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USA 98 AIRFOIL (usa98-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: USA 98 AIRFOIL (usa98-il)
Reynolds number: 100,000
Max Cl/Cd: 54.21 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa98-il-100000.txt
Download as CSV file: xf-usa98-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.1326   0.10341   0.09831  -0.0649   0.9454   0.1324
  -6.500  -0.1288   0.10143   0.09633  -0.0678   0.9365   0.1370
  -6.250  -0.1425   0.09935   0.09429  -0.0757   0.9231   0.1404
  -6.000  -0.1167   0.09576   0.09069  -0.0731   0.9191   0.1421
  -5.750  -0.0877   0.09252   0.08744  -0.0747   0.9150   0.1457
  -5.500  -0.0768   0.09024   0.08517  -0.0772   0.9062   0.1510
  -5.250  -0.0633   0.08645   0.08136  -0.0861   0.8980   0.1571
  -5.000  -0.0289   0.08330   0.07820  -0.0862   0.8962   0.1615
  -4.750  -0.0246   0.08096   0.07582  -0.0977   0.8823   0.1725
  -4.500   0.0046   0.07767   0.07255  -0.0947   0.8805   0.1751
  -4.250   0.0189   0.07651   0.07132  -0.1034   0.8680   0.1881
  -4.000   0.0449   0.07244   0.06728  -0.1031   0.8652   0.1911
  -3.750   0.0800   0.06961   0.06444  -0.1037   0.8633   0.1969
  -3.500   0.0987   0.05928   0.05442  -0.0981   0.8294   0.2092
  -3.250   0.1225   0.06512   0.05992  -0.1089   0.8483   0.2149
  -3.000   0.1687   0.06159   0.05633  -0.1166   0.8460   0.2306
  -2.750   0.2161   0.05835   0.05303  -0.1236   0.8440   0.2485
  -2.500   0.3315   0.03771   0.03057  -0.1682   0.8352   0.1419
  -2.250   0.3820   0.03457   0.02701  -0.1736   0.8315   0.1344
  -2.000   0.4342   0.03201   0.02401  -0.1787   0.8287   0.1330
  -1.750   0.4863   0.02986   0.02142  -0.1833   0.8262   0.1314
  -1.500   0.5049   0.02966   0.02101  -0.1820   0.8156   0.1306
  -1.250   0.5467   0.02846   0.01958  -0.1842   0.8107   0.1310
  -1.000   0.5920   0.02730   0.01824  -0.1870   0.8072   0.1330
  -0.750   0.6098   0.02756   0.01845  -0.1854   0.7973   0.1357
  -0.500   0.6453   0.02705   0.01779  -0.1864   0.7912   0.1391
  -0.250   0.6872   0.02602   0.01680  -0.1884   0.7872   0.1429
   0.000   0.7026   0.02648   0.01736  -0.1864   0.7771   0.1463
   0.250   0.7355   0.02617   0.01704  -0.1870   0.7709   0.1527
   0.500   0.7758   0.02551   0.01644  -0.1888   0.7666   0.1653
   0.750   0.7896   0.02617   0.01723  -0.1866   0.7563   0.1768
   1.000   0.8238   0.02574   0.01713  -0.1876   0.7503   0.2281
   1.250   0.8623   0.02552   0.01741  -0.1887   0.7461   0.4482
   1.500   0.8716   0.02664   0.01865  -0.1856   0.7354   0.4882
   1.750   0.9018   0.02667   0.01874  -0.1855   0.7296   0.5322
   2.000   0.9383   0.02642   0.01849  -0.1862   0.7256   0.5737
   2.250   0.9449   0.02754   0.01976  -0.1829   0.7147   0.6006
   2.500   0.9752   0.02732   0.01968  -0.1826   0.7093   0.6510
   2.750   1.0107   0.02682   0.01930  -0.1831   0.7055   0.7103
   3.000   1.0129   0.02786   0.02065  -0.1791   0.6944   0.7635
   3.250   1.0454   0.02731   0.02020  -0.1793   0.6891   1.0000
   3.500   1.0774   0.02762   0.02032  -0.1800   0.6832   1.0000
   3.750   1.0930   0.02854   0.02119  -0.1782   0.6736   1.0000
   4.000   1.1325   0.02815   0.02063  -0.1796   0.6685   1.0000
   4.250   1.1477   0.02898   0.02145  -0.1775   0.6589   1.0000
   4.500   1.1806   0.02874   0.02112  -0.1777   0.6516   1.0000
   4.750   1.2254   0.02800   0.02019  -0.1796   0.6470   1.0000
   5.000   1.2296   0.02929   0.02159  -0.1759   0.6356   1.0000
   5.250   1.2682   0.02883   0.02102  -0.1770   0.6302   1.0000
   5.500   1.2838   0.02963   0.02187  -0.1749   0.6214   1.0000
