HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il) Reynolds number: 100,000 Max Cl/Cd: 61.74 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3510-il-100000.txt Download as CSV file: xf-hq3510-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/10 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3742 0.09989 0.09549 -0.0387 1.0000 0.0776
-8.000 -0.3962 0.09911 0.09484 -0.0366 1.0000 0.0778
-7.750 -0.4163 0.09784 0.09368 -0.0357 1.0000 0.0779
-7.500 -0.4332 0.09555 0.09146 -0.0378 1.0000 0.0781
-7.250 -0.4051 0.09045 0.08636 -0.0279 1.0000 0.0816
-7.000 -0.4149 0.08872 0.08471 -0.0255 1.0000 0.0829
-6.750 -0.4243 0.08665 0.08271 -0.0243 1.0000 0.0848
-6.500 -0.4335 0.08426 0.08038 -0.0243 1.0000 0.0866
-6.250 -0.4418 0.08114 0.07730 -0.0270 1.0000 0.0892
-6.000 -0.4505 0.07730 0.07310 -0.0402 1.0000 0.0921
-5.750 -0.4469 0.07267 0.06874 -0.0354 1.0000 0.0938
-5.500 -0.4428 0.07033 0.06647 -0.0322 1.0000 0.0966
-5.250 -0.4358 0.06706 0.06315 -0.0338 1.0000 0.1020
-5.000 -0.4244 0.06223 0.05810 -0.0391 1.0000 0.1086
-4.750 -0.4146 0.05967 0.05554 -0.0380 1.0000 0.1132
-4.500 -0.3903 0.05534 0.05100 -0.0429 0.9981 0.1246
-4.250 -0.3558 0.05143 0.04692 -0.0481 0.9935 0.1403
-4.000 -0.3216 0.04779 0.04303 -0.0533 0.9883 0.1657
-3.250 -0.1677 0.03207 0.02425 -0.0664 0.9777 0.0648
-3.000 -0.1293 0.02936 0.02115 -0.0684 0.9735 0.0632
-2.750 -0.0869 0.02753 0.01879 -0.0706 0.9699 0.0642
-2.500 -0.0556 0.02555 0.01677 -0.0715 0.9645 0.0700
-2.250 -0.0194 0.02441 0.01557 -0.0730 0.9594 0.0865
-2.000 0.0209 0.02330 0.01458 -0.0755 0.9554 0.1231
-1.750 0.0484 0.02250 0.01396 -0.0758 0.9481 0.1565
-1.500 0.0800 0.02035 0.01394 -0.0766 0.9440 0.6468
-1.250 0.0942 0.02046 0.01431 -0.0722 0.9360 0.7886
-1.000 0.1172 0.02037 0.01429 -0.0698 0.9294 0.8692
-0.750 0.1574 0.02019 0.01406 -0.0722 0.9215 1.0000
-0.500 0.2028 0.02049 0.01406 -0.0763 0.9154 1.0000
-0.250 0.2345 0.02078 0.01413 -0.0779 0.9064 1.0000
0.000 0.2806 0.02104 0.01418 -0.0818 0.9008 1.0000
0.250 0.3087 0.02134 0.01432 -0.0825 0.8910 1.0000
0.500 0.3527 0.02155 0.01438 -0.0858 0.8850 1.0000
0.750 0.3853 0.02174 0.01446 -0.0870 0.8751 1.0000
1.000 0.4210 0.02181 0.01443 -0.0884 0.8645 1.0000
1.250 0.4682 0.02152 0.01406 -0.0914 0.8547 1.0000
1.500 0.5210 0.02095 0.01344 -0.0950 0.8459 1.0000
1.750 0.5550 0.02082 0.01328 -0.0958 0.8347 1.0000
2.000 0.5929 0.02061 0.01304 -0.0971 0.8262 1.0000
2.250 0.6336 0.02022 0.01266 -0.0987 0.8185 1.0000
2.500 0.6639 0.02012 0.01259 -0.0987 0.8075 1.0000
2.750 0.6990 0.01979 0.01228 -0.0993 0.7979 1.0000
3.000 0.7389 0.01922 0.01173 -0.1004 0.7897 1.0000
