USA 98 AIRFOIL (usa98-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 98 AIRFOIL (usa98-il) Reynolds number: 1,000,000 Max Cl/Cd: 147.37 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa98-il-1000000.txt Download as CSV file: xf-usa98-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.0314 0.07660 0.07388 -0.1104 0.8113 0.0435
-8.000 -0.0204 0.07475 0.07196 -0.1111 0.7996 0.0437
-7.750 -0.0099 0.07277 0.06994 -0.1119 0.7898 0.0439
-7.500 0.0004 0.07067 0.06781 -0.1130 0.7818 0.0442
-7.250 0.0096 0.06839 0.06551 -0.1143 0.7744 0.0445
-7.000 0.0163 0.06598 0.06306 -0.1156 0.7669 0.0450
-6.750 0.0023 0.01803 0.01321 -0.1829 0.7612 0.0449
-6.500 0.0310 0.01744 0.01253 -0.1835 0.7557 0.0453
-6.250 0.0597 0.01654 0.01146 -0.1842 0.7499 0.0456
-6.000 0.0885 0.01573 0.01049 -0.1848 0.7443 0.0459
-5.750 0.1180 0.01499 0.00963 -0.1855 0.7399 0.0462
-5.500 0.1473 0.01437 0.00890 -0.1859 0.7346 0.0466
-5.250 0.1764 0.01388 0.00828 -0.1863 0.7292 0.0469
-5.000 0.2057 0.01347 0.00776 -0.1867 0.7239 0.0472
-4.750 0.2354 0.01311 0.00735 -0.1870 0.7195 0.0475
-4.500 0.2649 0.01288 0.00704 -0.1873 0.7143 0.0477
-4.250 0.2940 0.01204 0.00610 -0.1878 0.7089 0.0483
-4.000 0.3232 0.01164 0.00567 -0.1881 0.7038 0.0487
-3.750 0.3529 0.01137 0.00541 -0.1884 0.6992 0.0492
-3.500 0.3823 0.01118 0.00520 -0.1887 0.6939 0.0497
-3.250 0.4113 0.01104 0.00501 -0.1888 0.6882 0.0503
-3.000 0.4408 0.01085 0.00480 -0.1890 0.6831 0.0509
-2.750 0.4704 0.01063 0.00456 -0.1893 0.6780 0.0514
-2.500 0.4997 0.01046 0.00435 -0.1895 0.6723 0.0519
-2.250 0.5286 0.01034 0.00418 -0.1896 0.6662 0.0523
-2.000 0.5584 0.01019 0.00402 -0.1898 0.6612 0.0528
-1.750 0.5877 0.01010 0.00391 -0.1899 0.6553 0.0531
-1.500 0.6170 0.00976 0.00353 -0.1903 0.6493 0.0541
-1.250 0.6465 0.00963 0.00340 -0.1905 0.6437 0.0549
-1.000 0.6758 0.00953 0.00330 -0.1907 0.6375 0.0558
-0.750 0.7047 0.00948 0.00322 -0.1907 0.6309 0.0567
-0.500 0.7337 0.00944 0.00316 -0.1908 0.6251 0.0577
-0.250 0.7629 0.00939 0.00310 -0.1909 0.6186 0.0586
0.000 0.7916 0.00933 0.00300 -0.1910 0.6116 0.0595
0.250 0.8208 0.00924 0.00291 -0.1911 0.6055 0.0610
0.500 0.8497 0.00921 0.00287 -0.1912 0.5989 0.0625
0.750 0.8779 0.00923 0.00286 -0.1911 0.5917 0.0641
1.000 0.9067 0.00923 0.00285 -0.1912 0.5851 0.0655
1.250 0.9352 0.00920 0.00281 -0.1912 0.5769 0.0686
1.500 0.9631 0.00924 0.00283 -0.1911 0.5683 0.0719
1.750 0.9914 0.00925 0.00283 -0.1910 0.5593 0.0778
2.000 1.0192 0.00926 0.00287 -0.1909 0.5510 0.0983
2.250 1.0488 0.00888 0.00297 -0.1915 0.5439 0.2999
2.500 1.0763 0.00893 0.00308 -0.1913 0.5368 0.3362
2.750 1.1043 0.00899 0.00317 -0.1913 0.5309 0.3615
3.000 1.1322 0.00904 0.00327 -0.1912 0.5245 0.3852
3.250 1.1591 0.00916 0.00339 -0.1909 0.5173 0.4054
3.500 1.1869 0.00923 0.00350 -0.1908 0.5114 0.4248
3.750 1.2145 0.00931 0.00361 -0.1906 0.5052 0.4445
4.000 1.2409 0.00944 0.00375 -0.1902 0.4982 0.4636
4.250 1.2684 0.00951 0.00386 -0.1901 0.4911 0.4830
4.500 1.2946 0.00965 0.00400 -0.1896 0.4820 0.5034
4.750 1.3213 0.00973 0.00415 -0.1894 0.4747 0.5324
5.000 1.3478 0.00980 0.00431 -0.1890 0.4665 0.5764
