HQ 2.5/8 AIRFOIL (hq258-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/8 AIRFOIL (hq258-il) Reynolds number: 100,000 Max Cl/Cd: 59.51 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq258-il-100000.txt Download as CSV file: xf-hq258-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/8 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4060 0.09139 0.08665 -0.0291 1.0000 0.0702
-7.750 -0.4101 0.08863 0.08399 -0.0306 1.0000 0.0727
-7.500 -0.4209 0.08620 0.08168 -0.0328 1.0000 0.0741
-7.250 -0.4291 0.08279 0.07833 -0.0403 1.0000 0.0750
-7.000 -0.4369 0.08001 0.07545 -0.0458 1.0000 0.0755
-6.750 -0.4242 0.07514 0.07082 -0.0377 1.0000 0.0781
-6.500 -0.4212 0.07238 0.06810 -0.0365 1.0000 0.0809
-6.250 -0.4215 0.06912 0.06485 -0.0379 1.0000 0.0847
-6.000 -0.4262 0.06650 0.06178 -0.0457 1.0000 0.0891
-5.750 -0.4201 0.06184 0.05745 -0.0413 1.0000 0.0914
-5.500 -0.4143 0.05916 0.05480 -0.0397 1.0000 0.0958
-5.250 -0.4067 0.05532 0.05071 -0.0425 1.0000 0.1044
-5.000 -0.3954 0.05271 0.04782 -0.0439 1.0000 0.1167
-4.750 -0.3852 0.04969 0.04478 -0.0433 1.0000 0.1306
-4.500 -0.3754 0.04680 0.04201 -0.0417 1.0000 0.1462
-4.250 -0.3622 0.04423 0.03934 -0.0417 1.0000 0.1721
-4.000 -0.3482 0.04171 0.03685 -0.0406 1.0000 0.1921
-3.500 -0.2604 0.03025 0.02320 -0.0457 1.0000 0.0724
-3.250 -0.2301 0.02699 0.01929 -0.0453 1.0000 0.0588
-3.000 -0.2019 0.02448 0.01633 -0.0449 1.0000 0.0547
-2.750 -0.1743 0.02250 0.01391 -0.0443 1.0000 0.0534
-2.500 -0.1489 0.02106 0.01220 -0.0435 1.0000 0.0554
-2.250 -0.1247 0.02000 0.01098 -0.0428 1.0000 0.0642
-2.000 -0.1003 0.01892 0.00984 -0.0420 1.0000 0.0755
-1.750 -0.0758 0.01746 0.00867 -0.0417 1.0000 0.1128
-1.500 -0.0556 0.01442 0.00834 -0.0398 1.0000 0.7194
-1.250 -0.0438 0.01370 0.00807 -0.0351 1.0000 1.0000
-1.000 -0.0192 0.01398 0.00797 -0.0355 1.0000 1.0000
-0.750 0.0166 0.01441 0.00801 -0.0381 0.9957 1.0000
-0.500 0.0597 0.01489 0.00819 -0.0419 0.9877 1.0000
-0.250 0.1047 0.01543 0.00848 -0.0461 0.9801 1.0000
0.000 0.1465 0.01584 0.00870 -0.0495 0.9711 1.0000
0.250 0.1867 0.01623 0.00890 -0.0526 0.9618 1.0000
0.500 0.2313 0.01664 0.00919 -0.0564 0.9537 1.0000
0.750 0.2710 0.01694 0.00940 -0.0592 0.9437 1.0000
1.000 0.3089 0.01721 0.00962 -0.0616 0.9333 1.0000
1.250 0.3498 0.01745 0.00981 -0.0644 0.9232 1.0000
1.500 0.3968 0.01749 0.00986 -0.0680 0.9118 1.0000
1.750 0.4507 0.01730 0.00970 -0.0725 0.9011 1.0000
2.000 0.4944 0.01716 0.00964 -0.0752 0.8891 1.0000
2.250 0.5338 0.01702 0.00956 -0.0768 0.8768 1.0000
2.500 0.5723 0.01680 0.00942 -0.0782 0.8641 1.0000
2.750 0.6096 0.01650 0.00921 -0.0790 0.8507 1.0000
3.000 0.6449 0.01615 0.00903 -0.0793 0.8363 1.0000
3.250 0.6786 0.01578 0.00876 -0.0791 0.8213 1.0000
3.500 0.7052 0.01557 0.00866 -0.0778 0.8015 1.0000
3.750 0.7354 0.01517 0.00835 -0.0768 0.7821 1.0000
4.000 0.7616 0.01489 0.00818 -0.0752 0.7577 1.0000
4.250 0.7879 0.01462 0.00806 -0.0736 0.7301 1.0000
4.500 0.8129 0.01443 0.00795 -0.0718 0.6964 1.0000
4.750 0.8369 0.01436 0.00789 -0.0699 0.6533 1.0000
5.000 0.8593 0.01444 0.00790 -0.0679 0.5970 1.0000
5.250 0.8796 0.01483 0.00804 -0.0656 0.5261 1.0000
5.500 0.8980 0.01561 0.00847 -0.0634 0.4501 1.0000
5.750 0.9162 0.01662 0.00915 -0.0615 0.3847 1.0000
6.000 0.9348 0.01769 0.01008 -0.0599 0.3305 1.0000
6.250 0.9521 0.01870 0.01088 -0.0583 0.2765 1.0000
6.500 0.9664 0.01955 0.01133 -0.0568 0.1916 1.0000
6.750 0.9731 0.02252 0.01320 -0.0540 0.0607 1.0000
7.000 0.9860 0.02483 0.01550 -0.0513 0.0432 1.0000
7.250 1.0004 0.02695 0.01764 -0.0492 0.0374 1.0000
7.500 1.0193 0.02948 0.02027 -0.0475 0.0348 1.0000
7.750 1.0434 0.03214 0.02316 -0.0463 0.0330 1.0000
8.000 1.0673 0.03515 0.02646 -0.0452 0.0318 1.0000
8.250 1.0870 0.03788 0.02952 -0.0439 0.0297 1.0000
8.500 1.1017 0.04070 0.03252 -0.0427 0.0269 1.0000
8.750 1.1144 0.04469 0.03699 -0.0411 0.0263 1.0000
9.000 1.1242 0.04813 0.04094 -0.0389 0.0267 1.0000
9.250 1.1277 0.05220 0.04563 -0.0361 0.0279 1.0000
9.500 1.1181 0.05715 0.05125 -0.0328 0.0293 1.0000
9.750 1.1048 0.06185 0.05639 -0.0300 0.0304 1.0000
10.000 1.0878 0.06584 0.06066 -0.0272 0.0312 1.0000
10.250 1.0683 0.06992 0.06497 -0.0253 0.0317 1.0000
10.500 1.0479 0.07437 0.06961 -0.0250 0.0321 1.0000
10.750 1.0269 0.07942 0.07483 -0.0261 0.0324 1.0000
11.000 1.0051 0.08543 0.08088 -0.0290 0.0326 1.0000
11.250 0.9832 0.09258 0.08816 -0.0337 0.0329 1.0000
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Polar data table (+)
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