USA 5 AIRFOIL (usa5-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 5 AIRFOIL (usa5-il) Reynolds number: 50,000 Max Cl/Cd: 40.72 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa5-il-50000-n5.txt Download as CSV file: xf-usa5-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 5 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3244 0.10110 0.09477 -0.0244 1.0000 0.0756
-7.250 -0.3323 0.09995 0.09375 -0.0242 1.0000 0.0774
-7.000 -0.3362 0.09868 0.09260 -0.0256 1.0000 0.0782
-6.750 -0.3377 0.09720 0.09121 -0.0274 1.0000 0.0787
-6.500 -0.3366 0.09550 0.08956 -0.0293 1.0000 0.0789
-6.250 -0.3318 0.09003 0.08420 -0.0251 1.0000 0.0806
-6.000 -0.3287 0.08689 0.08111 -0.0236 1.0000 0.0823
-5.750 -0.3260 0.08419 0.07847 -0.0232 1.0000 0.0840
-5.500 -0.3225 0.08160 0.07592 -0.0232 1.0000 0.0853
-5.250 -0.3178 0.07894 0.07329 -0.0236 1.0000 0.0866
-5.000 -0.3114 0.07626 0.07063 -0.0243 1.0000 0.0876
-4.750 -0.3031 0.07347 0.06780 -0.0252 1.0000 0.0884
-4.500 -0.2938 0.07046 0.06477 -0.0258 1.0000 0.0876
-4.250 -0.2631 0.06489 0.05890 -0.0329 1.0000 0.0516
-4.000 -0.2584 0.06170 0.05571 -0.0305 1.0000 0.0486
-3.750 -0.2447 0.05847 0.05240 -0.0309 1.0000 0.0468
-3.500 -0.2278 0.05530 0.04911 -0.0319 1.0000 0.0461
-3.250 -0.2089 0.05224 0.04589 -0.0329 1.0000 0.0466
-3.000 -0.1737 0.04842 0.04176 -0.0368 0.9952 0.0476
-2.750 -0.1338 0.04428 0.03724 -0.0409 0.9884 0.0476
-2.500 -0.0953 0.04051 0.03303 -0.0442 0.9814 0.0476
-2.250 -0.0533 0.03669 0.02854 -0.0473 0.9735 0.0500
-2.000 -0.0130 0.03433 0.02581 -0.0503 0.9628 0.0575
-1.750 0.0330 0.03105 0.02174 -0.0532 0.9526 0.0626
-1.500 0.0779 0.02907 0.01903 -0.0558 0.9406 0.0790
-1.250 0.1197 0.02739 0.01696 -0.0581 0.9280 0.0953
-1.000 0.1577 0.02618 0.01536 -0.0597 0.9159 0.1154
-0.750 0.2025 0.02505 0.01376 -0.0625 0.9053 0.1378
-0.500 0.2464 0.02425 0.01269 -0.0653 0.8949 0.1649
-0.250 0.2913 0.02344 0.01170 -0.0682 0.8851 0.1902
0.000 0.3287 0.02278 0.01095 -0.0698 0.8725 0.2098
0.500 0.4000 0.02153 0.00979 -0.0722 0.8455 0.2683
1.000 0.5006 0.01940 0.00880 -0.0804 0.8176 1.0000
1.250 0.5315 0.01935 0.00853 -0.0804 0.7994 1.0000
1.500 0.5609 0.01934 0.00835 -0.0802 0.7797 1.0000
1.750 0.5922 0.01929 0.00815 -0.0802 0.7604 1.0000
2.000 0.6205 0.01932 0.00806 -0.0797 0.7384 1.0000
2.250 0.6501 0.01934 0.00795 -0.0794 0.7171 1.0000
2.500 0.6773 0.01947 0.00799 -0.0787 0.6939 1.0000
