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USA 98 AIRFOIL (usa98-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: USA 98 AIRFOIL (usa98-il)
Reynolds number: 1,000,000
Max Cl/Cd: 124.31 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa98-il-1000000-n5.txt
Download as CSV file: xf-usa98-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6264   0.03309   0.03002  -0.1516   0.9623   0.0375
 -12.000  -0.5946   0.02662   0.02326  -0.1663   0.9572   0.0376
 -11.750  -0.5709   0.02475   0.02126  -0.1692   0.9477   0.0378
 -11.500  -0.5414   0.02328   0.01968  -0.1721   0.9372   0.0379
 -11.250  -0.5064   0.02200   0.01822  -0.1755   0.9067   0.0380
 -10.750  -0.4561   0.02055   0.01614  -0.1770   0.8127   0.0383
 -10.500  -0.4298   0.01981   0.01526  -0.1777   0.8001   0.0384
 -10.250  -0.4031   0.01914   0.01446  -0.1784   0.7902   0.0386
 -10.000  -0.3758   0.01847   0.01367  -0.1791   0.7815   0.0388
  -9.500  -0.3205   0.01729   0.01227  -0.1803   0.7673   0.0391
  -9.250  -0.2923   0.01679   0.01169  -0.1808   0.7607   0.0394
  -9.000  -0.2643   0.01632   0.01111  -0.1813   0.7543   0.0396
  -8.750  -0.2356   0.01581   0.01051  -0.1818   0.7494   0.0398
  -8.500  -0.2069   0.01531   0.00992  -0.1823   0.7438   0.0400
  -8.250  -0.1783   0.01486   0.00938  -0.1828   0.7380   0.0402
  -8.000  -0.1497   0.01446   0.00888  -0.1832   0.7326   0.0404
  -7.750  -0.1204   0.01406   0.00841  -0.1836   0.7282   0.0405
  -7.500  -0.0913   0.01369   0.00798  -0.1840   0.7229   0.0407
  -7.250  -0.0622   0.01337   0.00757  -0.1844   0.7175   0.0408
  -7.000  -0.0332   0.01309   0.00721  -0.1847   0.7126   0.0410
  -6.750  -0.0036   0.01280   0.00687  -0.1851   0.7084   0.0411
  -6.500   0.0258   0.01243   0.00645  -0.1855   0.7033   0.0413
  -6.250   0.0551   0.01208   0.00605  -0.1858   0.6979   0.0416
  -6.000   0.0843   0.01183   0.00575  -0.1861   0.6930   0.0419
  -5.750   0.1140   0.01161   0.00550  -0.1865   0.6888   0.0421
  -5.500   0.1436   0.01141   0.00528  -0.1868   0.6835   0.0424
  -5.250   0.1730   0.01125   0.00508  -0.1870   0.6780   0.0426
  -5.000   0.2023   0.01111   0.00489  -0.1873   0.6731   0.0429
  -4.750   0.2321   0.01094   0.00471  -0.1876   0.6686   0.0432
  -4.500   0.2617   0.01079   0.00453  -0.1878   0.6630   0.0435
  -4.250   0.2910   0.01066   0.00435  -0.1880   0.6571   0.0438
  -4.000   0.3205   0.01053   0.00419  -0.1883   0.6523   0.0441
  -3.750   0.3501   0.01040   0.00404  -0.1885   0.6471   0.0445
  -3.500   0.3795   0.01029   0.00390  -0.1887   0.6409   0.0449
  -3.250   0.4086   0.01022   0.00377  -0.1888   0.6348   0.0453
  -3.000   0.4383   0.01011   0.00364  -0.1891   0.6296   0.0456
  -2.750   0.4677   0.01002   0.00352  -0.1893   0.6235   0.0458
  -2.500   0.4967   0.00995   0.00341  -0.1894   0.6169   0.0461
