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GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 195 AIRFOIL (goe195-il)
Reynolds number: 100,000
Max Cl/Cd: 63.31 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe195-il-100000.txt
Download as CSV file: xf-goe195-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 195 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3173   0.10061   0.09561  -0.0295   1.0000   0.0996
  -7.750  -0.3345   0.10049   0.09564  -0.0291   1.0000   0.1022
  -7.500  -0.3579   0.10106   0.09637  -0.0299   1.0000   0.1031
  -7.250  -0.3520   0.09646   0.09180  -0.0272   1.0000   0.1049
  -7.000  -0.3382   0.09309   0.08843  -0.0235   1.0000   0.1084
  -6.750  -0.3404   0.09123   0.08663  -0.0221   1.0000   0.1116
  -6.500  -0.3480   0.08982   0.08532  -0.0224   1.0000   0.1154
  -6.250  -0.3580   0.08861   0.08421  -0.0323   1.0000   0.1184
  -6.000  -0.3298   0.07875   0.07485  -0.0139   1.0000   0.1210
  -5.750  -0.3309   0.07675   0.07289  -0.0118   1.0000   0.1237
  -5.500  -0.3356   0.07493   0.07112  -0.0112   1.0000   0.1273
  -5.250  -0.3395   0.07765   0.07338  -0.0321   1.0000   0.1336
  -5.000  -0.3389   0.07532   0.07110  -0.0266   1.0000   0.1354
  -4.750  -0.3339   0.07342   0.06922  -0.0242   1.0000   0.1400
  -4.500  -0.3145   0.06987   0.06564  -0.0323   1.0000   0.1496
  -4.250  -0.3093   0.06796   0.06377  -0.0291   1.0000   0.1532
  -4.000  -0.2347   0.06322   0.05870  -0.0515   0.9943   0.1773
  -3.750  -0.2139   0.05928   0.05486  -0.0501   0.9885   0.1798
  -3.500  -0.1634   0.05542   0.05086  -0.0591   0.9827   0.1946
  -3.250  -0.0349   0.03365   0.02700  -0.0951   0.9851   0.1032
  -3.000   0.0145   0.02955   0.02257  -0.1008   0.9816   0.0965
  -2.750   0.0678   0.02633   0.01826  -0.1060   0.9768   0.0903
  -2.500   0.1169   0.02464   0.01625  -0.1104   0.9720   0.0914
  -2.250   0.1597   0.02352   0.01499  -0.1135   0.9640   0.0944
  -2.000   0.2086   0.02244   0.01374  -0.1174   0.9579   0.0960
  -1.750   0.2494   0.02165   0.01287  -0.1197   0.9482   0.0989
  -1.500   0.2990   0.02085   0.01203  -0.1236   0.9422   0.1043
  -1.250   0.3375   0.02023   0.01148  -0.1256   0.9309   0.1164
  -1.000   0.3819   0.01936   0.01099  -0.1286   0.9219   0.1648
  -0.750   0.4284   0.01918   0.01109  -0.1317   0.9133   0.3306
  -0.500   0.4649   0.01896   0.01102  -0.1331   0.9012   0.3858
  -0.250   0.5022   0.01863   0.01079  -0.1343   0.8898   0.4274
   0.000   0.5442   0.01810   0.01034  -0.1362   0.8817   0.4682
   0.250   0.5764   0.01774   0.01011  -0.1363   0.8681   0.5133
   0.500   0.6088   0.01730   0.00979  -0.1363   0.8547   0.5573
   0.750   0.6403   0.01669   0.00941  -0.1363   0.8414   0.6239
   1.000   0.6695   0.01561   0.00886  -0.1354   0.8282   1.0000
   1.250   0.7017   0.01555   0.00856  -0.1355   0.8148   1.0000
   1.500   0.7325   0.01552   0.00837  -0.1354   0.8017   1.0000
   1.750   0.7628   0.01551   0.00821  -0.1351   0.7890   1.0000
   2.000   0.7913   0.01559   0.00816  -0.1346   0.7752   1.0000
   2.250   0.8186   0.01573   0.00819  -0.1339   0.7605   1.0000
   2.500   0.8455   0.01589   0.00827  -0.1332   0.7458   1.0000
   2.750   0.8721   0.01612   0.00843  -0.1325   0.7316   1.0000
   3.000   0.8985   0.01640   0.00866  -0.1318   0.7183   1.0000
