HQ 1.5/11 AIRFOIL (hq1511-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/11 AIRFOIL (hq1511-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.42 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1511-il-1000000-n5.txt Download as CSV file: xf-hq1511-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/11 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7836 0.09983 0.09784 -0.0207 1.0000 0.0042
-14.500 -0.8563 0.08049 0.07833 -0.0310 1.0000 0.0041
-14.250 -0.9110 0.06390 0.06151 -0.0414 1.0000 0.0039
-14.000 -0.9406 0.05347 0.05089 -0.0493 1.0000 0.0039
-13.750 -0.9513 0.04784 0.04512 -0.0535 1.0000 0.0040
-13.500 -0.9716 0.04173 0.03882 -0.0574 1.0000 0.0039
-13.250 -0.9856 0.03729 0.03420 -0.0594 1.0000 0.0039
-13.000 -0.9897 0.03447 0.03125 -0.0599 1.0000 0.0040
-12.750 -0.9934 0.03206 0.02871 -0.0597 1.0000 0.0040
-12.500 -1.0002 0.02987 0.02638 -0.0583 1.0000 0.0040
-12.250 -1.0006 0.02855 0.02494 -0.0558 1.0000 0.0041
-12.000 -0.9969 0.02705 0.02331 -0.0538 1.0000 0.0041
-11.750 -0.9885 0.02564 0.02176 -0.0522 1.0000 0.0042
-11.500 -0.9776 0.02432 0.02030 -0.0507 1.0000 0.0042
-11.250 -0.9641 0.02318 0.01904 -0.0494 1.0000 0.0043
-11.000 -0.9497 0.02206 0.01779 -0.0481 1.0000 0.0043
-10.750 -0.9335 0.02112 0.01675 -0.0468 1.0000 0.0044
-10.500 -0.9168 0.02025 0.01577 -0.0455 1.0000 0.0044
-10.250 -0.8925 0.01927 0.01467 -0.0458 0.9936 0.0045
-10.000 -0.8631 0.01835 0.01364 -0.0471 0.9865 0.0045
-9.750 -0.8327 0.01743 0.01261 -0.0485 0.9790 0.0046
-9.500 -0.8011 0.01661 0.01170 -0.0500 0.9711 0.0046
-9.250 -0.7709 0.01590 0.01088 -0.0511 0.9613 0.0047
-9.000 -0.7429 0.01528 0.01016 -0.0516 0.9495 0.0047
-8.750 -0.7179 0.01471 0.00950 -0.0515 0.9351 0.0047
-8.500 -0.6947 0.01410 0.00878 -0.0509 0.9193 0.0048
-8.250 -0.6720 0.01349 0.00805 -0.0501 0.9036 0.0049
-8.000 -0.6491 0.01289 0.00733 -0.0494 0.8894 0.0050
-7.750 -0.6252 0.01242 0.00675 -0.0489 0.8776 0.0051
-7.500 -0.6008 0.01199 0.00622 -0.0483 0.8676 0.0053
-7.250 -0.5756 0.01159 0.00575 -0.0480 0.8590 0.0055
-7.000 -0.5501 0.01125 0.00534 -0.0476 0.8515 0.0056
-6.750 -0.5241 0.01093 0.00495 -0.0474 0.8438 0.0057
-6.500 -0.4981 0.01063 0.00458 -0.0471 0.8365 0.0058
-6.250 -0.4717 0.01036 0.00425 -0.0469 0.8287 0.0060
-6.000 -0.4453 0.01011 0.00393 -0.0467 0.8211 0.0062
-5.750 -0.4186 0.00988 0.00365 -0.0465 0.8126 0.0065
-5.500 -0.3917 0.00966 0.00337 -0.0463 0.8046 0.0068
-5.250 -0.3649 0.00945 0.00312 -0.0461 0.7954 0.0078
-5.000 -0.3385 0.00916 0.00284 -0.0459 0.7858 0.0143
