HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/8 AIRFOIL (hq358-il) Reynolds number: 100,000 Max Cl/Cd: 63.5 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq358-il-100000-n5.txt Download as CSV file: xf-hq358-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/8 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3501 0.09173 0.08718 -0.0317 1.0000 0.0343
-7.250 -0.3580 0.09002 0.08557 -0.0297 1.0000 0.0360
-7.000 -0.3700 0.08850 0.08414 -0.0274 1.0000 0.0357
-6.750 -0.3791 0.08665 0.08238 -0.0260 1.0000 0.0361
-6.500 -0.3860 0.08447 0.08028 -0.0254 1.0000 0.0369
-6.250 -0.3807 0.08114 0.07699 -0.0292 0.9978 0.0397
-6.000 -0.3432 0.07489 0.07061 -0.0461 0.9897 0.0422
-5.750 -0.3053 0.06969 0.06505 -0.0593 0.9824 0.0430
-5.500 -0.2906 0.06333 0.05880 -0.0613 0.9781 0.0442
-5.250 -0.2667 0.05874 0.05418 -0.0647 0.9744 0.0454
-5.000 -0.2416 0.05433 0.04962 -0.0689 0.9682 0.0461
-4.750 -0.2029 0.04807 0.04299 -0.0745 0.9638 0.0278
-4.500 -0.1697 0.04310 0.03774 -0.0793 0.9600 0.0247
-4.250 -0.1376 0.03858 0.03282 -0.0825 0.9542 0.0225
-4.000 -0.0978 0.03374 0.02734 -0.0860 0.9506 0.0203
-3.750 -0.0581 0.03020 0.02318 -0.0887 0.9481 0.0194
-3.500 -0.0279 0.02771 0.02022 -0.0894 0.9426 0.0191
-3.250 0.0064 0.02515 0.01719 -0.0910 0.9388 0.0194
-3.000 0.0418 0.02356 0.01529 -0.0930 0.9359 0.0226
-2.750 0.0739 0.02206 0.01348 -0.0936 0.9315 0.0254
-2.500 0.1054 0.02054 0.01170 -0.0940 0.9269 0.0264
-2.250 0.1402 0.01921 0.01019 -0.0950 0.9236 0.0282
-2.000 0.1766 0.01813 0.00897 -0.0965 0.9211 0.0308
-1.750 0.2030 0.01748 0.00821 -0.0963 0.9140 0.0381
-1.500 0.2377 0.01660 0.00749 -0.0978 0.9102 0.1019
-1.250 0.2627 0.01462 0.00762 -0.0974 0.9069 0.7081
-1.000 0.2802 0.01436 0.00752 -0.0943 0.8991 0.8128
-0.750 0.3179 0.01383 0.00706 -0.0953 0.8955 1.0000
-0.500 0.3479 0.01390 0.00690 -0.0960 0.8882 1.0000
-0.250 0.3828 0.01390 0.00664 -0.0974 0.8827 1.0000
0.000 0.4128 0.01395 0.00652 -0.0979 0.8747 1.0000
0.250 0.4472 0.01391 0.00633 -0.0991 0.8685 1.0000
0.500 0.4760 0.01393 0.00625 -0.0992 0.8590 1.0000
0.750 0.5078 0.01385 0.00606 -0.0997 0.8499 1.0000
1.000 0.5408 0.01370 0.00581 -0.1002 0.8403 1.0000
1.250 0.5696 0.01361 0.00566 -0.1000 0.8274 1.0000
1.500 0.5979 0.01354 0.00553 -0.0997 0.8142 1.0000
1.750 0.6257 0.01352 0.00550 -0.0994 0.8013 1.0000
2.000 0.6531 0.01355 0.00551 -0.0992 0.7892 1.0000
2.250 0.6807 0.01358 0.00553 -0.0989 0.7767 1.0000
2.500 0.7084 0.01361 0.00556 -0.0986 0.7635 1.0000
2.750 0.7360 0.01364 0.00565 -0.0983 0.7490 1.0000
3.000 0.7637 0.01367 0.00569 -0.0980 0.7335 1.0000
3.250 0.7903 0.01374 0.00579 -0.0975 0.7153 1.0000
3.500 0.8169 0.01381 0.00589 -0.0970 0.6952 1.0000
3.750 0.8432 0.01391 0.00600 -0.0964 0.6722 1.0000
4.000 0.8691 0.01404 0.00621 -0.0957 0.6456 1.0000
4.250 0.8944 0.01422 0.00637 -0.0949 0.6134 1.0000
4.500 0.9189 0.01447 0.00657 -0.0939 0.5745 1.0000
4.750 0.9422 0.01484 0.00680 -0.0928 0.5289 1.0000
5.000 0.9640 0.01535 0.00714 -0.0915 0.4796 1.0000
5.250 0.9849 0.01598 0.00759 -0.0902 0.4336 1.0000
5.500 1.0057 0.01666 0.00823 -0.0890 0.3936 1.0000
5.750 1.0268 0.01733 0.00885 -0.0879 0.3594 1.0000
6.000 1.0477 0.01803 0.00951 -0.0868 0.3291 1.0000
6.250 1.0684 0.01875 0.01022 -0.0857 0.3016 1.0000
6.500 1.0870 0.01959 0.01095 -0.0844 0.2651 1.0000
6.750 1.1055 0.02044 0.01173 -0.0831 0.2262 1.0000
7.000 1.1218 0.02149 0.01249 -0.0817 0.1580 1.0000
7.250 1.1299 0.02380 0.01396 -0.0796 0.0527 1.0000
7.500 1.1416 0.02594 0.01589 -0.0773 0.0216 1.0000
7.750 1.1547 0.02777 0.01788 -0.0751 0.0166 1.0000
8.000 1.1682 0.02935 0.01971 -0.0730 0.0140 1.0000
8.250 1.1813 0.03083 0.02141 -0.0710 0.0118 1.0000
8.500 1.1921 0.03245 0.02325 -0.0689 0.0105 1.0000
8.750 1.1998 0.03429 0.02531 -0.0663 0.0100 1.0000
9.000 1.2048 0.03630 0.02751 -0.0635 0.0095 1.0000
9.250 1.2097 0.03852 0.02993 -0.0608 0.0092 1.0000
9.500 1.2152 0.04102 0.03263 -0.0583 0.0090 1.0000
9.750 1.2214 0.04388 0.03572 -0.0562 0.0088 1.0000
10.000 1.2273 0.04705 0.03916 -0.0541 0.0086 1.0000
10.250 1.2304 0.05044 0.04286 -0.0521 0.0085 1.0000
10.500 1.2296 0.05397 0.04671 -0.0500 0.0085 1.0000
10.750 1.2252 0.05762 0.05068 -0.0481 0.0085 1.0000
11.000 1.2176 0.06141 0.05477 -0.0465 0.0085 1.0000
11.250 1.2078 0.06542 0.05907 -0.0454 0.0085 1.0000
11.500 1.1961 0.06973 0.06366 -0.0450 0.0085 1.0000
11.750 1.1834 0.07433 0.06851 -0.0452 0.0085 1.0000
12.000 1.1693 0.07939 0.07382 -0.0463 0.0085 1.0000
12.250 1.1550 0.08488 0.07954 -0.0483 0.0085 1.0000
12.500 1.1403 0.09088 0.08576 -0.0511 0.0086 1.0000
12.750 1.1256 0.09743 0.09251 -0.0547 0.0086 1.0000
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Polar data table (+)
Polar graphs
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