HQ 2.5/10 AIRFOIL (hq2510-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/10 AIRFOIL (hq2510-il) Reynolds number: 100,000 Max Cl/Cd: 57.5 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2510-il-100000.txt Download as CSV file: xf-hq2510-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/10 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4037 0.10205 0.09721 -0.0347 1.0000 0.0869
-9.000 -0.4221 0.09948 0.09478 -0.0400 1.0000 0.0880
-8.750 -0.4404 0.09651 0.09195 -0.0439 1.0000 0.0883
-8.500 -0.3984 0.09140 0.08673 -0.0358 1.0000 0.0932
-8.250 -0.3988 0.08849 0.08389 -0.0362 1.0000 0.0964
-8.000 -0.4112 0.08560 0.08112 -0.0378 1.0000 0.0996
-7.750 -0.4385 0.08274 0.07844 -0.0410 1.0000 0.1011
-7.500 -0.4665 0.07970 0.07540 -0.0454 1.0000 0.1018
-7.250 -0.4548 0.07565 0.07151 -0.0408 1.0000 0.1043
-7.000 -0.4520 0.07359 0.06950 -0.0374 1.0000 0.1075
-6.750 -0.4622 0.07092 0.06686 -0.0369 1.0000 0.1107
-6.250 -0.4831 0.06430 0.06017 -0.0376 1.0000 0.1190
-6.000 -0.4821 0.06200 0.05783 -0.0364 1.0000 0.1269
-5.750 -0.4816 0.05878 0.05459 -0.0358 1.0000 0.1341
-5.500 -0.4786 0.05592 0.05164 -0.0356 1.0000 0.1472
-5.250 -0.4724 0.05324 0.04891 -0.0350 1.0000 0.1613
-5.000 -0.4637 0.05052 0.04610 -0.0344 1.0000 0.1760
-4.750 -0.4209 0.03858 0.03262 -0.0410 1.0000 0.0828
-4.500 -0.3896 0.03279 0.02555 -0.0407 1.0000 0.0602
-4.250 -0.3658 0.02966 0.02196 -0.0404 1.0000 0.0591
-4.000 -0.3410 0.02734 0.01914 -0.0398 1.0000 0.0597
-3.750 -0.3182 0.02540 0.01698 -0.0395 1.0000 0.0659
-3.500 -0.2946 0.02401 0.01532 -0.0387 1.0000 0.0715
-3.250 -0.2708 0.02237 0.01355 -0.0380 1.0000 0.0794
-3.000 -0.2373 0.02127 0.01238 -0.0392 0.9967 0.0998
-2.750 -0.2007 0.02021 0.01146 -0.0413 0.9919 0.1260
-2.500 -0.1649 0.01931 0.01071 -0.0432 0.9864 0.1598
-2.250 -0.1350 0.01693 0.01056 -0.0442 0.9827 0.5754
-2.000 -0.1138 0.01718 0.01111 -0.0415 0.9748 0.7326
-1.750 -0.0856 0.01755 0.01147 -0.0405 0.9681 0.7985
-1.500 -0.0644 0.01759 0.01150 -0.0383 0.9596 0.8477
-1.250 -0.0356 0.01763 0.01152 -0.0376 0.9529 0.9025
-1.000 0.0352 0.01768 0.01145 -0.0456 0.9485 1.0000
-0.750 0.0795 0.01789 0.01141 -0.0501 0.9416 1.0000
-0.500 0.1111 0.01803 0.01138 -0.0522 0.9317 1.0000
-0.250 0.1509 0.01827 0.01144 -0.0554 0.9240 1.0000
0.000 0.1909 0.01847 0.01149 -0.0585 0.9159 1.0000
0.250 0.2249 0.01870 0.01160 -0.0604 0.9067 1.0000
0.500 0.2719 0.01885 0.01165 -0.0644 0.9004 1.0000
0.750 0.3023 0.01908 0.01180 -0.0654 0.8900 1.0000
1.000 0.3407 0.01921 0.01187 -0.0676 0.8813 1.0000
1.250 0.3941 0.01897 0.01159 -0.0720 0.8730 1.0000
1.500 0.4330 0.01880 0.01141 -0.0736 0.8611 1.0000
1.750 0.4692 0.01869 0.01129 -0.0748 0.8499 1.0000
