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