HQ 1.0/10 AIRFOIL (hq1010-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.0/10 AIRFOIL (hq1010-il) Reynolds number: 500,000 Max Cl/Cd: 68.24 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1010-il-500000-n5.txt Download as CSV file: xf-hq1010-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.8185 0.05615 0.05361 -0.0366 1.0000 0.0041
-11.750 -0.8409 0.04873 0.04600 -0.0424 1.0000 0.0041
-11.500 -0.8574 0.04376 0.04085 -0.0451 1.0000 0.0040
-11.250 -0.8743 0.03976 0.03665 -0.0459 1.0000 0.0040
-11.000 -0.8928 0.03644 0.03309 -0.0440 1.0000 0.0041
-10.750 -0.9006 0.03356 0.02994 -0.0418 1.0000 0.0041
-10.500 -0.9003 0.03080 0.02688 -0.0400 1.0000 0.0042
-10.250 -0.8939 0.02843 0.02422 -0.0385 1.0000 0.0042
-10.000 -0.8833 0.02640 0.02191 -0.0371 1.0000 0.0044
-9.750 -0.8699 0.02464 0.01991 -0.0359 1.0000 0.0044
-9.500 -0.8532 0.02327 0.01833 -0.0348 1.0000 0.0045
-9.250 -0.8380 0.02161 0.01642 -0.0335 1.0000 0.0047
-9.000 -0.8231 0.01989 0.01451 -0.0321 1.0000 0.0050
-8.750 -0.8038 0.01893 0.01343 -0.0311 1.0000 0.0053
-8.500 -0.7838 0.01812 0.01254 -0.0301 1.0000 0.0055
-8.250 -0.7638 0.01733 0.01164 -0.0290 1.0000 0.0058
-8.000 -0.7440 0.01657 0.01079 -0.0279 1.0000 0.0061
-7.750 -0.7210 0.01582 0.00993 -0.0273 0.9984 0.0065
-7.500 -0.6901 0.01509 0.00909 -0.0285 0.9917 0.0071
-7.250 -0.6583 0.01431 0.00819 -0.0298 0.9857 0.0080
-7.000 -0.6270 0.01365 0.00748 -0.0310 0.9782 0.0091
-6.750 -0.5941 0.01308 0.00683 -0.0323 0.9711 0.0102
-6.500 -0.5629 0.01256 0.00622 -0.0333 0.9612 0.0112
-6.250 -0.5321 0.01199 0.00558 -0.0341 0.9504 0.0133
-6.000 -0.5020 0.01156 0.00513 -0.0348 0.9382 0.0168
-5.750 -0.4736 0.01116 0.00471 -0.0351 0.9248 0.0228
-5.500 -0.4462 0.01088 0.00436 -0.0350 0.9123 0.0278
-5.250 -0.4198 0.01060 0.00405 -0.0348 0.9005 0.0338
-5.000 -0.3935 0.01038 0.00377 -0.0345 0.8892 0.0392
-4.750 -0.3674 0.01014 0.00351 -0.0342 0.8785 0.0473
-4.500 -0.3413 0.00990 0.00325 -0.0339 0.8689 0.0566
-4.000 -0.2888 0.00941 0.00277 -0.0334 0.8507 0.0863
-3.750 -0.2625 0.00915 0.00255 -0.0331 0.8423 0.1080
-3.500 -0.2364 0.00887 0.00234 -0.0329 0.8338 0.1402
-3.250 -0.2101 0.00857 0.00215 -0.0327 0.8256 0.1819
-2.500 -0.1326 0.00750 0.00163 -0.0321 0.8007 0.3660
-2.250 -0.1074 0.00709 0.00149 -0.0317 0.7917 0.4556
-2.000 -0.0807 0.00691 0.00142 -0.0315 0.7829 0.5017
-1.750 -0.0544 0.00674 0.00138 -0.0312 0.7746 0.5534
-1.500 -0.0276 0.00662 0.00136 -0.0309 0.7660 0.5964
-1.250 -0.0005 0.00656 0.00134 -0.0307 0.7565 0.6239
-1.000 0.0267 0.00654 0.00131 -0.0304 0.7450 0.6421
-0.750 0.0541 0.00654 0.00128 -0.0302 0.7328 0.6560
-0.500 0.0816 0.00653 0.00126 -0.0301 0.7210 0.6703
-0.250 0.1090 0.00653 0.00125 -0.0299 0.7092 0.6839
0.000 0.1365 0.00654 0.00125 -0.0297 0.6972 0.6966
0.250 0.1638 0.00656 0.00126 -0.0295 0.6837 0.7097
0.500 0.1911 0.00658 0.00127 -0.0293 0.6704 0.7226
0.750 0.2186 0.00661 0.00129 -0.0292 0.6581 0.7335
1.000 0.2461 0.00664 0.00131 -0.0290 0.6458 0.7419
1.250 0.2736 0.00668 0.00135 -0.0289 0.6323 0.7503
1.500 0.3009 0.00673 0.00139 -0.0287 0.6170 0.7593