   3.250   0.9251   0.01669   0.00893  -0.1313   0.7059   1.0000
   3.500   0.9524   0.01695   0.00914  -0.1307   0.6946   1.0000
   3.750   0.9786   0.01725   0.00943  -0.1301   0.6823   1.0000
   4.000   1.0039   0.01758   0.00981  -0.1294   0.6693   1.0000
   4.250   1.0294   0.01783   0.01007  -0.1286   0.6556   1.0000
   4.500   1.0547   0.01801   0.01025  -0.1276   0.6405   1.0000
   4.750   1.0799   0.01813   0.01036  -0.1265   0.6242   1.0000
   5.000   1.1051   0.01822   0.01045  -0.1254   0.6070   1.0000
   5.250   1.1304   0.01837   0.01056  -0.1243   0.5901   1.0000
   5.500   1.1554   0.01861   0.01077  -0.1232   0.5730   1.0000
   5.750   1.1788   0.01893   0.01114  -0.1220   0.5535   1.0000
   6.000   1.2020   0.01923   0.01142  -0.1207   0.5319   1.0000
   6.250   1.2248   0.01956   0.01169  -0.1192   0.5088   1.0000
   6.500   1.2457   0.01987   0.01205  -0.1176   0.4840   1.0000
   6.750   1.2664   0.02014   0.01241  -0.1160   0.4595   1.0000
   7.000   1.2865   0.02038   0.01273  -0.1143   0.4338   1.0000
   7.250   1.3048   0.02061   0.01301  -0.1123   0.4016   1.0000
   7.500   1.3213   0.02098   0.01335  -0.1101   0.3617   1.0000
   7.750   1.3359   0.02170   0.01393  -0.1078   0.3197   1.0000
   8.000   1.3478   0.02277   0.01477  -0.1052   0.2738   1.0000
   8.250   1.3558   0.02421   0.01592  -0.1023   0.2236   1.0000
   8.500   1.3586   0.02616   0.01748  -0.0987   0.1623   1.0000
   8.750   1.3554   0.02870   0.01953  -0.0945   0.1216   1.0000
   9.000   1.3576   0.03081   0.02151  -0.0908   0.1024   1.0000
   9.250   1.3617   0.03271   0.02334  -0.0874   0.0926   1.0000
   9.500   1.3691   0.03447   0.02507  -0.0846   0.0852   1.0000
   9.750   1.3806   0.03623   0.02690  -0.0823   0.0788   1.0000
  10.000   1.3924   0.03790   0.02854  -0.0803   0.0736   1.0000
  10.250   1.4127   0.04007   0.03071  -0.0792   0.0696   1.0000
  10.500   1.4292   0.04188   0.03272  -0.0775   0.0658   1.0000
  10.750   1.4450   0.04372   0.03457  -0.0762   0.0623   1.0000
  11.000   1.4737   0.04677   0.03770  -0.0764   0.0595   1.0000
  11.250   1.4896   0.04948   0.04076  -0.0749   0.0579   1.0000
  11.500   1.4991   0.05218   0.04378  -0.0727   0.0564   1.0000
  11.750   1.5048   0.05475   0.04660  -0.0704   0.0547   1.0000
  12.000   1.5092   0.05729   0.04935  -0.0681   0.0532   1.0000
  12.250   1.5116   0.06030   0.05257  -0.0659   0.0523   1.0000
  12.500   1.5097   0.06381   0.05635  -0.0635   0.0519   1.0000
  12.750   1.5020   0.06753   0.06037  -0.0609   0.0517   1.0000
  13.000   1.4883   0.07146   0.06463  -0.0584   0.0517   1.0000
  13.250   1.4690   0.07576   0.06927  -0.0564   0.0520   1.0000
  13.500   1.4441   0.08072   0.07459  -0.0552   0.0524   1.0000
  13.750   1.4073   0.08704   0.08131  -0.0555   0.0530   1.0000
  14.000   1.3689   0.09464   0.08928  -0.0577   0.0538   1.0000
  14.250   1.3300   0.10345   0.09837  -0.0618   0.0547   1.0000
  14.500   1.2895   0.11380   0.10898  -0.0680   0.0558   1.0000
  14.750   1.2479   0.12613   0.12151  -0.0762   0.0571   1.0000
  15.000   1.2115   0.13945   0.13492  -0.0851   0.0586   1.0000
  15.250   1.1912   0.15019   0.14569  -0.0914   0.0598   1.0000
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