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GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 499 AIRFOIL (goe499-il)
Reynolds number: 100,000
Max Cl/Cd: 71.22 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe499-il-100000.txt
Download as CSV file: xf-goe499-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 499 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3794   0.10651   0.10219  -0.0170   1.0000   0.0757
  -6.750  -0.3922   0.10573   0.10148  -0.0150   1.0000   0.0775
  -6.500  -0.4049   0.10535   0.10117  -0.0151   1.0000   0.0790
  -6.250  -0.4102   0.10511   0.10100  -0.0215   1.0000   0.0800
  -6.000  -0.4092   0.10090   0.09683  -0.0208   1.0000   0.0809
  -5.750  -0.4061   0.09703   0.09297  -0.0144   1.0000   0.0830
  -5.500  -0.4030   0.09451   0.09047  -0.0131   1.0000   0.0858
  -5.250  -0.3987   0.09207   0.08804  -0.0144   1.0000   0.0894
  -5.000  -0.3703   0.08870   0.08463  -0.0327   1.0000   0.0943
  -4.750  -0.3768   0.08539   0.08137  -0.0241   1.0000   0.0959
  -4.500  -0.3730   0.08301   0.07901  -0.0208   1.0000   0.1002
  -4.250  -0.3326   0.07836   0.07425  -0.0374   1.0000   0.1090
  -4.000  -0.3327   0.07566   0.07157  -0.0321   1.0000   0.1111
  -3.750  -0.2779   0.07089   0.06660  -0.0497   1.0000   0.1230
  -3.500  -0.2780   0.06819   0.06396  -0.0445   1.0000   0.1247
  -3.250  -0.2660   0.06584   0.06161  -0.0433   1.0000   0.1301
  -3.000  -0.2115   0.06164   0.05726  -0.0543   0.9946   0.1443
  -2.750  -0.1450   0.05707   0.05247  -0.0675   0.9855   0.1588
  -2.500  -0.0849   0.05314   0.04835  -0.0785   0.9774   0.1743
  -2.250  -0.0225   0.04959   0.04459  -0.0894   0.9713   0.1977
  -2.000   0.0377   0.04677   0.04146  -0.0999   0.9646   0.2238
  -1.750   0.1933   0.03028   0.02207  -0.1301   0.9699   0.0934
  -1.500   0.2294   0.02887   0.02032  -0.1322   0.9634   0.0949
  -1.250   0.2718   0.02817   0.01952  -0.1354   0.9583   0.1006
  -1.000   0.3085   0.02747   0.01858  -0.1372   0.9520   0.1032
  -0.750   0.3476   0.02696   0.01785  -0.1393   0.9459   0.1076
  -0.500   0.3867   0.02651   0.01751  -0.1416   0.9402   0.1178
  -0.250   0.4221   0.02611   0.01725  -0.1431   0.9328   0.1456
   0.000   0.4671   0.02590   0.01743  -0.1466   0.9275   0.2877
   0.250   0.4983   0.02589   0.01760  -0.1475   0.9183   0.3582
   0.500   0.5358   0.02585   0.01779  -0.1494   0.9112   0.4323
   0.750   0.5723   0.02551   0.01797  -0.1510   0.9036   0.5871
   1.000   0.6003   0.02482   0.01778  -0.1507   0.8943   1.0000
   1.250   0.6448   0.02489   0.01764  -0.1536   0.8877   1.0000
   1.500   0.6755   0.02506   0.01770  -0.1540   0.8766   1.0000
   1.750   0.7113   0.02515   0.01773  -0.1553   0.8675   1.0000
   2.000   0.7535   0.02504   0.01758  -0.1576   0.8602   1.0000
   2.250   0.7852   0.02508   0.01760  -0.1581   0.8489   1.0000
   2.500   0.8341   0.02465   0.01722  -0.1612   0.8438   1.0000
   2.750   0.8666   0.02452   0.01714  -0.1616   0.8322   1.0000
   3.000   0.8992   0.02439   0.01707  -0.1620   0.8208   1.0000
   3.250   0.9503   0.02362   0.01644  -0.1652   0.8167   1.0000
   3.500   0.9823   0.02333   0.01626  -0.1651   0.8043   1.0000
   3.750   1.0163   0.02288   0.01594  -0.1653   0.7922   1.0000
   4.000   1.0534   0.02211   0.01535  -0.1656   0.7801   1.0000
   4.250   1.1066   0.01907   0.01243  -0.1658   0.7600   1.0000
   4.500   1.1328   0.01788   0.01132  -0.1631   0.7277   1.0000
   4.750   1.1573   0.01690   0.01032  -0.1601   0.6779   1.0000
   5.000   1.1794   0.01656   0.00948  -0.1564   0.5720   1.0000
   5.250   1.1813   0.01824   0.00994  -0.1505   0.4100   1.0000
   5.500   1.1661   0.02228   0.01179  -0.1442   0.1009   1.0000
   5.750   1.1787   0.02396   0.01327  -0.1414   0.0679   1.0000
   6.250   1.2042   0.02667   0.01619  -0.1359   0.0570   1.0000
   6.500   1.2139   0.02803   0.01766  -0.1328   0.0532   1.0000
   6.750   1.2197   0.02969   0.01934  -0.1293   0.0500   1.0000
   7.000   1.2299   0.03184   0.02148  -0.1265   0.0482   1.0000
   7.250   1.2578   0.03386   0.02352  -0.1260   0.0475   1.0000
   7.500   1.3029   0.03665   0.02634  -0.1280   0.0472   1.0000
   7.750   1.3506   0.04028   0.03006  -0.1302   0.0477   1.0000
   8.000   1.3809   0.04313   0.03321  -0.1298   0.0472   1.0000
   8.250   1.4084   0.04656   0.03702  -0.1292   0.0473   1.0000
   8.500   1.4377   0.04952   0.04031  -0.1282   0.0502   1.0000
  12.250   0.9600   0.15716   0.15369  -0.1205   0.1693   1.0000
  12.500   0.9869   0.16047   0.15705  -0.1177   0.1659   1.0000
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