  -2.250   0.5264   0.00979   0.00324  -0.1897   0.6110   0.0467
  -2.000   0.5558   0.00971   0.00313  -0.1898   0.6045   0.0472
  -1.750   0.5847   0.00967   0.00306  -0.1899   0.5980   0.0477
  -1.500   0.6140   0.00962   0.00300  -0.1901   0.5921   0.0482
  -1.250   0.6431   0.00958   0.00295  -0.1902   0.5849   0.0488
  -1.000   0.6718   0.00958   0.00290  -0.1902   0.5783   0.0494
  -0.750   0.7011   0.00954   0.00286  -0.1904   0.5728   0.0500
  -0.500   0.7299   0.00953   0.00282  -0.1904   0.5660   0.0506
  -0.250   0.7584   0.00955   0.00281  -0.1904   0.5592   0.0511
   0.000   0.7875   0.00953   0.00278  -0.1905   0.5536   0.0519
   0.250   0.8163   0.00951   0.00276  -0.1906   0.5474   0.0530
   0.500   0.8445   0.00954   0.00276  -0.1905   0.5410   0.0539
   0.750   0.8734   0.00954   0.00277  -0.1906   0.5354   0.0549
   1.000   0.9017   0.00958   0.00279  -0.1906   0.5277   0.0559
   1.250   0.9296   0.00964   0.00282  -0.1904   0.5194   0.0569
   1.500   0.9575   0.00970   0.00285  -0.1903   0.5097   0.0582
   1.750   0.9852   0.00977   0.00290  -0.1902   0.5006   0.0603
   2.000   1.0129   0.00984   0.00295  -0.1900   0.4913   0.0629
   2.250   1.0404   0.00992   0.00302  -0.1898   0.4836   0.0667
   2.500   1.0685   0.00996   0.00308  -0.1898   0.4777   0.0738
   2.750   1.0964   0.00999   0.00316  -0.1897   0.4716   0.0951
   3.000   1.1247   0.00978   0.00328  -0.1900   0.4653   0.2548
   3.250   1.1526   0.00981   0.00339  -0.1899   0.4588   0.2918
   3.500   1.1795   0.00990   0.00352  -0.1897   0.4513   0.3200
   3.750   1.2066   0.00999   0.00365  -0.1895   0.4454   0.3462
   4.000   1.2336   0.01009   0.00379  -0.1892   0.4372   0.3678
   4.250   1.2595   0.01025   0.00394  -0.1887   0.4277   0.3848
   4.500   1.2858   0.01038   0.00409  -0.1883   0.4181   0.4021
   4.750   1.3110   0.01058   0.00427  -0.1878   0.4069   0.4196
   5.000   1.3357   0.01079   0.00447  -0.1871   0.3942   0.4393
   5.250   1.3612   0.01095   0.00464  -0.1866   0.3849   0.4569
   5.500   1.3855   0.01118   0.00485  -0.1858   0.3747   0.4734
   5.750   1.4094   0.01141   0.00507  -0.1850   0.3616   0.4873
   6.000   1.4314   0.01174   0.00534  -0.1838   0.3437   0.5004
   6.250   1.4526   0.01210   0.00563  -0.1825   0.3258   0.5158
   6.500   1.4740   0.01240   0.00593  -0.1813   0.3107   0.5393
   6.750   1.4948   0.01271   0.00626  -0.1799   0.2960   0.5851
   7.000   1.5093   0.01252   0.00667  -0.1773   0.2804   1.0000
   7.250   1.5262   0.01303   0.00707  -0.1751   0.2616   1.0000
   7.500   1.5418   0.01350   0.00747  -0.1727   0.2470   1.0000
   7.750   1.5578   0.01398   0.00788  -0.1704   0.2350   1.0000
   8.000   1.5734   0.01449   0.00832  -0.1681   0.2231   1.0000
   8.250   1.5900   0.01497   0.00876  -0.1661   0.2120   1.0000
   8.500   1.6059   0.01549   0.00923  -0.1639   0.2025   1.0000
