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USA 98 AIRFOIL (usa98-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 98 AIRFOIL (usa98-il)
Reynolds number: 200,000
Max Cl/Cd: 84.26 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa98-il-200000-n5.txt
Download as CSV file: xf-usa98-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 98 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.0992   0.10390   0.09967  -0.0796   0.9498   0.0629
  -8.750  -0.1106   0.09906   0.09481  -0.0866   0.9326   0.0642
  -8.250  -0.0853   0.09111   0.08683  -0.0936   0.9041   0.0644
  -8.000  -0.0577   0.08812   0.08380  -0.0957   0.8938   0.0648
  -7.000   0.0056   0.06983   0.06510  -0.1152   0.8376   0.0571
  -6.750   0.0216   0.06730   0.06249  -0.1174   0.8261   0.0567
  -6.500   0.0353   0.06419   0.05928  -0.1206   0.8158   0.0562
  -6.250   0.0478   0.06043   0.05546  -0.1249   0.8064   0.0558
  -6.000   0.0621   0.05562   0.05055  -0.1314   0.7977   0.0554
  -5.750   0.0930   0.03222   0.02609  -0.1698   0.7903   0.0553
  -5.500   0.1229   0.02857   0.02195  -0.1746   0.7832   0.0556
  -5.250   0.1533   0.02621   0.01915  -0.1774   0.7768   0.0560
  -5.000   0.1835   0.02445   0.01701  -0.1794   0.7708   0.0565
  -4.750   0.2129   0.02307   0.01532  -0.1807   0.7643   0.0569
  -4.500   0.2430   0.02202   0.01393  -0.1818   0.7582   0.0576
  -4.250   0.2721   0.02126   0.01307  -0.1825   0.7529   0.0582
  -4.000   0.3002   0.02066   0.01242  -0.1828   0.7465   0.0588
  -3.750   0.3291   0.02008   0.01175  -0.1833   0.7403   0.0594
  -3.500   0.3584   0.01952   0.01104  -0.1837   0.7350   0.0599
  -3.250   0.3875   0.01898   0.01040  -0.1841   0.7293   0.0605
  -3.000   0.4162   0.01848   0.00981  -0.1843   0.7230   0.0611
  -2.750   0.4453   0.01803   0.00925  -0.1846   0.7172   0.0618
  -2.500   0.4747   0.01764   0.00874  -0.1848   0.7122   0.0625
  -2.250   0.5031   0.01727   0.00832  -0.1849   0.7059   0.0633
  -2.000   0.5319   0.01700   0.00796  -0.1850   0.6998   0.0642
  -1.750   0.5607   0.01664   0.00760  -0.1852   0.6944   0.0654
  -1.500   0.5891   0.01639   0.00738  -0.1853   0.6886   0.0665
  -1.250   0.6175   0.01616   0.00716  -0.1854   0.6823   0.0677
  -1.000   0.6463   0.01596   0.00692  -0.1854   0.6765   0.0687
  -0.750   0.6750   0.01578   0.00672  -0.1855   0.6709   0.0699
  -0.500   0.7033   0.01562   0.00657  -0.1855   0.6645   0.0712
  -0.250   0.7319   0.01548   0.00641  -0.1856   0.6585   0.0724
   0.000   0.7607   0.01534   0.00628  -0.1857   0.6530   0.0745
   0.250   0.7888   0.01526   0.00625  -0.1857   0.6463   0.0771
   0.500   0.8172   0.01521   0.00617  -0.1857   0.6402   0.0798
   0.750   0.8459   0.01516   0.00606  -0.1857   0.6348   0.0825
   1.000   0.8737   0.01510   0.00606  -0.1856   0.6279   0.0861
   1.750   0.9588   0.01468   0.00607  -0.1860   0.6095   0.2231
   2.000   0.9863   0.01463   0.00625  -0.1859   0.6030   0.3233
   2.250   1.0138   0.01471   0.00637  -0.1857   0.5976   0.3616
   2.500   1.0405   0.01479   0.00655  -0.1853   0.5908   0.3925
   2.750   1.0671   0.01489   0.00670  -0.1849   0.5842   0.4192
   3.000   1.0940   0.01501   0.00682  -0.1846   0.5784   0.4463
   3.250   1.1197   0.01510   0.00702  -0.1841   0.5702   0.4752
   3.500   1.1452   0.01520   0.00712  -0.1834   0.5612   0.5023
