060   0.06435  -0.0683   0.0678   1.0000
  15.500   1.5162   0.07570   0.06948  -0.0690   0.0631   1.0000
  15.750   1.5064   0.08043   0.07430  -0.0698   0.0583   1.0000
  16.000   1.4931   0.08564   0.07948  -0.0707   0.0550   1.0000
  16.250   1.4866   0.09010   0.08409  -0.0716   0.0511   1.0000
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