   5.750   1.3114   0.02968   0.02189  -0.1745   0.6139   1.0000
   6.000   1.3554   0.02902   0.02111  -0.1764   0.6092   1.0000
   6.250   1.3583   0.03031   0.02254  -0.1724   0.5981   1.0000
   6.500   1.3984   0.02974   0.02189  -0.1737   0.5922   1.0000
   6.750   1.4097   0.03063   0.02288  -0.1710   0.5824   1.0000
   7.000   1.4435   0.03032   0.02252  -0.1713   0.5750   1.0000
   7.250   1.4647   0.03070   0.02293  -0.1699   0.5663   1.0000
   7.500   1.4904   0.03077   0.02302  -0.1691   0.5574   1.0000
   7.750   1.5177   0.03084   0.02309  -0.1686   0.5489   1.0000
   8.000   1.5401   0.03094   0.02321  -0.1672   0.5386   1.0000
   8.250   1.5618   0.03108   0.02338  -0.1657   0.5279   1.0000
   8.500   1.5977   0.03045   0.02263  -0.1662   0.5171   1.0000
   8.750   1.6060   0.03102   0.02331  -0.1626   0.5044   1.0000
   9.000   1.6310   0.03086   0.02312  -0.1615   0.4923   1.0000
   9.250   1.6587   0.03060   0.02276  -0.1608   0.4799   1.0000
   9.500   1.6631   0.03127   0.02354  -0.1567   0.4669   1.0000
   9.750   1.6785   0.03152   0.02380  -0.1542   0.4543   1.0000
  10.000   1.7011   0.03147   0.02364  -0.1528   0.4413   1.0000
  10.250   1.7013   0.03214   0.02440  -0.1480   0.4282   1.0000
  10.500   1.7022   0.03281   0.02512  -0.1433   0.4157   1.0000
  10.750   1.7122   0.03326   0.02553  -0.1402   0.4032   1.0000
  11.000   1.7161   0.03404   0.02633  -0.1363   0.3910   1.0000
  11.250   1.7148   0.03519   0.02757  -0.1320   0.3790   1.0000
  11.500   1.7209   0.03606   0.02842  -0.1288   0.3672   1.0000
  11.750   1.7238   0.03711   0.02947  -0.1254   0.3551   1.0000
  12.000   1.7190   0.03875   0.03121  -0.1214   0.3431   1.0000
  12.250   1.7197   0.04016   0.03263  -0.1182   0.3312   1.0000
  12.500   1.7220   0.04151   0.03392  -0.1153   0.3187   1.0000
  12.750   1.7124   0.04385   0.03641  -0.1118   0.3064   1.0000
  13.000   1.7069   0.04608   0.03868  -0.1089   0.2935   1.0000
  13.250   1.7009   0.04844   0.04104  -0.1063   0.2801   1.0000
  13.500   1.6928   0.05109   0.04367  -0.1037   0.2659   1.0000
  13.750   1.6819   0.05414   0.04669  -0.1013   0.2507   1.0000
  14.000   1.6678   0.05776   0.05029  -0.0991   0.2344   1.0000
  14.250   1.6511   0.06189   0.05442  -0.0973   0.2169   1.0000
  14.500   1.6335   0.06636   0.05886  -0.0957   0.1988   1.0000
  14.750   1.6173   0.07089   0.06333  -0.0944   0.1816   1.0000
  15.000   1.6046   0.07515   0.06750  -0.0934   0.1669   1.0000
  15.250   1.5964   0.07895   0.07119  -0.0924   0.1553   1.0000
  15.500   1.5923   0.08222   0.07432  -0.0916   0.1459   1.0000
  15.750   1.5889   0.08567   0.07784  -0.0910   0.1375   1.0000
  16.000   1.5906   0.08826   0.08031  -0.0901   0.1307   1.0000
  16.250   1.5915   0.09111   0.08321  -0.0895   0.1246   1.0000
  16.500   1.5988   0.09291   0.08490  -0.0884   0.1193   1.0000
  16.750   1.6009   0.09568   0.08778  -0.0880   0.1147   1.0000
  17.000   1.6160   0.09630   0.08818  -0.0866   0.1099   1.0000
  17.250   1.6166   0.09939   0.09147  -0.0863   0.1065   1.0000
  17.500   1.6224   0.10165   0.09379  -0.0858   0.1030   1.0000
  17.750   1.6483   0.10089   0.09277  -0.0839   0.0989   1.0000
  18.000   1.6430   0.10485   0.09702  -0.0842   0.0967   1.0000
  18.250   1.6435   0.10798   0.10033  -0.0843   0.0943   1.0000
  18.500   1.6554   0.10940   0.10173  -0.0836   0.0916   1.0000
  18.750   1.6778   0.10954   0.10177  -0.0822   0.0888   1.0000
  19.000   1.6663   0.11440   0.10695  -0.0833   0.0875   1.0000
  19.250   1.6573   0.11906   0.11186  -0.0845   0.0861   1.0000
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