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GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 518 AIRFOIL (goe518-il)
Reynolds number: 500,000
Max Cl/Cd: 64.47 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe518-il-500000.txt
Download as CSV file: xf-goe518-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 518 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750   0.1280   0.10125   0.09865  -0.1268   0.9561   0.0314
 -11.500   0.1077   0.09548   0.09289  -0.1319   0.9488   0.0336
 -11.250   0.1218   0.09183   0.08923  -0.1339   0.9465   0.0338
 -11.000   0.1438   0.08945   0.08686  -0.1354   0.9448   0.0340
 -10.750   0.1628   0.08651   0.08391  -0.1383   0.9432   0.0343
 -10.500   0.1837   0.08367   0.08107  -0.1415   0.9417   0.0349
 -10.250   0.1935   0.08096   0.07835  -0.1432   0.9367   0.0354
 -10.000   0.2038   0.07791   0.07531  -0.1456   0.9312   0.0363
  -9.750   0.2020   0.06897   0.06633  -0.1581   0.9268   0.0384
  -9.500   0.2266   0.06682   0.06416  -0.1607   0.9233   0.0387
  -9.250   0.2330   0.06502   0.06237  -0.1603   0.9144   0.0390
  -9.000   0.2554   0.06211   0.05943  -0.1647   0.9097   0.0397
  -8.750   0.2570   0.05957   0.05689  -0.1656   0.8994   0.0405
  -8.500   0.2594   0.05494   0.05221  -0.1719   0.8897   0.0414
  -8.250   0.1635   0.04500   0.04186  -0.1694   0.8683   0.0433
  -8.000   0.1784   0.04348   0.04032  -0.1690   0.8607   0.0436
  -7.750   0.1829   0.04230   0.03911  -0.1664   0.8512   0.0438
  -7.500   0.1937   0.04073   0.03745  -0.1654   0.8425   0.0441
  -7.250   0.1957   0.03953   0.03619  -0.1621   0.8315   0.0445
  -7.000   0.1655   0.03607   0.03208  -0.1544   0.8202   0.0485
  -6.750   0.1699   0.03328   0.02922  -0.1518   0.8100   0.0490
  -6.500   0.1822   0.03216   0.02809  -0.1496   0.7993   0.0494
  -6.250   0.1973   0.03119   0.02705  -0.1479   0.7882   0.0498
  -6.000   0.2061   0.03038   0.02619  -0.1448   0.7752   0.0504
  -5.750   0.1928   0.02842   0.02362  -0.1371   0.7622   0.0551
  -5.500   0.2062   0.02702   0.02222  -0.1349   0.7477   0.0555
  -5.250   0.2176   0.02615   0.02130  -0.1320   0.7312   0.0560
  -5.000   0.2272   0.02546   0.02050  -0.1286   0.7125   0.0566
  -4.750   0.2342   0.02478   0.01968  -0.1245   0.6920   0.0576
  -4.500   0.2289   0.02368   0.01811  -0.1176   0.6743   0.0624
  -4.250   0.2354   0.02292   0.01726  -0.1135   0.6566   0.0629
  -4.000   0.2440   0.02237   0.01662  -0.1097   0.6406   0.0637
  -3.750   0.2383   0.01691   0.00984  -0.1007   0.6304   0.0434
  -3.500   0.2523   0.01676   0.00954  -0.0975   0.6166   0.0432
  -3.250   0.2683   0.01609   0.00875  -0.0950   0.6041   0.0429
  -3.000   0.2835   0.01563   0.00814  -0.0923   0.5915   0.0429
  -2.750   0.2999   0.01526   0.00768  -0.0898   0.5792   0.0429
  -2.500   0.3161   0.01496   0.00727  -0.0873   0.5669   0.0430