2.750 0.7058 0.01959 0.00798 -0.0783 0.6720 1.0000
3.000 0.7318 0.01984 0.00815 -0.0776 0.6493 1.0000
3.250 0.7586 0.02010 0.00835 -0.0770 0.6286 1.0000
3.500 0.7833 0.02045 0.00865 -0.0761 0.6068 1.0000
3.750 0.8086 0.02079 0.00893 -0.0753 0.5869 1.0000
4.000 0.8322 0.02121 0.00934 -0.0744 0.5667 1.0000
4.250 0.8559 0.02162 0.00980 -0.0735 0.5479 1.0000
4.500 0.8797 0.02203 0.01022 -0.0725 0.5305 1.0000
4.750 0.9033 0.02246 0.01068 -0.0716 0.5141 1.0000
5.000 0.9264 0.02293 0.01124 -0.0706 0.4979 1.0000
5.250 0.9495 0.02342 0.01189 -0.0697 0.4826 1.0000
5.500 0.9727 0.02393 0.01253 -0.0687 0.4680 1.0000
5.750 0.9964 0.02447 0.01323 -0.0679 0.4552 1.0000
6.000 1.0169 0.02499 0.01391 -0.0664 0.4368 1.0000
6.250 1.0304 0.02539 0.01433 -0.0636 0.4038 1.0000
6.500 1.0445 0.02590 0.01487 -0.0611 0.3742 1.0000
6.750 1.0544 0.02645 0.01540 -0.0580 0.3349 1.0000
7.000 1.0701 0.02706 0.01619 -0.0559 0.3078 1.0000
7.250 1.0812 0.02778 0.01693 -0.0532 0.2524 1.0000
7.500 1.0889 0.02905 0.01776 -0.0504 0.1820 1.0000
8.000 1.0919 0.03429 0.02184 -0.0447 0.0397 1.0000
8.250 1.0964 0.03644 0.02403 -0.0420 0.0340 1.0000
8.500 1.1009 0.03828 0.02609 -0.0392 0.0310 1.0000
8.750 1.1015 0.04034 0.02848 -0.0362 0.0292 1.0000
9.000 1.1009 0.04249 0.03085 -0.0335 0.0283 1.0000
9.250 1.0971 0.04500 0.03355 -0.0311 0.0276 1.0000
9.500 1.0910 0.04786 0.03660 -0.0290 0.0271 1.0000
9.750 1.0862 0.05080 0.03970 -0.0276 0.0268 1.0000
10.000 1.0824 0.05383 0.04295 -0.0265 0.0264 1.0000
10.250 1.0795 0.05694 0.04627 -0.0258 0.0260 1.0000
10.500 1.0767 0.06024 0.04977 -0.0252 0.0254 1.0000
10.750 1.0759 0.06339 0.05312 -0.0247 0.0250 1.0000
11.000 1.0763 0.06651 0.05644 -0.0242 0.0241 1.0000
11.250 1.0785 0.06948 0.05960 -0.0234 0.0233 1.0000
11.500 1.0830 0.07227 0.06259 -0.0224 0.0226 1.0000
11.750 1.0914 0.07479 0.06533 -0.0210 0.0224 1.0000
12.000 1.0999 0.07752 0.06833 -0.0198 0.0223 1.0000
12.250 1.1049 0.08091 0.07203 -0.0190 0.0222 1.0000
12.500 1.1045 0.08501 0.07642 -0.0192 0.0222 1.0000
12.750 1.0998 0.08968 0.08135 -0.0202 0.0223 1.0000
13.000 1.0918 0.09493 0.08686 -0.0219 0.0224 1.0000
13.250 1.0817 0.10066 0.09282 -0.0243 0.0225 1.0000
13.500 1.0704 0.10681 0.09919 -0.0272 0.0226 1.0000
13.750 1.0587 0.11330 0.10588 -0.0306 0.0229 1.0000
14.000 1.0457 0.12047 0.11323 -0.0345 0.0230 1.0000
14.250 1.0330 0.12796 0.12088 -0.0388 0.0232 1.0000
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