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GOE 497 AIRFOIL (goe497-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 497 AIRFOIL (goe497-il)
Reynolds number: 500,000
Max Cl/Cd: 117.99 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe497-il-500000.txt
Download as CSV file: xf-goe497-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 497 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.3154   0.13510   0.13263  -0.0437   1.0000   0.0353
 -12.750  -0.5210   0.08473   0.08222  -0.0644   1.0000   0.0320
 -12.500  -0.7223   0.04694   0.04386  -0.0967   0.9929   0.0304
 -12.250  -0.7175   0.03702   0.03361  -0.1156   0.9834   0.0309
 -12.000  -0.6936   0.03141   0.02760  -0.1284   0.9758   0.0316
 -11.750  -0.6677   0.02801   0.02391  -0.1345   0.9721   0.0325
 -11.500  -0.6356   0.02648   0.02234  -0.1379   0.9704   0.0334
 -11.250  -0.6064   0.02536   0.02115  -0.1401   0.9670   0.0342
 -11.000  -0.5778   0.02433   0.02001  -0.1420   0.9627   0.0353
 -10.750  -0.5457   0.02317   0.01866  -0.1446   0.9601   0.0365
 -10.500  -0.5122   0.02224   0.01752  -0.1470   0.9578   0.0373
 -10.250  -0.4822   0.02033   0.01552  -0.1494   0.9556   0.0386
 -10.000  -0.4581   0.01970   0.01487  -0.1493   0.9494   0.0396
  -9.750  -0.4285   0.01901   0.01410  -0.1503   0.9451   0.0408
  -9.500  -0.3976   0.01829   0.01325  -0.1515   0.9417   0.0421
  -9.250  -0.3701   0.01768   0.01250  -0.1519   0.9369   0.0430
  -9.000  -0.3462   0.01665   0.01136  -0.1518   0.9307   0.0442
  -8.750  -0.3184   0.01592   0.01061  -0.1523   0.9263   0.0456
  -8.500  -0.2910   0.01543   0.01006  -0.1525   0.9214   0.0469
  -8.250  -0.2656   0.01494   0.00950  -0.1522   0.9151   0.0482
  -8.000  -0.2376   0.01452   0.00896  -0.1523   0.9101   0.0496
  -7.750  -0.2111   0.01390   0.00825  -0.1522   0.9049   0.0511
  -7.500  -0.1860   0.01328   0.00762  -0.1519   0.8985   0.0529
  -7.250  -0.1582   0.01288   0.00715  -0.1520   0.8931   0.0548
  -7.000  -0.1315   0.01254   0.00675  -0.1517   0.8868   0.0568
  -6.750  -0.1046   0.01221   0.00633  -0.1515   0.8803   0.0587
  -6.500  -0.0769   0.01168   0.00576  -0.1516   0.8750   0.0620
  -6.250  -0.0506   0.01139   0.00545  -0.1512   0.8680   0.0650
  -6.000  -0.0231   0.01110   0.00507  -0.1510   0.8616   0.0682
  -5.750   0.0047   0.01076   0.00474  -0.1510   0.8558   0.0734
  -5.500   0.0319   0.01056   0.00449  -0.1508   0.8494   0.0785
  -5.250   0.0600   0.01030   0.00423  -0.1508   0.8438   0.0861
  -5.000   0.0876   0.01007   0.00399  -0.1506   0.8375   0.0944
  -4.750   0.1151   0.00990   0.00379  -0.1504   0.8305   0.1034
  -4.250   0.1706   0.00953   0.00342  -0.1502   0.8174   0.1235
  -4.000   0.1987   0.00940   0.00324  -0.1500   0.8109   0.1324
  -3.750   0.2266   0.00926   0.00310  -0.1499   0.8045   0.1429
  -3.500   0.2541   0.00910   0.00297  -0.1498   0.7973   0.1543
  -3.250   0.2824   0.00899   0.00283  -0.1497   0.7908   0.1676
  -3.000   0.3096   0.00886   0.00275  -0.1494   0.7831   0.1834
  -2.750   0.3377   0.00876   0.00266  -0.1493   0.7765   0.2019
  -2.500   0.3654   0.00868   0.00261  -0.1492   0.7693   0.2207
  -2.250   0.3932   0.00861   0.00255  -0.1490   0.7622   0.2383
  -2.000   0.4212   0.00857   0.00252  -0.1489   0.7556   0.2555
  -1.750   0.4488   0.00853   0.00250  -0.1487   0.7483   0.2729
  -1.500   0.4769   0.00852   0.00246  -0.1485   0.7416   0.2875
  -1.250   0.5042   0.00847   0.00245  -0.1483   0.7332   0.3006
  -1.000   0.5319   0.00848   0.00241  -0.1480   0.7253   0.3142
  -0.750   0.5591   0.00845   0.00241  -0.1478   0.7166   0.3274
  -0.250   0.6141   0.00843   0.00242  -0.1473   0.7012   0.3537
   0.000   0.6414   0.00846   0.00242  -0.1470   0.6935   0.3675
   0.250   0.6686   0.00846   0.00245  -0.1467   0.6845   0.3827
   0.500   0.6956   0.00851   0.00247  -0.1464   0.6758   0.3987
   0.750   0.7225   0.00852   0.00252  -0.1460   0.6664   0.4149
   1.000   0.7494   0.00857   0.00257  -0.1457   0.6581   0.4336
   1.250   0.7762   0.00858   0.00264  -0.1453   0.6491   0.4535
   1.500   0.8027   0.00863   0.00271  -0.1449   0.6401   0.4732
