HQ 3.5/18 AIRFOIL (hq3518-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/18 AIRFOIL (hq3518-il) Reynolds number: 50,000 Max Cl/Cd: 21.39 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3518-il-50000-n5.txt Download as CSV file: xf-hq3518-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/18 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3973 0.11187 0.10474 -0.0540 1.0000 0.0889
-11.500 -0.4192 0.10760 0.10056 -0.0538 1.0000 0.0889
-11.250 -0.4401 0.09912 0.09211 -0.0589 0.9965 0.0886
-11.000 -0.4908 0.08411 0.07699 -0.0706 0.9887 0.0878
-10.750 -0.5483 0.07274 0.06535 -0.0800 0.9781 0.0868
-10.500 -0.5805 0.06685 0.05916 -0.0841 0.9676 0.0868
-10.250 -0.6014 0.06325 0.05530 -0.0845 0.9568 0.0872
-10.000 -0.6112 0.06013 0.05192 -0.0844 0.9473 0.0884
-9.750 -0.6108 0.05679 0.04819 -0.0853 0.9402 0.0902
-9.500 -0.6169 0.05434 0.04538 -0.0836 0.9309 0.0918
-9.250 -0.6096 0.05142 0.04190 -0.0840 0.9251 0.0938
-9.000 -0.6024 0.04970 0.04005 -0.0823 0.9181 0.0953
-8.750 -0.5828 0.04814 0.03844 -0.0823 0.9131 0.0979
-8.500 -0.5586 0.04646 0.03655 -0.0833 0.9093 0.1015
-8.250 -0.5515 0.04519 0.03502 -0.0811 0.9021 0.1042
-8.000 -0.5322 0.04364 0.03304 -0.0809 0.8972 0.1074
-7.750 -0.5024 0.04240 0.03193 -0.0818 0.8942 0.1115
-7.500 -0.4885 0.04160 0.03105 -0.0802 0.8886 0.1153
-7.250 -0.4687 0.04067 0.02989 -0.0793 0.8835 0.1198
-7.000 -0.4406 0.03976 0.02903 -0.0797 0.8799 0.1250
-6.750 -0.4092 0.03896 0.02816 -0.0807 0.8771 0.1318
-6.500 -0.4033 0.03861 0.02773 -0.0774 0.8703 0.1361
-6.250 -0.3831 0.03808 0.02727 -0.0766 0.8658 0.1426
-6.000 -0.3557 0.03747 0.02662 -0.0769 0.8624 0.1516
-5.750 -0.3425 0.03710 0.02626 -0.0751 0.8569 0.1595
-5.500 -0.3300 0.03674 0.02591 -0.0732 0.8514 0.1689
-5.250 -0.3080 0.03620 0.02538 -0.0728 0.8473 0.1836
-5.000 -0.2813 0.03544 0.02470 -0.0733 0.8442 0.2050
-4.750 -0.2813 0.03514 0.02452 -0.0696 0.8367 0.2216
-4.500 -0.2639 0.03439 0.02401 -0.0689 0.8320 0.2560
-4.250 -0.2399 0.03350 0.02347 -0.0692 0.8284 0.3183
-4.000 -0.2344 0.03333 0.02396 -0.0657 0.8215 0.3787
-3.750 -0.2156 0.03363 0.02454 -0.0636 0.8152 0.4753
-3.500 -0.1835 0.03389 0.02470 -0.0636 0.8108 0.5312
-3.250 -0.1760 0.03442 0.02521 -0.0598 0.8015 0.5603
-3.000 -0.1503 0.03494 0.02567 -0.0583 0.7959 0.5923
-2.750 -0.1306 0.03543 0.02605 -0.0563 0.7897 0.6194
-2.500 -0.1176 0.03601 0.02657 -0.0533 0.7823 0.6398
-2.250 -0.0922 0.03648 0.02696 -0.0516 0.7778 0.6611
-2.000 -0.0780 0.03693 0.02733 -0.0491 0.7714 0.6779
-1.750 -0.0621 0.03724 0.02755 -0.0472 0.7646 0.6928
-1.500 -0.0348 0.03739 0.02759 -0.0465 0.7602 0.7060
-1.250 -0.0209 0.03773 0.02787 -0.0442 0.7533 0.7176
-1.000 -0.0042 0.03797 0.02804 -0.0424 0.7463 0.7313
-0.750 0.0241 0.03799 0.02795 -0.0420 0.7420 0.7460
-0.500 0.0327 0.03842 0.02837 -0.0390 0.7340 0.7564
-0.250 0.0524 0.03860 0.02849 -0.0379 0.7278 0.7681
0.000 0.0818 0.03858 0.02837 -0.0379 0.7239 0.7788
