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GOE 490 AIRFOIL (goe490-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 490 AIRFOIL (goe490-il)
Reynolds number: 200,000
Max Cl/Cd: 70.1 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe490-il-200000-n5.txt
Download as CSV file: xf-goe490-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 490 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3910   0.08749   0.08405  -0.0320   1.0000   0.0180
  -8.500  -0.4003   0.08367   0.08030  -0.0323   1.0000   0.0182
  -8.250  -0.4123   0.08043   0.07714  -0.0319   1.0000   0.0182
  -8.000  -0.4307   0.07743   0.07423  -0.0306   1.0000   0.0184
  -7.750  -0.4461   0.07312   0.07001  -0.0312   1.0000   0.0187
  -7.500  -0.4561   0.06538   0.06229  -0.0367   0.9979   0.0192
  -7.250  -0.4382   0.05588   0.05266  -0.0480   0.9906   0.0203
  -6.750  -0.4071   0.03141   0.02697  -0.0650   0.9753   0.0230
  -6.500  -0.3872   0.02697   0.02183  -0.0660   0.9683   0.0253
  -6.250  -0.3570   0.02474   0.01898  -0.0674   0.9647   0.0276
  -6.000  -0.3359   0.02237   0.01627  -0.0671   0.9577   0.0295
  -5.750  -0.3045   0.02167   0.01547  -0.0683   0.9538   0.0320
  -5.500  -0.2759   0.02057   0.01410  -0.0687   0.9488   0.0344
  -5.250  -0.2472   0.01950   0.01272  -0.0689   0.9429   0.0365
  -5.000  -0.2133   0.01851   0.01144  -0.0702   0.9390   0.0383
  -4.750  -0.1858   0.01716   0.00991  -0.0702   0.9319   0.0402
  -4.500  -0.1525   0.01637   0.00903  -0.0713   0.9262   0.0424
  -4.250  -0.1179   0.01568   0.00822  -0.0727   0.9206   0.0447
  -4.000  -0.0861   0.01498   0.00740  -0.0733   0.9127   0.0462
  -3.750  -0.0503   0.01433   0.00660  -0.0747   0.9064   0.0478
  -3.500  -0.0181   0.01381   0.00598  -0.0754   0.8969   0.0492
  -3.250   0.0144   0.01328   0.00538  -0.0763   0.8882   0.0512
  -3.000   0.0479   0.01283   0.00488  -0.0773   0.8801   0.0547
  -2.750   0.0781   0.01250   0.00451  -0.0776   0.8702   0.0601
  -2.500   0.1097   0.01213   0.00416  -0.0783   0.8606   0.0693
  -2.250   0.1408   0.01183   0.00388  -0.0788   0.8501   0.0899
  -2.000   0.1696   0.01164   0.00373  -0.0788   0.8381   0.1145
  -1.750   0.1985   0.01152   0.00356  -0.0788   0.8260   0.1300
  -1.500   0.2270   0.01139   0.00339  -0.0788   0.8131   0.1430
  -1.250   0.2550   0.01127   0.00325  -0.0787   0.7998   0.1578
  -1.000   0.2823   0.01114   0.00312  -0.0784   0.7861   0.1742
  -0.750   0.3090   0.01102   0.00304  -0.0780   0.7719   0.1957
  -0.500   0.3354   0.01093   0.00302  -0.0776   0.7572   0.2286
  -0.250   0.3616   0.01088   0.00298  -0.0770   0.7418   0.2597
   0.000   0.3874   0.01085   0.00291  -0.0764   0.7262   0.2827
   0.250   0.4127   0.01081   0.00284  -0.0757   0.7100   0.3054
   0.500   0.4372   0.01074   0.00278  -0.0749   0.6925   0.3313
   0.750   0.4600   0.01059   0.00272  -0.0738   0.6715   0.3828
   1.250   0.5895   0.00966   0.00288  -0.0893   0.6133   1.0000
   1.500   0.6118   0.00982   0.00291  -0.0881   0.5925   1.0000
   1.750   0.6339   0.00999   0.00296  -0.0867   0.5712   1.0000
   2.000   0.6556   0.01018   0.00303  -0.0854   0.5489   1.0000
   2.250   0.6769   0.01040   0.00310  -0.0839   0.5256   1.0000
   2.500   0.6978   0.01064   0.00320  -0.0824   0.5010   1.0000
   2.750   0.7185   0.01090   0.00332  -0.0809   0.4785   1.0000
   3.000   0.7393   0.01117   0.00345  -0.0794   0.4570   1.0000
   3.250   0.7605   0.01143   0.00362  -0.0780   0.4391   1.0000
   3.500   0.7823   0.01168   0.00380  -0.0768   0.4250   1.0000
   3.750   0.8045   0.01191   0.00399  -0.0756   0.4132   1.0000
   4.000   0.8266   0.01214   0.00420  -0.0744   0.4018   1.0000
   4.250   0.8485   0.01239   0.00441  -0.0732   0.3900   1.0000