   3.750   1.1700   0.01529   0.00728  -0.1827   0.5515   0.5246
   4.000   1.1952   0.01540   0.00740  -0.1820   0.5432   0.5450
   4.250   1.2205   0.01551   0.00760  -0.1814   0.5363   0.5723
   4.500   1.2452   0.01557   0.00780  -0.1807   0.5292   0.6230
   4.750   1.2632   0.01517   0.00785  -0.1782   0.5229   0.9692
   5.000   1.2886   0.01539   0.00807  -0.1777   0.5156   1.0000
   5.250   1.3133   0.01564   0.00828  -0.1770   0.5086   1.0000
   5.500   1.3378   0.01591   0.00849  -0.1762   0.5020   1.0000
   5.750   1.3616   0.01616   0.00875  -0.1754   0.4943   1.0000
   6.000   1.3849   0.01645   0.00899  -0.1744   0.4868   1.0000
   6.250   1.4081   0.01672   0.00928  -0.1734   0.4794   1.0000
   6.500   1.4303   0.01702   0.00957  -0.1723   0.4712   1.0000
   6.750   1.4515   0.01734   0.00987  -0.1710   0.4624   1.0000
   7.000   1.4712   0.01767   0.01019  -0.1693   0.4517   1.0000
   7.250   1.4902   0.01803   0.01053  -0.1676   0.4411   1.0000
   7.500   1.5072   0.01843   0.01089  -0.1655   0.4301   1.0000
   7.750   1.5245   0.01881   0.01129  -0.1635   0.4188   1.0000
   8.000   1.5385   0.01926   0.01172  -0.1608   0.4080   1.0000
   8.250   1.5517   0.01976   0.01221  -0.1581   0.3960   1.0000
   8.500   1.5649   0.02031   0.01274  -0.1555   0.3832   1.0000
   8.750   1.5764   0.02094   0.01336  -0.1526   0.3698   1.0000
   9.000   1.5868   0.02166   0.01404  -0.1497   0.3568   1.0000
   9.250   1.5973   0.02242   0.01478  -0.1468   0.3429   1.0000
   9.500   1.6062   0.02329   0.01562  -0.1439   0.3281   1.0000
   9.750   1.6139   0.02427   0.01656  -0.1408   0.3137   1.0000
  10.000   1.6205   0.02537   0.01763  -0.1378   0.2998   1.0000
  10.250   1.6256   0.02661   0.01882  -0.1348   0.2860   1.0000
  10.750   1.6349   0.02940   0.02156  -0.1291   0.2596   1.0000
  11.000   1.6397   0.03091   0.02307  -0.1266   0.2484   1.0000
  11.250   1.6426   0.03264   0.02477  -0.1240   0.2383   1.0000
  11.500   1.6488   0.03422   0.02639  -0.1220   0.2280   1.0000
  11.750   1.6522   0.03608   0.02825  -0.1199   0.2187   1.0000
  12.000   1.6555   0.03802   0.03020  -0.1179   0.2087   1.0000
  12.250   1.6593   0.03997   0.03219  -0.1161   0.1989   1.0000
  12.500   1.6600   0.04227   0.03449  -0.1143   0.1889   1.0000
  12.750   1.6622   0.04450   0.03674  -0.1126   0.1772   1.0000
  13.000   1.6624   0.04697   0.03922  -0.1110   0.1648   1.0000
  13.250   1.6602   0.04976   0.04198  -0.1094   0.1508   1.0000
  13.500   1.6553   0.05290   0.04509  -0.1079   0.1355   1.0000
  14.000   1.6403   0.05999   0.05209  -0.1051   0.1070   1.0000
  14.250   1.6329   0.06367   0.05575  -0.1040   0.0971   1.0000
  14.500   1.6272   0.06726   0.05934  -0.1031   0.0900   1.0000
  14.750   1.6225   0.07079   0.06292  -0.1023   0.0850   1.0000
  15.000   1.6179   0.07440   0.06657  -0.1016   0.0809   1.0000
  15.250   1.6133   0.07808   0.07031  -0.1012   0.0777   1.0000
  15.500   1.6106   0.08157   0.07387  -0.1008   0.0747   1.0000
  15.750   1.6058   0.08538   0.07775  -0.1005   0.0722   1.0000
  16.000   1.5998   0.08940   0.08183  -0.1004   0.0702   1.0000
  16.250   1.5987   0.09278   0.08532  -0.1003   0.0681   1.0000
  16.500   1.5957   0.09648   0.08910  -0.1004   0.0661   1.0000
  16.750   1.5913   0.10038   0.09307  -0.1006   0.0644   1.0000
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