HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/9 AIRFOIL (hq359-il) Reynolds number: 50,000 Max Cl/Cd: 41.98 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq359-il-50000-n5.txt Download as CSV file: xf-hq359-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/9 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3561 0.10235 0.09595 -0.0361 1.0000 0.0902
-7.750 -0.3748 0.10158 0.09537 -0.0358 1.0000 0.0910
-7.500 -0.3893 0.10007 0.09401 -0.0367 1.0000 0.0913
-7.250 -0.3838 0.09607 0.09008 -0.0337 1.0000 0.0924
-7.000 -0.3823 0.09311 0.08718 -0.0315 1.0000 0.0936
-6.750 -0.3853 0.09060 0.08468 -0.0303 1.0000 0.0947
-6.500 -0.3896 0.08802 0.08219 -0.0297 1.0000 0.0957
-6.250 -0.3932 0.08543 0.07966 -0.0298 1.0000 0.0966
-6.000 -0.3956 0.08257 0.07686 -0.0304 1.0000 0.0975
-5.750 -0.3847 0.07574 0.06983 -0.0369 1.0000 0.0477
-5.500 -0.3818 0.07237 0.06648 -0.0369 1.0000 0.0445
-5.250 -0.3646 0.06669 0.06048 -0.0444 1.0000 0.0371
-5.000 -0.3587 0.06339 0.05716 -0.0435 1.0000 0.0359
-4.750 -0.3474 0.05988 0.05357 -0.0446 1.0000 0.0348
-4.500 -0.3298 0.05608 0.04959 -0.0468 0.9994 0.0335
-4.250 -0.2947 0.05131 0.04447 -0.0525 0.9947 0.0319
-4.000 -0.2584 0.04685 0.03959 -0.0574 0.9899 0.0305
-3.750 -0.2192 0.04272 0.03491 -0.0620 0.9858 0.0291
-3.500 -0.1821 0.03919 0.03080 -0.0652 0.9814 0.0282
-3.250 -0.1440 0.03616 0.02717 -0.0679 0.9772 0.0274
-3.000 -0.1054 0.03361 0.02406 -0.0703 0.9736 0.0273
-2.750 -0.0723 0.03176 0.02181 -0.0716 0.9687 0.0284
-2.500 -0.0377 0.03026 0.01989 -0.0730 0.9640 0.0314
-2.250 -0.0015 0.02896 0.01822 -0.0742 0.9601 0.0346
-2.000 0.0274 0.02795 0.01688 -0.0739 0.9540 0.0371
-1.750 0.0610 0.02683 0.01563 -0.0750 0.9492 0.0417
-1.500 0.0958 0.02603 0.01455 -0.0763 0.9440 0.0516
-1.250 0.1317 0.02476 0.01362 -0.0787 0.9385 0.1227
-1.000 0.1442 0.02151 0.01348 -0.0730 0.9338 1.0000
-0.750 0.1762 0.02177 0.01308 -0.0742 0.9259 1.0000
-0.500 0.2158 0.02208 0.01289 -0.0769 0.9201 1.0000
-0.250 0.2456 0.02236 0.01282 -0.0778 0.9113 1.0000
0.000 0.2830 0.02266 0.01278 -0.0800 0.9048 1.0000
0.250 0.3143 0.02295 0.01279 -0.0811 0.8960 1.0000
0.500 0.3466 0.02324 0.01287 -0.0824 0.8875 1.0000
0.750 0.3838 0.02348 0.01292 -0.0844 0.8801 1.0000
1.000 0.4128 0.02377 0.01307 -0.0849 0.8701 1.0000
1.250 0.4458 0.02401 0.01316 -0.0861 0.8612 1.0000
1.500 0.4824 0.02418 0.01325 -0.0878 0.8531 1.0000
1.750 0.5109 0.02444 0.01345 -0.0881 0.8423 1.0000
2.000 0.5432 0.02456 0.01355 -0.0888 0.8311 1.0000
