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GOE 592 AIRFOIL (goe592-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 592 AIRFOIL (goe592-il)
Reynolds number: 200,000
Max Cl/Cd: 76.48 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe592-il-200000.txt
Download as CSV file: xf-goe592-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 592 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.0728   0.10444   0.10046  -0.1209   0.9444   0.0612
 -10.500   0.0918   0.10083   0.09682  -0.1261   0.9426   0.0634
 -10.250   0.0743   0.09928   0.09528  -0.1341   0.9328   0.0647
 -10.000   0.1069   0.09453   0.09051  -0.1336   0.9314   0.0653
  -9.750   0.1337   0.09118   0.08714  -0.1352   0.9289   0.0665
  -9.500   0.1549   0.08807   0.08400  -0.1385   0.9262   0.0682
  -9.250   0.1602   0.08596   0.08190  -0.1390   0.9180   0.0699
  -9.000   0.1469   0.08374   0.07965  -0.1469   0.9085   0.0723
  -8.750   0.1427   0.08129   0.07723  -0.1456   0.8979   0.0727
  -8.500   0.1707   0.07797   0.07389  -0.1450   0.8953   0.0734
  -8.250   0.1931   0.07531   0.07119  -0.1457   0.8921   0.0745
  -8.000   0.1964   0.07381   0.06971  -0.1441   0.8829   0.0759
  -7.750   0.2040   0.07155   0.06742  -0.1451   0.8765   0.0782
  -7.500   0.1845   0.07020   0.06610  -0.1449   0.8640   0.0805
  -7.250   0.1579   0.06693   0.06277  -0.1514   0.8520   0.0816
  -7.000   0.1740   0.06475   0.06062  -0.1478   0.8469   0.0822
  -6.750   0.1920   0.06263   0.05848  -0.1466   0.8427   0.0831
  -6.500   0.2105   0.06034   0.05613  -0.1474   0.8391   0.0845
  -6.250   0.2107   0.05887   0.05469  -0.1461   0.8292   0.0861
  -6.000   0.2136   0.05330   0.04878  -0.1568   0.8223   0.0922
  -5.750   0.2217   0.05196   0.04752  -0.1537   0.8146   0.0928
  -5.500   0.2387   0.05042   0.04600  -0.1523   0.8095   0.0942
  -5.250   0.2606   0.04759   0.04252  -0.1591   0.8047   0.1033
  -5.000   0.2668   0.04459   0.03970  -0.1568   0.7970   0.1042
  -4.750   0.2857   0.04276   0.03792  -0.1560   0.7921   0.1053
  -4.500   0.3100   0.04108   0.03619  -0.1563   0.7886   0.1075
  -4.250   0.3271   0.03969   0.03471  -0.1559   0.7825   0.1124
  -4.000   0.3434   0.03722   0.03202  -0.1563   0.7761   0.1194
  -3.750   0.3687   0.03579   0.03054  -0.1565   0.7723   0.1228
  -3.500   0.3918   0.02656   0.01986  -0.1582   0.7689   0.0903
  -3.250   0.4046   0.02532   0.01837  -0.1557   0.7612   0.0908
  -3.000   0.4309   0.02394   0.01658  -0.1553   0.7567   0.0916
  -2.750   0.4610   0.02229   0.01483  -0.1561   0.7535   0.0941
  -2.500   0.4830   0.02197   0.01451  -0.1551   0.7479   0.0971
  -2.250   0.5056   0.02134   0.01370  -0.1540   0.7421   0.0999
  -2.000   0.5360   0.02067   0.01272  -0.1541   0.7380   0.1029
  -1.750   0.5689   0.01968   0.01164  -0.1551   0.7349   0.1069
  -1.500   0.5860   0.01956   0.01155  -0.1531   0.7282   0.1099
  -1.250   0.6121   0.01923   0.01111  -0.1526   0.7232   0.1138
  -1.000   0.6443   0.01867   0.01038  -0.1532   0.7194   0.1177
  -0.750   0.6724   0.01829   0.01002  -0.1532   0.7152   0.1220
  -0.500   0.6912   0.01826   0.01001  -0.1515   0.7088   0.1261
  -0.250   0.7198   0.01801   0.00968  -0.1514   0.7042   0.1302
   0.000   0.7529   0.01751   0.00916  -0.1523   0.7006   0.1358
   0.250   0.7727   0.01753   0.00924  -0.1508   0.6949   0.1409
   0.500   0.7958   0.01747   0.00917  -0.1497   0.6893   0.1462
   0.750   0.8259   0.01713   0.00887  -0.1501   0.6851   0.1545
   1.000   0.8579   0.01700   0.00867  -0.1507   0.6813   0.1647
   1.250   0.8721   0.01704   0.00889  -0.1482   0.6746   0.1763
   1.500   0.8981   0.01684   0.00879  -0.1478   0.6697   0.2041
   1.750   0.9612   0.01501   0.00871  -0.1550   0.6660   1.0000
   2.000   0.9808   0.01528   0.00891  -0.1534   0.6603   1.0000
   2.250   1.0015   0.01549   0.00906  -0.1520   0.6544   1.0000
   2.500   1.0317   0.01554   0.00898  -0.1524   0.6498   1.0000
   2.750   1.0592   0.01571   0.00905  -0.1522   0.6451   1.0000
   3.000   1.0746   0.01601   0.00936  -0.1499   0.6386   1.0000
