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USA 98 AIRFOIL (usa98-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 98 AIRFOIL (usa98-il)
Reynolds number: 500,000
Max Cl/Cd: 112.65 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa98-il-500000-n5.txt
Download as CSV file: xf-usa98-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1972   0.02953   0.02497  -0.1679   0.7925   0.0422
  -8.250  -0.1718   0.02692   0.02209  -0.1719   0.7845   0.0424
  -8.000  -0.1457   0.02503   0.01993  -0.1744   0.7770   0.0427
  -7.750  -0.1187   0.02365   0.01836  -0.1761   0.7709   0.0431
  -7.500  -0.0912   0.02245   0.01698  -0.1775   0.7645   0.0435
  -7.250  -0.0634   0.02125   0.01557  -0.1788   0.7583   0.0439
  -7.000  -0.0354   0.02005   0.01412  -0.1800   0.7527   0.0443
  -6.750  -0.0068   0.01898   0.01287  -0.1810   0.7475   0.0446
  -6.500   0.0218   0.01810   0.01181  -0.1818   0.7417   0.0450
  -6.250   0.0506   0.01737   0.01090  -0.1824   0.7361   0.0453
  -6.000   0.0795   0.01675   0.01012  -0.1830   0.7313   0.0456
  -5.750   0.1087   0.01620   0.00946  -0.1835   0.7262   0.0458
  -5.500   0.1378   0.01574   0.00888  -0.1839   0.7207   0.0460
  -5.250   0.1666   0.01516   0.00822  -0.1843   0.7153   0.0464
  -5.000   0.1956   0.01477   0.00778  -0.1847   0.7107   0.0467
  -4.750   0.2249   0.01443   0.00742  -0.1850   0.7055   0.0470
  -4.500   0.2540   0.01414   0.00709  -0.1853   0.7000   0.0473
  -4.250   0.2829   0.01389   0.00678  -0.1855   0.6946   0.0477
  -4.000   0.3122   0.01365   0.00650  -0.1858   0.6899   0.0482
  -3.750   0.3415   0.01342   0.00624  -0.1860   0.6845   0.0487
  -3.500   0.3706   0.01320   0.00596  -0.1862   0.6788   0.0493
  -3.250   0.3995   0.01300   0.00569  -0.1864   0.6734   0.0498
  -3.000   0.4290   0.01276   0.00543  -0.1866   0.6682   0.0503
  -2.750   0.4582   0.01256   0.00519  -0.1868   0.6625   0.0507
  -2.500   0.4871   0.01241   0.00497  -0.1869   0.6567   0.0511
  -2.250   0.5162   0.01226   0.00479  -0.1871   0.6512   0.0514
  -2.000   0.5456   0.01200   0.00453  -0.1874   0.6453   0.0521
  -1.750   0.5745   0.01185   0.00437  -0.1875   0.6393   0.0527
  -1.500   0.6034   0.01175   0.00425  -0.1876   0.6336   0.0533
  -1.250   0.6325   0.01164   0.00414  -0.1878   0.6273   0.0540
  -1.000   0.6613   0.01157   0.00404  -0.1879   0.6209   0.0549
  -0.750   0.6898   0.01152   0.00396  -0.1879   0.6152   0.0559
  -0.500   0.7188   0.01145   0.00389  -0.1880   0.6088   0.0568
  -0.250   0.7473   0.01142   0.00382  -0.1880   0.6020   0.0575
   0.000   0.7759   0.01134   0.00373  -0.1880   0.5960   0.0586
   0.250   0.8047   0.01129   0.00369  -0.1881   0.5899   0.0597
   0.500   0.8330   0.01128   0.00366  -0.1881   0.5831   0.0610
   0.750   0.8610   0.01129   0.00365  -0.1880   0.5770   0.0624
   1.000   0.8895   0.01129   0.00365  -0.1880   0.5708   0.0639
   1.250   0.9175   0.01130   0.00365  -0.1879   0.5644   0.0662
   1.500   0.9453   0.01134   0.00368  -0.1878   0.5583   0.0692
   1.750   0.9734   0.01136   0.00371  -0.1877   0.5517   0.0726
   2.000   1.0006   0.01141   0.00375  -0.1874   0.5440   0.0790
   2.250   1.0280   0.01144   0.00381  -0.1872   0.5354   0.0944
   2.500   1.0555   0.01120   0.00394  -0.1874   0.5250   0.2589
   2.750   1.0825   0.01125   0.00408  -0.1872   0.5162   0.3091
   3.000   1.1092   0.01133   0.00422  -0.1869   0.5084   0.3391
   3.250   1.1357   0.01145   0.00436  -0.1865   0.5019   0.3634
   3.500   1.1628   0.01153   0.00450  -0.1863   0.4954   0.3861
   3.750   1.1892   0.01165   0.00466  -0.1859   0.4891   0.4078
   4.000   1.2152   0.01179   0.00482  -0.1854   0.4830   0.4286
