USA 5 AIRFOIL (usa5-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 5 AIRFOIL (usa5-il) Reynolds number: 100,000 Max Cl/Cd: 56.29 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa5-il-100000-n5.txt Download as CSV file: xf-usa5-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3214 0.09379 0.08935 -0.0233 1.0000 0.0356
-7.000 -0.3276 0.09202 0.08767 -0.0219 1.0000 0.0359
-6.750 -0.3317 0.08999 0.08572 -0.0212 1.0000 0.0366
-6.500 -0.3343 0.08800 0.08380 -0.0212 1.0000 0.0374
-6.250 -0.3357 0.08620 0.08207 -0.0224 1.0000 0.0383
-6.000 -0.3338 0.08436 0.08025 -0.0246 1.0000 0.0389
-5.750 -0.3289 0.08195 0.07785 -0.0263 1.0000 0.0391
-5.250 -0.2880 0.07426 0.07005 -0.0347 0.9940 0.0393
-4.750 -0.2492 0.06348 0.05923 -0.0383 0.9839 0.0271
-4.500 -0.2167 0.05872 0.05432 -0.0440 0.9782 0.0248
-4.250 -0.1843 0.05403 0.04949 -0.0492 0.9711 0.0235
-4.000 -0.1475 0.04956 0.04482 -0.0545 0.9655 0.0244
-3.750 -0.1123 0.04521 0.04024 -0.0587 0.9574 0.0252
-3.500 -0.0753 0.04067 0.03541 -0.0625 0.9495 0.0250
-3.250 -0.0361 0.03592 0.03027 -0.0659 0.9418 0.0248
-3.000 -0.0023 0.03140 0.02529 -0.0675 0.9322 0.0250
-2.750 0.0361 0.02611 0.01923 -0.0691 0.9255 0.0268
-2.500 0.0681 0.02230 0.01449 -0.0691 0.9160 0.0300
-2.250 0.1008 0.02050 0.01236 -0.0696 0.9063 0.0340
-2.000 0.1377 0.01913 0.01068 -0.0709 0.8990 0.0445
-1.750 0.1666 0.01830 0.00967 -0.0706 0.8883 0.0573
-1.500 0.1974 0.01782 0.00898 -0.0708 0.8784 0.0742
-1.250 0.2305 0.01736 0.00823 -0.0713 0.8693 0.0927
-1.000 0.2615 0.01673 0.00746 -0.0716 0.8586 0.1059
-0.750 0.2911 0.01627 0.00693 -0.0717 0.8464 0.1212
-0.500 0.3211 0.01586 0.00647 -0.0719 0.8334 0.1369
-0.250 0.3516 0.01547 0.00602 -0.0721 0.8196 0.1504
0.000 0.3837 0.01513 0.00558 -0.0727 0.8049 0.1630
0.250 0.4165 0.01481 0.00519 -0.0733 0.7894 0.1728
0.500 0.4472 0.01457 0.00488 -0.0736 0.7723 0.1876
0.750 0.4764 0.01436 0.00462 -0.0736 0.7526 0.2075
1.000 0.5064 0.01405 0.00440 -0.0738 0.7317 0.2557
1.500 0.6184 0.01264 0.00403 -0.0857 0.6734 1.0000
1.750 0.6433 0.01283 0.00398 -0.0848 0.6446 1.0000
2.000 0.6676 0.01305 0.00400 -0.0838 0.6164 1.0000
2.250 0.6913 0.01330 0.00408 -0.0828 0.5881 1.0000
2.500 0.7148 0.01356 0.00419 -0.0818 0.5613 1.0000
2.750 0.7382 0.01384 0.00434 -0.0808 0.5368 1.0000
3.250 0.7848 0.01444 0.00473 -0.0789 0.4942 1.0000
3.500 0.8081 0.01477 0.00497 -0.0780 0.4765 1.0000
3.750 0.8314 0.01510 0.00524 -0.0771 0.4613 1.0000
4.000 0.8549 0.01544 0.00558 -0.0762 0.4480 1.0000
4.250 0.8785 0.01578 0.00592 -0.0754 0.4365 1.0000
4.500 0.9020 0.01615 0.00629 -0.0746 0.4260 1.0000
4.750 0.9255 0.01651 0.00670 -0.0738 0.4155 1.0000
5.000 0.9491 0.01686 0.00719 -0.0730 0.4053 1.0000
5.250 0.9690 0.01727 0.00756 -0.0715 0.3808 1.0000
5.500 0.9886 0.01768 0.00794 -0.0700 0.3551 1.0000
5.750 1.0076 0.01808 0.00833 -0.0685 0.3220 1.0000
6.000 1.0242 0.01866 0.00868 -0.0666 0.2554 1.0000
6.250 1.0363 0.01995 0.00940 -0.0643 0.1698 1.0000
6.500 1.0438 0.02210 0.01077 -0.0616 0.0426 1.0000
6.750 1.0555 0.02369 0.01223 -0.0590 0.0227 1.0000
7.000 1.0713 0.02477 0.01353 -0.0569 0.0202 1.0000
7.250 1.0856 0.02598 0.01498 -0.0547 0.0188 1.0000
7.500 1.0997 0.02710 0.01637 -0.0524 0.0176 1.0000
7.750 1.1119 0.02833 0.01784 -0.0500 0.0164 1.0000
8.000 1.1210 0.02970 0.01945 -0.0473 0.0156 1.0000
8.250 1.1272 0.03119 0.02124 -0.0441 0.0151 1.0000
8.500 1.1309 0.03270 0.02292 -0.0407 0.0148 1.0000
8.750 1.1312 0.03432 0.02470 -0.0369 0.0145 1.0000
9.000 1.1334 0.03595 0.02645 -0.0337 0.0144 1.0000
9.250 1.1365 0.03779 0.02839 -0.0307 0.0141 1.0000
9.500 1.1424 0.03975 0.03043 -0.0282 0.0137 1.0000
9.750 1.1505 0.04187 0.03262 -0.0262 0.0129 1.0000
10.000 1.1630 0.04424 0.03505 -0.0246 0.0123 1.0000
10.250 1.1808 0.04726 0.03816 -0.0237 0.0116 1.0000
10.500 1.1979 0.05039 0.04149 -0.0226 0.0115 1.0000
10.750 1.2065 0.05302 0.04438 -0.0208 0.0116 1.0000
11.000 1.2103 0.05581 0.04744 -0.0188 0.0116 1.0000
11.250 1.2099 0.05861 0.05051 -0.0168 0.0117 1.0000
11.500 1.2059 0.06151 0.05369 -0.0149 0.0118 1.0000
11.750 1.1993 0.06459 0.05705 -0.0134 0.0119 1.0000
12.000 1.1913 0.06780 0.06053 -0.0123 0.0121 1.0000
12.250 1.1808 0.07161 0.06461 -0.0118 0.0122 1.0000
12.500 1.1687 0.07578 0.06903 -0.0119 0.0123 1.0000
12.750 1.1557 0.08022 0.07373 -0.0128 0.0125 1.0000
13.000 1.1397 0.08531 0.07907 -0.0145 0.0126 1.0000
13.250 1.1229 0.09098 0.08497 -0.0169 0.0127 1.0000
13.500 1.1067 0.09694 0.09115 -0.0200 0.0129 1.0000
13.750 1.0903 0.10342 0.09782 -0.0237 0.0130 1.0000
14.000 1.0731 0.11061 0.10519 -0.0280 0.0131 1.0000
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Polar data table (+)
Polar graphs
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