2.000 0.5088 0.01849 0.01110 -0.0765 0.8411 1.0000
2.250 0.5469 0.01823 0.01086 -0.0776 0.8315 1.0000
2.500 0.5775 0.01812 0.01080 -0.0776 0.8193 1.0000
2.750 0.6087 0.01792 0.01064 -0.0775 0.8068 1.0000
3.000 0.6400 0.01766 0.01042 -0.0772 0.7939 1.0000
3.250 0.6708 0.01736 0.01016 -0.0768 0.7802 1.0000
3.500 0.7009 0.01704 0.00992 -0.0761 0.7656 1.0000
3.750 0.7308 0.01670 0.00962 -0.0754 0.7500 1.0000
4.000 0.7609 0.01633 0.00928 -0.0746 0.7334 1.0000
4.250 0.7855 0.01617 0.00918 -0.0732 0.7113 1.0000
4.500 0.8128 0.01589 0.00897 -0.0720 0.6887 1.0000
4.750 0.8387 0.01570 0.00879 -0.0706 0.6623 1.0000
5.000 0.8625 0.01563 0.00874 -0.0691 0.6300 1.0000
5.250 0.8863 0.01562 0.00868 -0.0675 0.5928 1.0000
5.500 0.9080 0.01579 0.00879 -0.0657 0.5470 1.0000
5.750 0.9286 0.01618 0.00896 -0.0638 0.4971 1.0000
6.000 0.9476 0.01683 0.00936 -0.0620 0.4462 1.0000
6.250 0.9663 0.01765 0.00991 -0.0603 0.4012 1.0000
6.500 0.9850 0.01853 0.01061 -0.0587 0.3610 1.0000
6.750 1.0040 0.01946 0.01138 -0.0573 0.3260 1.0000
7.000 1.0234 0.02047 0.01232 -0.0560 0.2955 1.0000
7.250 1.0430 0.02153 0.01329 -0.0548 0.2679 1.0000
7.500 1.0625 0.02261 0.01430 -0.0536 0.2429 1.0000
7.750 1.0818 0.02368 0.01528 -0.0524 0.2204 1.0000
8.000 1.0977 0.02447 0.01618 -0.0507 0.1967 1.0000
8.250 1.1090 0.02500 0.01675 -0.0486 0.1708 1.0000
8.500 1.1188 0.02547 0.01726 -0.0465 0.1414 1.0000
8.750 1.1285 0.02652 0.01828 -0.0443 0.1026 1.0000
9.000 1.1253 0.02934 0.02063 -0.0404 0.0535 1.0000
9.250 1.1288 0.03143 0.02279 -0.0371 0.0440 1.0000
9.500 1.1322 0.03365 0.02498 -0.0343 0.0395 1.0000
9.750 1.1444 0.03588 0.02737 -0.0322 0.0365 1.0000
10.000 1.1600 0.03825 0.02992 -0.0306 0.0341 1.0000
10.250 1.1769 0.04083 0.03268 -0.0294 0.0324 1.0000
10.500 1.1928 0.04376 0.03583 -0.0283 0.0313 1.0000
10.750 1.2056 0.04709 0.03941 -0.0270 0.0306 1.0000
11.000 1.2120 0.05059 0.04322 -0.0251 0.0303 1.0000
11.250 1.2117 0.05419 0.04712 -0.0231 0.0299 1.0000
11.500 1.2060 0.05766 0.05090 -0.0208 0.0298 1.0000
11.750 1.1946 0.06196 0.05546 -0.0190 0.0293 1.0000
12.000 1.1814 0.06579 0.05957 -0.0176 0.0293 1.0000
12.250 1.1659 0.06991 0.06396 -0.0168 0.0293 1.0000
12.500 1.1499 0.07387 0.06821 -0.0167 0.0296 1.0000
12.750 1.1296 0.07877 0.07340 -0.0176 0.0300 1.0000
13.000 1.1057 0.08483 0.07974 -0.0200 0.0303 1.0000
13.250 1.0518 0.09694 0.09233 -0.0277 0.0328 1.0000
13.500 1.0155 0.10849 0.10407 -0.0359 0.0339 1.0000
13.750 0.9815 0.12191 0.11759 -0.0454 0.0352 1.0000
14.000 0.9563 0.13486 0.13054 -0.0533 0.0367 1.0000
14.250 0.9428 0.14488 0.14052 -0.0586 0.0377 1.0000
14.500 0.9374 0.15226 0.14786 -0.0619 0.0385 1.0000
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