5.250 1.3736 0.00978 0.00454 -0.1887 0.4584 0.7115
5.500 1.3941 0.00946 0.00466 -0.1869 0.4505 1.0000
5.750 1.4189 0.00969 0.00483 -0.1863 0.4411 1.0000
6.000 1.4445 0.00986 0.00498 -0.1857 0.4315 1.0000
6.250 1.4688 0.01010 0.00517 -0.1850 0.4216 1.0000
6.500 1.4927 0.01035 0.00536 -0.1841 0.4099 1.0000
6.750 1.5165 0.01059 0.00557 -0.1833 0.3986 1.0000
7.000 1.5388 0.01090 0.00581 -0.1822 0.3853 1.0000
7.250 1.5597 0.01126 0.00608 -0.1808 0.3689 1.0000
7.500 1.5797 0.01165 0.00639 -0.1792 0.3517 1.0000
7.750 1.5986 0.01207 0.00672 -0.1775 0.3342 1.0000
8.000 1.6156 0.01254 0.00710 -0.1754 0.3152 1.0000
8.250 1.6292 0.01310 0.00754 -0.1726 0.2943 1.0000
8.500 1.6421 0.01370 0.00804 -0.1698 0.2746 1.0000
8.750 1.6555 0.01432 0.00857 -0.1671 0.2573 1.0000
9.000 1.6688 0.01495 0.00911 -0.1644 0.2413 1.0000
9.250 1.6823 0.01558 0.00967 -0.1619 0.2278 1.0000
9.500 1.6961 0.01621 0.01026 -0.1594 0.2163 1.0000
9.750 1.7087 0.01690 0.01089 -0.1568 0.2047 1.0000
10.000 1.7228 0.01754 0.01149 -0.1545 0.1939 1.0000
10.250 1.7344 0.01831 0.01222 -0.1519 0.1821 1.0000
10.500 1.7444 0.01920 0.01304 -0.1491 0.1684 1.0000
10.750 1.7504 0.02033 0.01407 -0.1458 0.1504 1.0000
11.000 1.7504 0.02188 0.01548 -0.1419 0.1266 1.0000
11.250 1.7426 0.02402 0.01743 -0.1371 0.0986 1.0000
11.750 1.7421 0.02776 0.02105 -0.1306 0.0728 1.0000
12.000 1.7487 0.02929 0.02259 -0.1285 0.0681 1.0000
12.250 1.7543 0.03097 0.02428 -0.1264 0.0643 1.0000
12.500 1.7627 0.03249 0.02583 -0.1247 0.0618 1.0000
12.750 1.7684 0.03429 0.02765 -0.1230 0.0593 1.0000
13.000 1.7749 0.03605 0.02945 -0.1213 0.0572 1.0000
13.250 1.7832 0.03769 0.03114 -0.1199 0.0556 1.0000
13.500 1.7890 0.03960 0.03308 -0.1184 0.0540 1.0000
13.750 1.7926 0.04174 0.03526 -0.1169 0.0523 1.0000
14.000 1.7978 0.04377 0.03733 -0.1155 0.0509 1.0000
14.250 1.8045 0.04565 0.03928 -0.1143 0.0497 1.0000
14.500 1.8089 0.04780 0.04148 -0.1131 0.0484 1.0000
14.750 1.8116 0.05015 0.04386 -0.1118 0.0471 1.0000
15.000 1.8107 0.05295 0.04670 -0.1105 0.0457 1.0000
15.250 1.8163 0.05508 0.04891 -0.1095 0.0449 1.0000
15.500 1.8208 0.05733 0.05121 -0.1086 0.0439 1.0000
15.750 1.8225 0.05995 0.05389 -0.1076 0.0429 1.0000
16.000 1.8231 0.06273 0.05672 -0.1068 0.0418 1.0000
16.250 1.8204 0.06595 0.05998 -0.1059 0.0407 1.0000
16.500 1.8223 0.06867 0.06278 -0.1052 0.0399 1.0000
16.750 1.8250 0.07130 0.06547 -0.1046 0.0391 1.0000
17.000 1.8253 0.07424 0.06847 -0.1040 0.0382 1.0000
17.250 1.8238 0.07746 0.07175 -0.1035 0.0374 1.0000
17.500 1.8209 0.08086 0.07521 -0.1031 0.0366 1.0000
17.750 1.8140 0.08486 0.07927 -0.1028 0.0358 1.0000
18.000 1.8143 0.08792 0.08241 -0.1026 0.0352 1.0000
18.250 1.8142 0.09101 0.08558 -0.1024 0.0346 1.0000
18.500 1.8115 0.09451 0.08915 -0.1023 0.0339 1.0000
18.750 1.8088 0.09802 0.09272 -0.1023 0.0332 1.0000
19.000 1.8043 0.10181 0.09656 -0.1025 0.0326 1.0000
19.250 1.7969 0.10606 0.10088 -0.1028 0.0320 1.0000
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Polar data table (+)
Polar graphs
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