   4.250   1.2417   0.01190   0.00498  -0.1850   0.4759   0.4500
   4.500   1.2669   0.01205   0.00516  -0.1845   0.4686   0.4708
   4.750   1.2928   0.01218   0.00533  -0.1840   0.4622   0.4903
   5.000   1.3180   0.01233   0.00551  -0.1834   0.4539   0.5082
   5.250   1.3422   0.01251   0.00571  -0.1826   0.4452   0.5264
   5.500   1.3663   0.01268   0.00593  -0.1818   0.4345   0.5519
   5.750   1.3898   0.01284   0.00619  -0.1809   0.4240   0.6060
   6.000   1.4059   0.01248   0.00640  -0.1784   0.4141   1.0000
   6.250   1.4290   0.01274   0.00664  -0.1774   0.4045   1.0000
   6.500   1.4498   0.01308   0.00691  -0.1759   0.3934   1.0000
   6.750   1.4709   0.01339   0.00718  -0.1746   0.3804   1.0000
   7.000   1.4904   0.01377   0.00750  -0.1729   0.3668   1.0000
   7.250   1.5070   0.01419   0.00785  -0.1707   0.3525   1.0000
   7.500   1.5226   0.01467   0.00826  -0.1684   0.3375   1.0000
   7.750   1.5376   0.01520   0.00872  -0.1659   0.3218   1.0000
   8.250   1.5663   0.01640   0.00977  -0.1610   0.2900   1.0000
   8.500   1.5790   0.01710   0.01039  -0.1584   0.2735   1.0000
   8.750   1.5911   0.01784   0.01106  -0.1557   0.2578   1.0000
   9.000   1.6042   0.01855   0.01173  -0.1533   0.2453   1.0000
   9.250   1.6162   0.01934   0.01246  -0.1508   0.2339   1.0000
   9.500   1.6266   0.02023   0.01330  -0.1480   0.2216   1.0000
   9.750   1.6381   0.02109   0.01413  -0.1456   0.2099   1.0000
  10.000   1.6491   0.02200   0.01501  -0.1431   0.1999   1.0000
  10.250   1.6584   0.02306   0.01603  -0.1406   0.1896   1.0000
  10.500   1.6693   0.02405   0.01701  -0.1383   0.1793   1.0000
  10.750   1.6778   0.02523   0.01817  -0.1359   0.1686   1.0000
  11.000   1.6844   0.02661   0.01950  -0.1334   0.1560   1.0000
  11.250   1.6884   0.02825   0.02108  -0.1308   0.1404   1.0000
  11.500   1.6879   0.03033   0.02307  -0.1280   0.1215   1.0000
  11.750   1.6849   0.03276   0.02540  -0.1253   0.1020   1.0000
  12.000   1.6823   0.03526   0.02784  -0.1228   0.0878   1.0000
  12.250   1.6834   0.03752   0.03008  -0.1208   0.0794   1.0000
  12.500   1.6868   0.03963   0.03221  -0.1191   0.0740   1.0000
  12.750   1.6896   0.04186   0.03446  -0.1175   0.0699   1.0000
  13.000   1.6945   0.04393   0.03657  -0.1160   0.0669   1.0000
  13.250   1.6976   0.04618   0.03885  -0.1146   0.0641   1.0000
  13.500   1.7007   0.04848   0.04120  -0.1133   0.0620   1.0000
  13.750   1.7051   0.05070   0.04348  -0.1121   0.0601   1.0000
  14.000   1.7081   0.05308   0.04592  -0.1109   0.0583   1.0000
  14.250   1.7094   0.05571   0.04859  -0.1098   0.0566   1.0000
  14.500   1.7111   0.05831   0.05125  -0.1088   0.0551   1.0000
  14.750   1.7147   0.06074   0.05376  -0.1079   0.0538   1.0000
  15.000   1.7166   0.06343   0.05651  -0.1070   0.0524   1.0000
  15.250   1.7173   0.06628   0.05943  -0.1063   0.0511   1.0000
  15.500   1.7170   0.06930   0.06250  -0.1055   0.0498   1.0000
  15.750   1.7173   0.07229   0.06556  -0.1049   0.0487   1.0000
  16.000   1.7191   0.07510   0.06845  -0.1044   0.0475   1.0000
  16.250   1.7197   0.07811   0.07154  -0.1039   0.0463   1.0000
  16.500   1.7187   0.08136   0.07486  -0.1036   0.0452   1.0000
  16.750   1.7170   0.08472   0.07827  -0.1033   0.0441   1.0000
  17.000   1.7151   0.08813   0.08175  -0.1030   0.0432   1.0000
  17.250   1.7151   0.09131   0.08502  -0.1029   0.0422   1.0000
  17.500   1.7144   0.09458   0.08837  -0.1028   0.0411   1.0000
  17.750   1.7122   0.09812   0.09199  -0.1029   0.0400   1.0000
  18.000   1.7098   0.10169   0.09562  -0.1030   0.0390   1.0000
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