-4.750 -0.3117 0.00896 0.00262 -0.0457 0.7750 0.0207
-4.500 -0.2847 0.00880 0.00244 -0.0456 0.7650 0.0251
-4.250 -0.2574 0.00862 0.00228 -0.0455 0.7565 0.0316
-4.000 -0.2301 0.00849 0.00213 -0.0455 0.7488 0.0371
-3.750 -0.2025 0.00833 0.00198 -0.0454 0.7412 0.0443
-3.250 -0.1475 0.00802 0.00172 -0.0454 0.7271 0.0660
-3.000 -0.1201 0.00789 0.00159 -0.0453 0.7188 0.0790
-2.750 -0.0927 0.00769 0.00146 -0.0453 0.7106 0.1033
-2.500 -0.0667 0.00726 0.00131 -0.0452 0.7032 0.1866
-2.250 -0.0392 0.00707 0.00121 -0.0452 0.6961 0.2204
-2.000 -0.0117 0.00689 0.00112 -0.0452 0.6901 0.2537
-1.750 0.0154 0.00660 0.00101 -0.0452 0.6843 0.3154
-1.500 0.0417 0.00623 0.00093 -0.0451 0.6767 0.4087
-1.250 0.0692 0.00607 0.00087 -0.0451 0.6682 0.4518
-1.000 0.0963 0.00591 0.00083 -0.0450 0.6567 0.5010
-0.750 0.1233 0.00576 0.00082 -0.0449 0.6446 0.5574
-0.500 0.1509 0.00570 0.00083 -0.0448 0.6331 0.5923
-0.250 0.1789 0.00571 0.00083 -0.0448 0.6206 0.6076
0.000 0.2069 0.00573 0.00084 -0.0448 0.6081 0.6218
0.250 0.2348 0.00576 0.00086 -0.0447 0.5945 0.6344
0.500 0.2625 0.00583 0.00088 -0.0447 0.5755 0.6454
0.750 0.2900 0.00592 0.00091 -0.0446 0.5525 0.6547
1.000 0.3172 0.00605 0.00095 -0.0444 0.5244 0.6623
1.250 0.3442 0.00621 0.00101 -0.0443 0.4933 0.6698
1.500 0.3713 0.00637 0.00108 -0.0442 0.4679 0.6757
1.750 0.3986 0.00650 0.00116 -0.0441 0.4481 0.6818
2.000 0.4261 0.00663 0.00124 -0.0440 0.4309 0.6881
2.250 0.4530 0.00678 0.00134 -0.0439 0.4094 0.6956
2.500 0.4789 0.00708 0.00146 -0.0436 0.3583 0.7026
2.750 0.5031 0.00753 0.00165 -0.0431 0.2935 0.7083
3.000 0.5291 0.00781 0.00181 -0.0428 0.2624 0.7146
3.250 0.5557 0.00799 0.00194 -0.0427 0.2435 0.7210
3.500 0.5827 0.00813 0.00207 -0.0426 0.2327 0.7288
3.750 0.6098 0.00826 0.00220 -0.0424 0.2236 0.7365
4.000 0.6368 0.00839 0.00233 -0.0423 0.2162 0.7454
4.250 0.6637 0.00850 0.00247 -0.0422 0.2099 0.7547
4.500 0.6904 0.00863 0.00263 -0.0420 0.2020 0.7654
4.750 0.7167 0.00880 0.00279 -0.0418 0.1889 0.7766
5.000 0.7415 0.00911 0.00298 -0.0413 0.1526 0.7876
5.250 0.7652 0.00953 0.00327 -0.0408 0.1189 0.7986
5.500 0.7895 0.00988 0.00355 -0.0403 0.0971 0.8097
5.750 0.8144 0.01015 0.00381 -0.0398 0.0837 0.8220
6.000 0.8392 0.01039 0.00406 -0.0393 0.0732 0.8363
6.250 0.8634 0.01063 0.00432 -0.0387 0.0631 0.8534
6.500 0.8866 0.01089 0.00461 -0.0379 0.0525 0.8767
6.750 0.9082 0.01108 0.00490 -0.0367 0.0432 0.9259
7.000 0.9437 0.01145 0.00526 -0.0387 0.0334 1.0000
7.250 0.9678 0.01182 0.00561 -0.0382 0.0272 1.0000
7.500 0.9918 0.01220 0.00596 -0.0377 0.0230 1.0000
