HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.94 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1512-il-1000000-n5.txt Download as CSV file: xf-hq1512-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/12 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.8630 0.11775 0.11553 -0.0166 1.0000 0.0044
-17.000 -0.9320 0.10008 0.09769 -0.0261 1.0000 0.0042
-16.750 -1.0182 0.07982 0.07718 -0.0375 1.0000 0.0038
-16.500 -1.0653 0.06680 0.06394 -0.0455 1.0000 0.0039
-16.250 -1.0965 0.05752 0.05447 -0.0516 1.0000 0.0039
-16.000 -1.1195 0.05043 0.04720 -0.0561 1.0000 0.0039
-15.750 -1.1253 0.04636 0.04303 -0.0583 1.0000 0.0039
-15.500 -1.1391 0.04156 0.03806 -0.0608 1.0000 0.0039
-15.250 -1.1421 0.03839 0.03479 -0.0620 1.0000 0.0039
-15.000 -1.1401 0.03597 0.03228 -0.0626 1.0000 0.0042
-14.750 -1.1408 0.03343 0.02961 -0.0631 1.0000 0.0042
-14.500 -1.1423 0.03100 0.02706 -0.0631 1.0000 0.0043
-14.250 -1.1377 0.02929 0.02527 -0.0627 1.0000 0.0043
-14.000 -1.1358 0.02753 0.02340 -0.0619 1.0000 0.0043
-13.750 -1.1324 0.02609 0.02185 -0.0607 1.0000 0.0044
-13.500 -1.1298 0.02482 0.02049 -0.0588 1.0000 0.0044
-13.250 -1.1237 0.02396 0.01955 -0.0565 1.0000 0.0045
-13.000 -1.1173 0.02301 0.01851 -0.0540 1.0000 0.0046
-12.750 -1.1075 0.02196 0.01737 -0.0522 1.0000 0.0048
-12.500 -1.0936 0.02115 0.01648 -0.0507 1.0000 0.0050
-12.250 -1.0782 0.02042 0.01570 -0.0493 1.0000 0.0052
-12.000 -1.0609 0.01982 0.01506 -0.0481 1.0000 0.0054
-11.750 -1.0436 0.01921 0.01440 -0.0468 1.0000 0.0056
-11.500 -1.0258 0.01866 0.01380 -0.0455 1.0000 0.0058
-11.250 -1.0081 0.01809 0.01318 -0.0442 1.0000 0.0061
-11.000 -0.9812 0.01750 0.01253 -0.0447 0.9944 0.0064
-10.750 -0.9514 0.01692 0.01186 -0.0458 0.9885 0.0066
-10.500 -0.9196 0.01625 0.01113 -0.0473 0.9830 0.0068
-10.250 -0.8890 0.01553 0.01035 -0.0486 0.9745 0.0073
-10.000 -0.8568 0.01496 0.00974 -0.0501 0.9652 0.0077
-9.750 -0.8255 0.01447 0.00919 -0.0513 0.9522 0.0080
-9.500 -0.7977 0.01405 0.00870 -0.0517 0.9338 0.0084
-9.250 -0.7730 0.01368 0.00822 -0.0513 0.9155 0.0088
-9.000 -0.7491 0.01335 0.00780 -0.0507 0.9010 0.0091
-8.750 -0.7248 0.01306 0.00742 -0.0502 0.8887 0.0094
-8.500 -0.7014 0.01262 0.00690 -0.0496 0.8779 0.0101
-8.250 -0.6772 0.01228 0.00651 -0.0491 0.8679 0.0108
-8.000 -0.6523 0.01197 0.00614 -0.0487 0.8588 0.0114
-7.750 -0.6270 0.01168 0.00577 -0.0483 0.8508 0.0119
-7.500 -0.6015 0.01141 0.00545 -0.0479 0.8427 0.0125
-7.250 -0.5757 0.01116 0.00514 -0.0477 0.8352 0.0130
-7.000 -0.5503 0.01082 0.00476 -0.0473 0.8275 0.0143
-6.750 -0.5243 0.01055 0.00446 -0.0470 0.8204 0.0153
-6.500 -0.4981 0.01032 0.00417 -0.0468 0.8129 0.0164
-6.250 -0.4716 0.01009 0.00390 -0.0466 0.8060 0.0179
-6.000 -0.4453 0.00983 0.00364 -0.0464 0.7988 0.0210
-5.750 -0.4187 0.00962 0.00340 -0.0462 0.7921 0.0246
-5.500 -0.3920 0.00940 0.00317 -0.0460 0.7849 0.0295
-5.250 -0.3653 0.00919 0.00296 -0.0458 0.7785 0.0354