   8.750   1.6208   0.01606   0.00975  -0.1616   0.1918   1.0000
   9.000   1.6358   0.01664   0.01028  -0.1593   0.1803   1.0000
   9.250   1.6489   0.01732   0.01090  -0.1568   0.1684   1.0000
   9.500   1.6606   0.01809   0.01160  -0.1542   0.1552   1.0000
   9.750   1.6698   0.01902   0.01244  -0.1512   0.1389   1.0000
  10.000   1.6744   0.02022   0.01352  -0.1476   0.1197   1.0000
  10.250   1.6759   0.02167   0.01485  -0.1438   0.0983   1.0000
  10.500   1.6779   0.02317   0.01626  -0.1403   0.0815   1.0000
  10.750   1.6850   0.02443   0.01749  -0.1376   0.0733   1.0000
  11.000   1.6939   0.02563   0.01869  -0.1353   0.0682   1.0000
  11.250   1.7031   0.02687   0.01993  -0.1332   0.0642   1.0000
  11.500   1.7131   0.02810   0.02118  -0.1313   0.0614   1.0000
  11.750   1.7235   0.02935   0.02245  -0.1295   0.0592   1.0000
  12.000   1.7325   0.03075   0.02388  -0.1278   0.0571   1.0000
  12.250   1.7417   0.03220   0.02536  -0.1262   0.0552   1.0000
  12.500   1.7518   0.03362   0.02681  -0.1247   0.0537   1.0000
  12.750   1.7607   0.03516   0.02839  -0.1233   0.0521   1.0000
  13.000   1.7685   0.03682   0.03008  -0.1218   0.0507   1.0000
  13.250   1.7754   0.03861   0.03190  -0.1203   0.0492   1.0000
  13.500   1.7841   0.04025   0.03359  -0.1191   0.0481   1.0000
  13.750   1.7920   0.04199   0.03537  -0.1178   0.0467   1.0000
  14.000   1.7980   0.04395   0.03737  -0.1165   0.0454   1.0000
  14.250   1.8027   0.04603   0.03949  -0.1152   0.0441   1.0000
  14.500   1.8083   0.04805   0.04155  -0.1140   0.0431   1.0000
  14.750   1.8137   0.05014   0.04370  -0.1129   0.0420   1.0000
  15.000   1.8187   0.05228   0.04588  -0.1118   0.0408   1.0000
  15.250   1.8217   0.05467   0.04832  -0.1108   0.0395   1.0000
  15.500   1.8234   0.05724   0.05092  -0.1097   0.0382   1.0000
  15.750   1.8275   0.05956   0.05330  -0.1088   0.0373   1.0000
  16.000   1.8298   0.06215   0.05595  -0.1079   0.0362   1.0000
  16.250   1.8319   0.06477   0.05861  -0.1071   0.0351   1.0000
  16.500   1.8322   0.06764   0.06154  -0.1064   0.0341   1.0000
  16.750   1.8323   0.07058   0.06453  -0.1057   0.0332   1.0000
  17.000   1.8339   0.07333   0.06735  -0.1051   0.0324   1.0000
  17.250   1.8332   0.07642   0.07050  -0.1046   0.0315   1.0000
  17.500   1.8323   0.07955   0.07368  -0.1041   0.0305   1.0000
  17.750   1.8301   0.08287   0.07705  -0.1037   0.0296   1.0000
  18.000   1.8276   0.08628   0.08053  -0.1035   0.0289   1.0000
  18.250   1.8270   0.08941   0.08373  -0.1032   0.0283   1.0000
  18.500   1.8241   0.09291   0.08729  -0.1031   0.0276   1.0000
  18.750   1.8215   0.09636   0.09081  -0.1031   0.0270   1.0000
  19.000   1.8180   0.09996   0.09448  -0.1031   0.0264   1.0000
  19.250   1.8134   0.10378   0.09835  -0.1033   0.0258   1.0000
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