1.750 0.3281 0.00679 0.00143 -0.0285 0.5993 0.7678
2.000 0.3549 0.00688 0.00148 -0.0283 0.5774 0.7769
2.250 0.3813 0.00701 0.00155 -0.0279 0.5475 0.7863
2.500 0.4071 0.00718 0.00163 -0.0275 0.5109 0.7958
2.750 0.4326 0.00740 0.00174 -0.0271 0.4704 0.8059
3.000 0.4575 0.00770 0.00188 -0.0266 0.4211 0.8166
3.250 0.4812 0.00810 0.00208 -0.0259 0.3566 0.8278
3.500 0.5056 0.00844 0.00227 -0.0254 0.3086 0.8399
3.750 0.5305 0.00870 0.00246 -0.0249 0.2775 0.8532
4.000 0.5553 0.00893 0.00266 -0.0244 0.2522 0.8686
4.500 0.6057 0.00931 0.00308 -0.0233 0.2090 0.9149
4.750 0.6396 0.00956 0.00331 -0.0248 0.1870 0.9531
5.000 0.6769 0.00992 0.00357 -0.0271 0.1564 0.9966
5.250 0.7016 0.01036 0.00386 -0.0268 0.1242 1.0000
5.500 0.7254 0.01081 0.00420 -0.0263 0.0975 1.0000
5.750 0.7496 0.01123 0.00454 -0.0259 0.0793 1.0000
6.000 0.7741 0.01162 0.00487 -0.0254 0.0662 1.0000
6.250 0.7983 0.01203 0.00523 -0.0250 0.0534 1.0000
6.500 0.8224 0.01246 0.00561 -0.0245 0.0419 1.0000
6.750 0.8465 0.01288 0.00603 -0.0240 0.0332 1.0000
7.000 0.8707 0.01327 0.00643 -0.0235 0.0271 1.0000
7.250 0.8943 0.01375 0.00689 -0.0230 0.0210 1.0000
7.500 0.9177 0.01423 0.00737 -0.0224 0.0163 1.0000
7.750 0.9408 0.01475 0.00791 -0.0218 0.0122 1.0000
8.000 0.9630 0.01537 0.00854 -0.0210 0.0090 1.0000
8.250 0.9854 0.01594 0.00915 -0.0203 0.0068 1.0000
8.500 1.0068 0.01663 0.00991 -0.0195 0.0058 1.0000
8.750 1.0285 0.01725 0.01062 -0.0187 0.0052 1.0000
9.000 1.0496 0.01793 0.01138 -0.0178 0.0048 1.0000
9.250 1.0701 0.01864 0.01218 -0.0169 0.0045 1.0000
9.500 1.0894 0.01946 0.01308 -0.0158 0.0042 1.0000
9.750 1.1076 0.02035 0.01407 -0.0147 0.0039 1.0000
10.000 1.1237 0.02140 0.01525 -0.0133 0.0038 1.0000
10.250 1.1359 0.02278 0.01677 -0.0114 0.0036 1.0000
10.500 1.1502 0.02384 0.01796 -0.0098 0.0035 1.0000
10.750 1.1624 0.02500 0.01929 -0.0080 0.0034 1.0000
11.000 1.1713 0.02620 0.02063 -0.0057 0.0033 1.0000
11.250 1.1763 0.02752 0.02209 -0.0030 0.0033 1.0000
11.500 1.1798 0.02897 0.02370 -0.0004 0.0032 1.0000
11.750 1.1822 0.03058 0.02546 0.0019 0.0032 1.0000
12.000 1.1826 0.03246 0.02750 0.0039 0.0031 1.0000
12.250 1.1821 0.03452 0.02972 0.0056 0.0031 1.0000
12.500 1.1801 0.03686 0.03223 0.0069 0.0031 1.0000
12.750 1.1749 0.03969 0.03525 0.0078 0.0030 1.0000
13.000 1.1748 0.04215 0.03785 0.0081 0.0030 1.0000
13.250 1.1683 0.04552 0.04139 0.0079 0.0030 1.0000
13.500 1.1613 0.04925 0.04528 0.0072 0.0028 1.0000
13.750 1.1527 0.05346 0.04966 0.0058 0.0029 1.0000
14.000 1.1350 0.05944 0.05585 0.0032 0.0029 1.0000
14.250 1.1198 0.06565 0.06224 -0.0001 0.0029 1.0000
14.500 1.1044 0.07247 0.06922 -0.0041 0.0029 1.0000
14.750 1.0838 0.08095 0.07788 -0.0093 0.0029 1.0000
15.000 1.0638 0.08996 0.08706 -0.0148 0.0029 1.0000
15.250 1.0427 0.09952 0.09675 -0.0205 0.0030 1.0000
15.500 1.0121 0.11143 0.10882 -0.0273 0.0031 1.0000
15.750 0.9893 0.12193 0.11944 -0.0332 0.0031 1.0000
16.000 0.9642 0.13349 0.13110 -0.0395 0.0032 1.0000
16.250 0.9385 0.14581 0.14352 -0.0460 0.0033 1.0000
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