0.250 0.0905 0.03904 0.02880 -0.0357 0.7149 0.7872
0.500 0.1158 0.03911 0.02880 -0.0357 0.7089 0.7943
0.750 0.1521 0.03895 0.02851 -0.0374 0.7052 0.8004
1.000 0.1575 0.03962 0.02918 -0.0351 0.6946 0.8064
1.250 0.1865 0.03968 0.02918 -0.0357 0.6897 0.8130
1.500 0.2229 0.03952 0.02894 -0.0371 0.6865 0.8201
1.750 0.2256 0.04032 0.02975 -0.0346 0.6741 0.8279
2.000 0.2641 0.03992 0.02927 -0.0360 0.6696 0.8356
2.250 0.2728 0.04047 0.02983 -0.0340 0.6572 0.8435
2.500 0.3116 0.03991 0.02922 -0.0351 0.6522 0.8517
2.750 0.3222 0.04039 0.02972 -0.0334 0.6395 0.8613
3.000 0.3588 0.03987 0.02918 -0.0342 0.6346 0.8714
3.250 0.3684 0.04067 0.03003 -0.0328 0.6229 0.8838
3.500 0.4033 0.04039 0.02978 -0.0337 0.6178 0.8962
3.750 0.4197 0.04121 0.03067 -0.0335 0.6068 0.9120
4.000 0.4596 0.04103 0.03052 -0.0356 0.6011 0.9293
4.500 0.5218 0.04161 0.03115 -0.0392 0.5839 1.0000
5.000 0.5690 0.04242 0.03191 -0.0400 0.5669 1.0000
5.500 0.6172 0.04316 0.03261 -0.0406 0.5498 1.0000
5.750 0.6299 0.04433 0.03377 -0.0401 0.5376 1.0000
6.000 0.6660 0.04373 0.03315 -0.0407 0.5328 1.0000
6.250 0.6769 0.04506 0.03450 -0.0401 0.5202 1.0000
6.500 0.7145 0.04427 0.03369 -0.0406 0.5158 1.0000
6.750 0.7247 0.04563 0.03506 -0.0398 0.5029 1.0000
7.000 0.7656 0.04443 0.03386 -0.0402 0.4987 1.0000
7.250 0.7765 0.04560 0.03503 -0.0392 0.4852 1.0000
7.750 0.8344 0.04473 0.03415 -0.0385 0.4665 1.0000
8.000 0.8510 0.04540 0.03483 -0.0377 0.4544 1.0000
8.250 0.8917 0.04404 0.03342 -0.0378 0.4473 1.0000
8.500 0.9002 0.04553 0.03495 -0.0368 0.4345 1.0000
8.750 0.9434 0.04410 0.03347 -0.0370 0.4277 1.0000
9.000 0.9441 0.04624 0.03567 -0.0357 0.4142 1.0000
9.250 0.9754 0.04583 0.03524 -0.0354 0.4057 1.0000
9.500 0.9815 0.04754 0.03701 -0.0343 0.3936 1.0000
9.750 0.9845 0.04960 0.03913 -0.0333 0.3817 1.0000
10.000 1.0164 0.04900 0.03849 -0.0329 0.3732 1.0000
10.250 1.0090 0.05201 0.04162 -0.0317 0.3607 1.0000
10.500 1.0202 0.05338 0.04302 -0.0310 0.3508 1.0000
10.750 1.0448 0.05337 0.04299 -0.0304 0.3421 1.0000
11.000 1.0490 0.05546 0.04515 -0.0296 0.3319 1.0000
11.250 1.0864 0.05426 0.04387 -0.0293 0.3245 1.0000
11.500 1.0823 0.05727 0.04699 -0.0284 0.3144 1.0000
11.750 1.1234 0.05586 0.04545 -0.0282 0.3073 1.0000
12.000 1.1096 0.05991 0.04968 -0.0273 0.2975 1.0000
12.250 1.1461 0.05903 0.04871 -0.0270 0.2904 1.0000
12.500 1.1279 0.06369 0.05358 -0.0264 0.2818 1.0000
12.750 1.1458 0.06470 0.05462 -0.0259 0.2749 1.0000
13.000 1.1492 0.06732 0.05732 -0.0256 0.2682 1.0000
13.250 1.1258 0.07302 0.06322 -0.0257 0.2605 1.0000
13.500 1.1625 0.07183 0.06200 -0.0250 0.2555 1.0000
13.750 1.0729 0.08673 0.07724 -0.0277 0.2457 1.0000
14.000 1.0830 0.08879 0.07936 -0.0277 0.2409 1.0000
14.250 1.1295 0.08573 0.07630 -0.0262 0.2382 1.0000
14.500 0.9972 0.11063 0.10144 -0.0349 0.2243 1.0000
14.750 1.0290 0.10887 0.09973 -0.0335 0.2223 1.0000
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