   1.750   0.8289   0.00868   0.00278  -0.1445   0.6295   0.4922
   2.000   0.8552   0.00872   0.00285  -0.1440   0.6191   0.5115
   2.250   0.8810   0.00879   0.00293  -0.1435   0.6085   0.5335
   2.500   0.9065   0.00881   0.00302  -0.1429   0.5962   0.5603
   2.750   0.9317   0.00882   0.00313  -0.1423   0.5830   0.5965
   3.000   0.9556   0.00877   0.00326  -0.1414   0.5686   0.6693
   3.250   0.9794   0.00833   0.00337  -0.1403   0.5539   1.0000
   3.500   1.0041   0.00851   0.00348  -0.1396   0.5376   1.0000
   3.750   1.0282   0.00872   0.00360  -0.1388   0.5205   1.0000
   4.000   1.0520   0.00896   0.00374  -0.1379   0.5041   1.0000
   4.250   1.0758   0.00920   0.00391  -0.1371   0.4901   1.0000
   4.500   1.0992   0.00947   0.00410  -0.1362   0.4780   1.0000
   4.750   1.1222   0.00976   0.00430  -0.1352   0.4644   1.0000
   5.000   1.1449   0.01005   0.00452  -0.1342   0.4500   1.0000
   5.250   1.1680   0.01032   0.00475  -0.1333   0.4380   1.0000
   5.500   1.1908   0.01061   0.00498  -0.1323   0.4285   1.0000
   5.750   1.2142   0.01085   0.00521  -0.1315   0.4186   1.0000
   6.000   1.2371   0.01112   0.00545  -0.1305   0.4092   1.0000
   6.250   1.2595   0.01139   0.00570  -0.1295   0.3995   1.0000
   6.500   1.2821   0.01162   0.00594  -0.1285   0.3892   1.0000
   6.750   1.3031   0.01192   0.00620  -0.1272   0.3773   1.0000
   7.000   1.3232   0.01222   0.00647  -0.1258   0.3637   1.0000
   7.250   1.3426   0.01250   0.00673  -0.1242   0.3485   1.0000
   7.500   1.3598   0.01284   0.00702  -0.1223   0.3309   1.0000
   7.750   1.3755   0.01325   0.00737  -0.1201   0.3090   1.0000
   8.000   1.3880   0.01381   0.00781  -0.1175   0.2863   1.0000
   8.250   1.4005   0.01442   0.00831  -0.1149   0.2678   1.0000
   8.500   1.4133   0.01503   0.00885  -0.1125   0.2532   1.0000
   8.750   1.4265   0.01565   0.00942  -0.1102   0.2401   1.0000
   9.000   1.4407   0.01625   0.00999  -0.1081   0.2281   1.0000
   9.250   1.4547   0.01686   0.01058  -0.1060   0.2171   1.0000
   9.500   1.4675   0.01755   0.01123  -0.1039   0.2051   1.0000
   9.750   1.4801   0.01827   0.01192  -0.1018   0.1904   1.0000
  10.000   1.4919   0.01907   0.01264  -0.0996   0.1682   1.0000
  10.250   1.4948   0.02041   0.01375  -0.0965   0.1345   1.0000
  10.500   1.4990   0.02174   0.01495  -0.0937   0.1160   1.0000
  10.750   1.5056   0.02296   0.01613  -0.0913   0.1056   1.0000
  11.000   1.5126   0.02421   0.01736  -0.0891   0.0982   1.0000
  11.250   1.5223   0.02531   0.01849  -0.0872   0.0927   1.0000
  11.500   1.5305   0.02655   0.01974  -0.0853   0.0876   1.0000
  11.750   1.5375   0.02791   0.02113  -0.0834   0.0835   1.0000
  12.000   1.5488   0.02900   0.02228  -0.0819   0.0802   1.0000
  12.250   1.5572   0.03033   0.02364  -0.0803   0.0767   1.0000
  12.500   1.5618   0.03201   0.02534  -0.0786   0.0732   1.0000
  12.750   1.5729   0.03321   0.02662  -0.0774   0.0707   1.0000
  13.000   1.5818   0.03462   0.02807  -0.0761   0.0677   1.0000
  13.250   1.5875   0.03634   0.02983  -0.0748   0.0647   1.0000
  13.500   1.5932   0.03814   0.03168  -0.0735   0.0619   1.0000
  13.750   1.6027   0.03961   0.03323  -0.0726   0.0588   1.0000
  14.000   1.6077   0.04158   0.03521  -0.0715   0.0554   1.0000
  14.250   1.6139   0.04348   0.03718  -0.0706   0.0518   1.0000
  14.500   1.6181   0.04564   0.03936  -0.0698   0.0472   1.0000
  14.750   1.6221   0.04789   0.04164  -0.0691   0.0422   1.0000
  15.000   1.6221   0.05065   0.04441  -0.0684   0.0365   1.0000
  15.250   1.6202   0.05373   0.04751  -0.0679   0.0319   1.0000
  15.500   1.6169   0.05708   0.05090  -0.0675   0.0286   1.0000
  15.750   1.6142   0.06047   0.05436  -0.0673   0.0264   1.0000
  16.000   1.6098   0.06419   0.05814  -0.0673   0.0247   1.0000
  16.250   1.6033   0.06831   0.06233  -0.0676   0.0235   1.0000
  16.500   1.6004   0.07206   0.06619  -0.0680   0.0225   1.0000
  16.750   1.5959   0.07614   0.07038  -0.0686   0.0217   1.0000
  17.000   1.5892   0.08065   0.07498  -0.0694   0.0210   1.0000
  17.250   1.5800   0.08570   0.08012  -0.0706   0.0204   1.0000
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