3.250 0.7688 0.01897 0.01155 -0.1000 0.7773 1.0000
3.500 0.7998 0.01863 0.01126 -0.0997 0.7645 1.0000
3.750 0.8312 0.01824 0.01092 -0.0994 0.7511 1.0000
4.000 0.8627 0.01782 0.01054 -0.0990 0.7365 1.0000
4.250 0.8946 0.01735 0.01016 -0.0986 0.7203 1.0000
4.500 0.9211 0.01712 0.00997 -0.0975 0.6996 1.0000
4.750 0.9515 0.01672 0.00958 -0.0968 0.6776 1.0000
5.000 0.9774 0.01654 0.00939 -0.0955 0.6493 1.0000
5.250 1.0003 0.01651 0.00939 -0.0939 0.6133 1.0000
5.500 1.0234 0.01660 0.00936 -0.0922 0.5716 1.0000
5.750 1.0452 0.01693 0.00948 -0.0905 0.5267 1.0000
6.000 1.0659 0.01752 0.00983 -0.0889 0.4846 1.0000
6.250 1.0867 0.01826 0.01036 -0.0876 0.4494 1.0000
6.500 1.1079 0.01904 0.01104 -0.0864 0.4201 1.0000
6.750 1.1296 0.01985 0.01173 -0.0854 0.3953 1.0000
7.000 1.1508 0.02064 0.01248 -0.0843 0.3723 1.0000
7.250 1.1720 0.02145 0.01328 -0.0833 0.3513 1.0000
7.500 1.1926 0.02227 0.01409 -0.0822 0.3311 1.0000
7.750 1.2134 0.02315 0.01499 -0.0812 0.3120 1.0000
8.000 1.2325 0.02403 0.01596 -0.0798 0.2920 1.0000
8.250 1.2518 0.02500 0.01687 -0.0786 0.2721 1.0000
8.500 1.2667 0.02588 0.01790 -0.0767 0.2508 1.0000
8.750 1.2776 0.02660 0.01862 -0.0743 0.2281 1.0000
9.000 1.2826 0.02709 0.01924 -0.0711 0.2042 1.0000
9.250 1.2855 0.02760 0.01987 -0.0676 0.1782 1.0000
9.500 1.2851 0.02834 0.02057 -0.0639 0.1483 1.0000
9.750 1.2834 0.02996 0.02197 -0.0604 0.1089 1.0000
10.000 1.2709 0.03316 0.02479 -0.0559 0.0667 1.0000
10.250 1.2631 0.03611 0.02764 -0.0522 0.0513 1.0000
10.500 1.2595 0.03889 0.03052 -0.0493 0.0450 1.0000
10.750 1.2614 0.04134 0.03305 -0.0470 0.0405 1.0000
11.000 1.2658 0.04449 0.03613 -0.0450 0.0372 1.0000
11.250 1.2762 0.04678 0.03869 -0.0434 0.0346 1.0000
11.500 1.2841 0.04924 0.04134 -0.0419 0.0320 1.0000
11.750 1.2906 0.05185 0.04406 -0.0407 0.0300 1.0000
12.000 1.3020 0.05517 0.04749 -0.0397 0.0286 1.0000
12.250 1.3136 0.05976 0.05235 -0.0387 0.0279 1.0000
12.500 1.3132 0.06429 0.05721 -0.0375 0.0277 1.0000
12.750 1.3061 0.06866 0.06185 -0.0364 0.0276 1.0000
13.000 1.2955 0.07298 0.06651 -0.0356 0.0277 1.0000
13.250 1.2830 0.07736 0.07118 -0.0353 0.0277 1.0000
13.500 1.2683 0.08206 0.07614 -0.0356 0.0278 1.0000
13.750 1.2526 0.08696 0.08130 -0.0366 0.0279 1.0000
14.000 1.2352 0.09235 0.08694 -0.0383 0.0281 1.0000
14.250 1.2164 0.09824 0.09308 -0.0410 0.0283 1.0000
14.500 1.1947 0.10512 0.10022 -0.0449 0.0286 1.0000
14.750 1.1690 0.11368 0.10907 -0.0505 0.0291 1.0000
15.000 1.1354 0.12549 0.12115 -0.0590 0.0299 1.0000
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Polar data table (+)
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