   4.500   0.8707   0.01262   0.00464  -0.0721   0.3775   1.0000
   4.750   0.8928   0.01285   0.00487  -0.0709   0.3648   1.0000
   5.000   0.9146   0.01310   0.00513  -0.0697   0.3513   1.0000
   5.250   0.9361   0.01336   0.00539  -0.0684   0.3372   1.0000
   5.500   0.9569   0.01365   0.00565  -0.0671   0.3198   1.0000
   5.750   0.9748   0.01407   0.00592  -0.0653   0.2881   1.0000
   6.000   0.9919   0.01458   0.00627  -0.0634   0.2547   1.0000
   6.250   1.0100   0.01507   0.00666  -0.0617   0.2312   1.0000
   6.500   1.0277   0.01560   0.00707  -0.0599   0.2066   1.0000
   6.750   1.0459   0.01611   0.00750  -0.0583   0.1865   1.0000
   7.000   1.0637   0.01665   0.00795  -0.0566   0.1630   1.0000
   7.250   1.0800   0.01731   0.00848  -0.0548   0.1363   1.0000
   7.500   1.0947   0.01808   0.00908  -0.0527   0.1079   1.0000
   7.750   1.1029   0.01936   0.00999  -0.0497   0.0513   1.0000
   8.000   1.1102   0.02070   0.01113  -0.0465   0.0205   1.0000
   8.250   1.1254   0.02140   0.01192  -0.0444   0.0181   1.0000
   8.500   1.1390   0.02217   0.01281  -0.0421   0.0164   1.0000
   8.750   1.1509   0.02296   0.01373  -0.0395   0.0155   1.0000
   9.000   1.1608   0.02387   0.01482  -0.0366   0.0145   1.0000
   9.250   1.1677   0.02496   0.01609  -0.0335   0.0137   1.0000
   9.500   1.1760   0.02594   0.01721  -0.0307   0.0131   1.0000
   9.750   1.1844   0.02693   0.01833  -0.0281   0.0124   1.0000
  10.000   1.1898   0.02813   0.01967  -0.0253   0.0118   1.0000
  10.250   1.1938   0.02945   0.02113  -0.0225   0.0116   1.0000
  10.500   1.1960   0.03095   0.02276  -0.0199   0.0113   1.0000
  10.750   1.1971   0.03262   0.02455  -0.0175   0.0111   1.0000
  11.000   1.1968   0.03450   0.02655  -0.0153   0.0109   1.0000
  11.250   1.1958   0.03658   0.02874  -0.0134   0.0106   1.0000
  11.500   1.1953   0.03877   0.03104  -0.0118   0.0105   1.0000
  11.750   1.1935   0.04123   0.03364  -0.0105   0.0103   1.0000
  12.000   1.1923   0.04378   0.03629  -0.0095   0.0101   1.0000
  12.250   1.1909   0.04646   0.03906  -0.0087   0.0099   1.0000
  12.500   1.1891   0.04931   0.04199  -0.0080   0.0097   1.0000
  12.750   1.1880   0.05216   0.04490  -0.0074   0.0095   1.0000
  13.000   1.1881   0.05500   0.04779  -0.0067   0.0093   1.0000
  13.250   1.1896   0.05781   0.05066  -0.0059   0.0090   1.0000
  13.500   1.1885   0.06086   0.05392  -0.0065   0.0087   1.0000
  13.750   1.1885   0.06394   0.05716  -0.0066   0.0085   1.0000
  14.000   1.1886   0.06710   0.06045  -0.0068   0.0085   1.0000
  14.250   1.1870   0.07054   0.06405  -0.0073   0.0083   1.0000
  14.500   1.1848   0.07419   0.06786  -0.0079   0.0082   1.0000
  14.750   1.1816   0.07810   0.07194  -0.0088   0.0081   1.0000
  15.000   1.1773   0.08226   0.07626  -0.0100   0.0081   1.0000
  15.250   1.1712   0.08685   0.08102  -0.0115   0.0080   1.0000
  15.500   1.1648   0.09161   0.08596  -0.0133   0.0080   1.0000
  15.750   1.1570   0.09677   0.09129  -0.0154   0.0079   1.0000
  16.000   1.1485   0.10217   0.09686  -0.0179   0.0079   1.0000
  16.250   1.1390   0.10795   0.10281  -0.0207   0.0079   1.0000
  16.500   1.1277   0.11428   0.10932  -0.0240   0.0079   1.0000
  16.750   1.1166   0.12079   0.11600  -0.0276   0.0079   1.0000
  17.000   1.1055   0.12749   0.12286  -0.0314   0.0079   1.0000
  17.250   1.0952   0.13417   0.12969  -0.0353   0.0080   1.0000
  17.500   1.0829   0.14168   0.13735  -0.0398   0.0080   1.0000
  17.750   1.0709   0.14942   0.14524  -0.0445   0.0080   1.0000
  18.000   1.0585   0.15757   0.15352  -0.0495   0.0081   1.0000
  18.250   1.0456   0.16624   0.16232  -0.0549   0.0082   1.0000
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