  -2.250   0.3312   0.01476   0.00694  -0.0846   0.5540   0.0431
  -2.000   0.3480   0.01440   0.00652  -0.0822   0.5405   0.0433
  -1.750   0.3636   0.01413   0.00620  -0.0797   0.5270   0.0437
  -1.500   0.3779   0.01400   0.00601  -0.0769   0.5128   0.0440
  -1.250   0.3915   0.01395   0.00590  -0.0740   0.4983   0.0448
  -1.000   0.4058   0.01394   0.00583  -0.0713   0.4837   0.0456
  -0.750   0.4211   0.01393   0.00575  -0.0687   0.4706   0.0463
  -0.500   0.4356   0.01396   0.00569  -0.0660   0.4576   0.0470
  -0.250   0.4500   0.01400   0.00565  -0.0634   0.4463   0.0474
   0.000   0.4669   0.01402   0.00562  -0.0612   0.4361   0.0482
   0.250   0.4817   0.01414   0.00565  -0.0586   0.4267   0.0487
   0.500   0.4987   0.01404   0.00556  -0.0565   0.4185   0.0499
   0.750   0.5147   0.01413   0.00559  -0.0542   0.4110   0.0511
   1.000   0.5330   0.01419   0.00563  -0.0524   0.4043   0.0528
   1.250   0.5511   0.01430   0.00569  -0.0505   0.3980   0.0546
   1.500   0.5673   0.01441   0.00576  -0.0484   0.3921   0.0585
   1.750   0.5871   0.01448   0.00583  -0.0469   0.3873   0.0629
   2.000   0.6050   0.01446   0.00598  -0.0450   0.3822   0.1059
   2.250   0.6179   0.01421   0.00619  -0.0424   0.3777   0.2795
   2.500   0.8985   0.01406   0.00769  -0.0965   0.3641   1.0000
   2.750   0.9115   0.01428   0.00785  -0.0938   0.3609   1.0000
   3.000   0.9246   0.01455   0.00804  -0.0912   0.3575   1.0000
   3.250   0.9401   0.01477   0.00822  -0.0891   0.3548   1.0000
   3.500   0.9564   0.01494   0.00839  -0.0871   0.3524   1.0000
   3.750   0.9724   0.01514   0.00857  -0.0850   0.3500   1.0000
   4.000   0.9887   0.01536   0.00876  -0.0831   0.3476   1.0000
   4.250   1.0049   0.01561   0.00897  -0.0811   0.3452   1.0000
   4.500   1.0213   0.01588   0.00919  -0.0792   0.3428   1.0000
   4.750   1.0383   0.01619   0.00944  -0.0775   0.3402   1.0000
   5.000   1.0568   0.01648   0.00969  -0.0761   0.3379   1.0000
   5.250   1.0738   0.01671   0.00994  -0.0744   0.3361   1.0000
   5.500   1.0918   0.01696   0.01019  -0.0728   0.3343   1.0000
   5.750   1.1095   0.01722   0.01045  -0.0713   0.3322   1.0000
   6.000   1.1276   0.01749   0.01071  -0.0699   0.3304   1.0000
   6.250   1.1455   0.01779   0.01100  -0.0685   0.3287   1.0000
   6.500   1.1635   0.01811   0.01129  -0.0671   0.3268   1.0000
   6.750   1.1823   0.01844   0.01159  -0.0659   0.3250   1.0000
   7.000   1.2035   0.01878   0.01189  -0.0651   0.3228   1.0000
   7.250   1.2250   0.01910   0.01220  -0.0644   0.3211   1.0000
   7.500   1.2431   0.01940   0.01254  -0.0632   0.3200   1.0000
   7.750   1.2609   0.01973   0.01289  -0.0619   0.3187   1.0000
   8.000   1.2786   0.02007   0.01326  -0.0606   0.3172   1.0000
   8.250   1.2963   0.02042   0.01363  -0.0594   0.3156   1.0000
   8.500   1.3133   0.02079   0.01401  -0.0581   0.3136   1.0000