7.750 1.0161 0.01254 0.00630 -0.0372 0.0203 1.0000
8.000 1.0400 0.01290 0.00667 -0.0367 0.0183 1.0000
8.250 1.0633 0.01332 0.00709 -0.0361 0.0163 1.0000
8.500 1.0870 0.01367 0.00747 -0.0356 0.0155 1.0000
8.750 1.1104 0.01404 0.00787 -0.0350 0.0146 1.0000
9.000 1.1331 0.01445 0.00830 -0.0343 0.0136 1.0000
9.250 1.1551 0.01491 0.00877 -0.0335 0.0126 1.0000
9.500 1.1767 0.01540 0.00930 -0.0327 0.0119 1.0000
9.750 1.1987 0.01581 0.00976 -0.0319 0.0115 1.0000
10.000 1.2201 0.01625 0.01024 -0.0311 0.0109 1.0000
10.250 1.2408 0.01672 0.01075 -0.0302 0.0104 1.0000
10.500 1.2608 0.01722 0.01127 -0.0292 0.0098 1.0000
10.750 1.2796 0.01779 0.01187 -0.0280 0.0093 1.0000
11.000 1.2963 0.01847 0.01261 -0.0265 0.0088 1.0000
11.250 1.3143 0.01898 0.01318 -0.0252 0.0085 1.0000
11.500 1.3300 0.01950 0.01376 -0.0235 0.0083 1.0000
11.750 1.3437 0.02006 0.01437 -0.0215 0.0080 1.0000
12.000 1.3571 0.02065 0.01501 -0.0196 0.0076 1.0000
12.250 1.3692 0.02133 0.01575 -0.0176 0.0073 1.0000
12.500 1.3811 0.02206 0.01652 -0.0157 0.0070 1.0000
12.750 1.3915 0.02290 0.01743 -0.0138 0.0068 1.0000
13.000 1.4003 0.02389 0.01848 -0.0119 0.0065 1.0000
13.250 1.4073 0.02504 0.01971 -0.0099 0.0063 1.0000
13.500 1.4166 0.02609 0.02083 -0.0084 0.0061 1.0000
13.750 1.4254 0.02721 0.02204 -0.0069 0.0060 1.0000
14.000 1.4339 0.02840 0.02331 -0.0056 0.0058 1.0000
14.250 1.4398 0.02986 0.02485 -0.0043 0.0057 1.0000
14.500 1.4468 0.03128 0.02635 -0.0032 0.0055 1.0000
14.750 1.4512 0.03299 0.02816 -0.0021 0.0054 1.0000
15.000 1.4560 0.03474 0.02999 -0.0013 0.0052 1.0000
15.250 1.4592 0.03673 0.03207 -0.0006 0.0051 1.0000
15.500 1.4619 0.03884 0.03427 -0.0002 0.0049 1.0000
15.750 1.4625 0.04127 0.03679 0.0001 0.0048 1.0000
16.000 1.4605 0.04409 0.03971 0.0002 0.0047 1.0000
16.250 1.4584 0.04705 0.04277 0.0000 0.0046 1.0000
16.500 1.4531 0.05056 0.04638 -0.0006 0.0044 1.0000
16.750 1.4450 0.05463 0.05057 -0.0016 0.0044 1.0000
17.000 1.4339 0.05943 0.05551 -0.0032 0.0043 1.0000
17.250 1.4252 0.06418 0.06038 -0.0051 0.0042 1.0000
17.500 1.4113 0.07004 0.06638 -0.0078 0.0042 1.0000
17.750 1.3993 0.07589 0.07237 -0.0107 0.0042 1.0000
18.000 1.3792 0.08340 0.08003 -0.0146 0.0042 1.0000
18.250 1.3591 0.09125 0.08803 -0.0189 0.0042 1.0000
18.500 1.3340 0.10041 0.09735 -0.0239 0.0042 1.0000
18.750 1.3117 0.10922 0.10630 -0.0289 0.0042 1.0000
19.000 1.2825 0.11965 0.11688 -0.0349 0.0042 1.0000
19.250 1.2526 0.13040 0.12777 -0.0413 0.0042 1.0000
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