   3.250   1.1026   0.01609   0.00936  -0.1499   0.6334   1.0000
   3.500   1.1369   0.01616   0.00930  -0.1510   0.6292   1.0000
   3.750   1.1472   0.01653   0.00973  -0.1478   0.6220   1.0000
   4.000   1.1735   0.01663   0.00978  -0.1475   0.6164   1.0000
   4.250   1.2088   0.01669   0.00970  -0.1488   0.6119   1.0000
   4.500   1.2174   0.01705   0.01015  -0.1453   0.6045   1.0000
   4.750   1.2437   0.01713   0.01018  -0.1450   0.5985   1.0000
   5.000   1.2733   0.01724   0.01021  -0.1453   0.5930   1.0000
   5.250   1.2844   0.01756   0.01059  -0.1423   0.5856   1.0000
   5.500   1.3124   0.01763   0.01061  -0.1423   0.5799   1.0000
   5.750   1.3337   0.01786   0.01083  -0.1411   0.5737   1.0000
   6.000   1.3484   0.01810   0.01110  -0.1387   0.5664   1.0000
   6.250   1.3801   0.01810   0.01100  -0.1394   0.5602   1.0000
   6.500   1.3864   0.01844   0.01142  -0.1355   0.5522   1.0000
   6.750   1.4093   0.01850   0.01143  -0.1346   0.5449   1.0000
   7.000   1.4228   0.01876   0.01171  -0.1321   0.5376   1.0000
   7.250   1.4352   0.01898   0.01195  -0.1293   0.5303   1.0000
   7.500   1.4623   0.01912   0.01203  -0.1292   0.5240   1.0000
   7.750   1.4610   0.01953   0.01253  -0.1241   0.5159   1.0000
   8.000   1.4861   0.01961   0.01252  -0.1236   0.5085   1.0000
   8.250   1.4853   0.02014   0.01314  -0.1189   0.5002   1.0000
   8.500   1.5043   0.02035   0.01332  -0.1175   0.4928   1.0000
   8.750   1.5099   0.02088   0.01391  -0.1140   0.4845   1.0000
   9.000   1.5245   0.02121   0.01421  -0.1120   0.4764   1.0000
   9.250   1.5311   0.02180   0.01485  -0.1089   0.4678   1.0000
   9.500   1.5443   0.02221   0.01524  -0.1068   0.4591   1.0000
   9.750   1.5475   0.02296   0.01605  -0.1034   0.4496   1.0000
  10.250   1.5613   0.02438   0.01749  -0.0979   0.4302   1.0000
  10.500   1.5726   0.02502   0.01811  -0.0958   0.4210   1.0000
  10.750   1.5763   0.02600   0.01915  -0.0930   0.4114   1.0000
  11.000   1.5840   0.02689   0.02005  -0.0907   0.4022   1.0000
  11.250   1.5897   0.02789   0.02105  -0.0883   0.3923   1.0000
  11.500   1.5926   0.02909   0.02233  -0.0857   0.3822   1.0000
  11.750   1.5982   0.03020   0.02339  -0.0834   0.3719   1.0000
  12.000   1.5991   0.03165   0.02491  -0.0809   0.3612   1.0000
  12.250   1.6011   0.03311   0.02640  -0.0786   0.3504   1.0000
  12.500   1.6041   0.03457   0.02782  -0.0765   0.3397   1.0000
  12.750   1.6029   0.03643   0.02976  -0.0743   0.3278   1.0000
  13.000   1.6024   0.03834   0.03169  -0.0722   0.3161   1.0000
  13.250   1.6009   0.04039   0.03373  -0.0702   0.3039   1.0000
  13.500   1.5973   0.04271   0.03603  -0.0683   0.2907   1.0000
  13.750   1.5921   0.04530   0.03861  -0.0665   0.2765   1.0000
  14.000   1.5847   0.04820   0.04151  -0.0647   0.2610   1.0000
  14.250   1.5749   0.05147   0.04472  -0.0630   0.2443   1.0000
  14.500   1.5631   0.05510   0.04832  -0.0616   0.2259   1.0000
  14.750   1.5498   0.05902   0.05219  -0.0602   0.2068   1.0000
  15.000   1.5359   0.06316   0.05625  -0.0591   0.1889   1.0000
  15.250   1.5237   0.06723   0.06024  -0.0582   0.1739   1.0000
  15.500   1.5152   0.07097   0.06392  -0.0575   0.1625   1.0000
  15.750   1.5083   0.07453   0.06740  -0.0570   0.1543   1.0000
  16.000   1.5072   0.07753   0.07042  -0.0566   0.1472   1.0000
  16.250   1.5051   0.08055   0.07334  -0.0561   0.1419   1.0000
  16.500   1.5087   0.08301   0.07589  -0.0559   0.1373   1.0000
  16.750   1.5118   0.08548   0.07838  -0.0556   0.1333   1.0000
  17.000   1.5176   0.08744   0.08026  -0.0552   0.1297   1.0000
  17.250   1.5256   0.08925   0.08212  -0.0549   0.1268   1.0000
  17.500   1.5324   0.09129   0.08424  -0.0547   0.1241   1.0000
  17.750   1.5394   0.09327   0.08628  -0.0546   0.1213   1.0000
  18.000   1.5489   0.09480   0.08779  -0.0543   0.1188   1.0000
  18.250   1.5677   0.09487   0.08777  -0.0535   0.1160   1.0000
  18.500   1.5714   0.09740   0.09047  -0.0537   0.1142   1.0000
  18.750   1.5776   0.09955   0.09274  -0.0538   0.1122   1.0000
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