   8.750   1.3315   0.02115   0.01439  -0.0570   0.3121   1.0000
   9.000   1.3485   0.02156   0.01479  -0.0558   0.3102   1.0000
   9.250   1.3665   0.02197   0.01519  -0.0548   0.3082   1.0000
   9.500   1.3893   0.02234   0.01551  -0.0545   0.3060   1.0000
   9.750   1.4108   0.02272   0.01591  -0.0540   0.3045   1.0000
  10.000   1.4261   0.02317   0.01643  -0.0527   0.3035   1.0000
  10.250   1.4419   0.02363   0.01695  -0.0515   0.3023   1.0000
  10.500   1.4576   0.02412   0.01748  -0.0502   0.3009   1.0000
  10.750   1.4723   0.02463   0.01805  -0.0490   0.2991   1.0000
  11.000   1.4871   0.02515   0.01860  -0.0477   0.2972   1.0000
  11.250   1.5039   0.02564   0.01913  -0.0468   0.2958   1.0000
  11.500   1.5197   0.02617   0.01968  -0.0458   0.2942   1.0000
  11.750   1.5357   0.02671   0.02023  -0.0448   0.2925   1.0000
  12.000   1.5556   0.02717   0.02067  -0.0444   0.2905   1.0000
  12.250   1.5756   0.02765   0.02116  -0.0440   0.2884   1.0000
  12.500   1.5854   0.02843   0.02204  -0.0424   0.2872   1.0000
  12.750   1.5962   0.02921   0.02291  -0.0410   0.2856   1.0000
  13.000   1.6063   0.03004   0.02381  -0.0396   0.2837   1.0000
  13.250   1.6183   0.03082   0.02465  -0.0385   0.2817   1.0000
  13.500   1.6300   0.03163   0.02551  -0.0374   0.2798   1.0000
  13.750   1.6408   0.03251   0.02642  -0.0362   0.2777   1.0000
  14.000   1.6537   0.03330   0.02721  -0.0353   0.2750   1.0000
  14.250   1.6716   0.03388   0.02780  -0.0349   0.2729   1.0000
  14.500   1.6769   0.03516   0.02921  -0.0335   0.2714   1.0000
  14.750   1.6835   0.03643   0.03058  -0.0323   0.2694   1.0000
  15.000   1.6907   0.03770   0.03193  -0.0312   0.2671   1.0000
  15.250   1.6969   0.03909   0.03338  -0.0302   0.2643   1.0000
  15.500   1.7032   0.04050   0.03483  -0.0293   0.2614   1.0000
  15.750   1.7145   0.04154   0.03585  -0.0286   0.2587   1.0000
  16.000   1.7149   0.04358   0.03803  -0.0276   0.2557   1.0000
  16.250   1.7183   0.04543   0.03999  -0.0269   0.2527   1.0000
  16.500   1.7217   0.04734   0.04198  -0.0263   0.2493   1.0000
  16.750   1.7252   0.04923   0.04390  -0.0257   0.2461   1.0000
  17.000   1.7277   0.05126   0.04597  -0.0251   0.2428   1.0000
  17.250   1.7276   0.05369   0.04855  -0.0247   0.2389   1.0000
  17.500   1.7283   0.05604   0.05098  -0.0243   0.2349   1.0000
  17.750   1.7247   0.05881   0.05376  -0.0238   0.2306   1.0000
  18.000   1.7232   0.06147   0.05653  -0.0236   0.2264   1.0000
  18.250   1.7174   0.06464   0.05980  -0.0234   0.2209   1.0000
  18.500   1.7064   0.06839   0.06357  -0.0232   0.2154   1.0000
  18.750   1.6941   0.07242   0.06770  -0.0231   0.2074   1.0000
  19.000   1.6773   0.07696   0.07228  -0.0231   0.2008   1.0000
  19.250   1.6525   0.08258   0.07794  -0.0233   0.1916   1.0000
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