2.250 0.5779 0.02447 0.01347 -0.0895 0.8179 1.0000
2.500 0.6123 0.02425 0.01324 -0.0900 0.8032 1.0000
2.750 0.6457 0.02400 0.01301 -0.0902 0.7885 1.0000
3.000 0.6771 0.02386 0.01291 -0.0902 0.7745 1.0000
3.250 0.7072 0.02378 0.01289 -0.0900 0.7608 1.0000
3.500 0.7371 0.02369 0.01293 -0.0898 0.7465 1.0000
3.750 0.7672 0.02355 0.01287 -0.0895 0.7315 1.0000
4.000 0.7958 0.02344 0.01286 -0.0890 0.7149 1.0000
4.250 0.8213 0.02345 0.01297 -0.0880 0.6954 1.0000
4.500 0.8514 0.02324 0.01298 -0.0875 0.6762 1.0000
4.750 0.8766 0.02325 0.01312 -0.0864 0.6523 1.0000
5.000 0.9032 0.02321 0.01319 -0.0854 0.6259 1.0000
5.250 0.9300 0.02320 0.01326 -0.0844 0.5963 1.0000
5.500 0.9557 0.02329 0.01346 -0.0832 0.5627 1.0000
5.750 0.9810 0.02349 0.01366 -0.0821 0.5267 1.0000
6.000 1.0042 0.02392 0.01404 -0.0807 0.4896 1.0000
6.250 1.0267 0.02451 0.01454 -0.0795 0.4552 1.0000
6.500 1.0478 0.02527 0.01526 -0.0782 0.4236 1.0000
6.750 1.0685 0.02611 0.01609 -0.0770 0.3954 1.0000
7.000 1.0889 0.02701 0.01712 -0.0758 0.3699 1.0000
7.250 1.1089 0.02796 0.01809 -0.0746 0.3461 1.0000
7.500 1.1278 0.02893 0.01918 -0.0734 0.3228 1.0000
7.750 1.1457 0.02996 0.02030 -0.0720 0.2997 1.0000
8.000 1.1625 0.03104 0.02145 -0.0705 0.2771 1.0000
8.250 1.1774 0.03220 0.02273 -0.0688 0.2540 1.0000
8.500 1.1897 0.03340 0.02411 -0.0669 0.2299 1.0000
8.750 1.1984 0.03465 0.02549 -0.0646 0.2051 1.0000
9.000 1.2033 0.03596 0.02691 -0.0619 0.1794 1.0000
9.250 1.2056 0.03742 0.02839 -0.0591 0.1544 1.0000
9.500 1.2069 0.03922 0.03027 -0.0565 0.1311 1.0000
9.750 1.2094 0.04134 0.03240 -0.0543 0.1086 1.0000
10.000 1.2115 0.04386 0.03489 -0.0521 0.0935 1.0000
10.250 1.2134 0.04657 0.03764 -0.0501 0.0807 1.0000
10.500 1.2124 0.04941 0.04055 -0.0484 0.0686 1.0000
10.750 1.2138 0.05247 0.04382 -0.0467 0.0593 1.0000
11.000 1.2139 0.05591 0.04741 -0.0451 0.0522 1.0000
11.250 1.2086 0.05929 0.05089 -0.0441 0.0458 1.0000
11.500 1.2036 0.06316 0.05502 -0.0434 0.0402 1.0000
11.750 1.1974 0.06706 0.05913 -0.0431 0.0361 1.0000
12.000 1.1888 0.07127 0.06333 -0.0433 0.0332 1.0000
12.250 1.1821 0.07598 0.06843 -0.0436 0.0308 1.0000
12.500 1.1730 0.08114 0.07392 -0.0446 0.0290 1.0000
12.750 1.1628 0.08663 0.07968 -0.0461 0.0278 1.0000
13.000 1.1511 0.09255 0.08586 -0.0483 0.0271 1.0000
13.250 1.1386 0.09897 0.09251 -0.0511 0.0267 1.0000
13.500 1.1249 0.10611 0.09989 -0.0547 0.0267 1.0000
13.750 1.1095 0.11414 0.10816 -0.0591 0.0270 1.0000
14.000 1.0930 0.12317 0.11741 -0.0643 0.0280 1.0000
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