-5.000 -0.3382 0.00900 0.00277 -0.0457 0.7715 0.0414
-4.750 -0.3114 0.00881 0.00258 -0.0456 0.7650 0.0499
-4.500 -0.2843 0.00860 0.00240 -0.0455 0.7584 0.0610
-4.250 -0.2573 0.00842 0.00223 -0.0454 0.7517 0.0736
-4.000 -0.2300 0.00823 0.00208 -0.0453 0.7452 0.0890
-3.750 -0.2031 0.00801 0.00193 -0.0452 0.7381 0.1104
-3.500 -0.1760 0.00781 0.00178 -0.0451 0.7314 0.1339
-3.250 -0.1493 0.00756 0.00164 -0.0450 0.7240 0.1699
-3.000 -0.1220 0.00737 0.00153 -0.0450 0.7170 0.1981
-2.750 -0.0947 0.00720 0.00142 -0.0449 0.7094 0.2262
-2.500 -0.0676 0.00700 0.00131 -0.0449 0.7016 0.2627
-2.000 -0.0148 0.00643 0.00108 -0.0446 0.6814 0.3846
-1.750 0.0119 0.00619 0.00101 -0.0445 0.6729 0.4438
-1.500 0.0393 0.00607 0.00096 -0.0444 0.6645 0.4810
-1.250 0.0671 0.00599 0.00094 -0.0444 0.6556 0.5078
-1.000 0.0948 0.00594 0.00091 -0.0443 0.6471 0.5315
-0.750 0.1228 0.00589 0.00091 -0.0443 0.6382 0.5562
-0.500 0.1506 0.00587 0.00091 -0.0443 0.6275 0.5761
-0.250 0.1786 0.00588 0.00091 -0.0442 0.6171 0.5902
0.000 0.2065 0.00589 0.00092 -0.0442 0.6052 0.6055
0.250 0.2343 0.00593 0.00094 -0.0442 0.5908 0.6191
0.500 0.2622 0.00597 0.00096 -0.0441 0.5776 0.6301
0.750 0.2901 0.00600 0.00099 -0.0441 0.5651 0.6401
1.000 0.3180 0.00606 0.00102 -0.0441 0.5511 0.6488
1.250 0.3455 0.00614 0.00106 -0.0440 0.5333 0.6572
1.500 0.3728 0.00625 0.00112 -0.0438 0.5127 0.6653
1.750 0.4000 0.00636 0.00118 -0.0437 0.4913 0.6729
2.000 0.4270 0.00652 0.00125 -0.0436 0.4665 0.6786
2.250 0.4535 0.00670 0.00135 -0.0434 0.4380 0.6847
2.500 0.4801 0.00690 0.00145 -0.0431 0.4090 0.6908
2.750 0.5060 0.00714 0.00158 -0.0429 0.3749 0.6969
3.000 0.5312 0.00745 0.00173 -0.0425 0.3310 0.7038
3.250 0.5563 0.00778 0.00191 -0.0421 0.2917 0.7104
3.500 0.5817 0.00806 0.00208 -0.0417 0.2624 0.7178
3.750 0.6072 0.00833 0.00225 -0.0414 0.2377 0.7246
4.000 0.6336 0.00851 0.00239 -0.0412 0.2213 0.7321
4.250 0.6603 0.00866 0.00253 -0.0410 0.2109 0.7389
4.500 0.6869 0.00880 0.00268 -0.0408 0.2014 0.7467
4.750 0.7133 0.00896 0.00283 -0.0406 0.1906 0.7539
5.000 0.7393 0.00915 0.00300 -0.0403 0.1782 0.7621
5.250 0.7648 0.00937 0.00319 -0.0400 0.1621 0.7699
5.500 0.7891 0.00970 0.00343 -0.0395 0.1382 0.7788
5.750 0.8133 0.01001 0.00368 -0.0389 0.1170 0.7878
6.000 0.8368 0.01039 0.00398 -0.0383 0.0959 0.7974
6.250 0.8603 0.01074 0.00428 -0.0376 0.0779 0.8083
6.500 0.8830 0.01113 0.00461 -0.0369 0.0613 0.8201
6.750 0.9068 0.01140 0.00489 -0.0362 0.0528 0.8331
7.000 0.9301 0.01168 0.00518 -0.0355 0.0456 0.8485
7.250 0.9527 0.01193 0.00549 -0.0347 0.0403 0.8686
7.500 0.9741 0.01208 0.00577 -0.0334 0.0370 0.9099
7.750 1.0120 0.01235 0.00612 -0.0359 0.0338 1.0000
8.000 1.0353 0.01270 0.00645 -0.0353 0.0307 1.0000
8.250 1.0587 0.01302 0.00677 -0.0347 0.0281 1.0000
8.500 1.0821 0.01333 0.00710 -0.0341 0.0260 1.0000
8.750 1.1046 0.01370 0.00746 -0.0333 0.0232 1.0000
9.000 1.1268 0.01408 0.00783 -0.0326 0.0208 1.0000
9.250 1.1484 0.01449 0.00823 -0.0317 0.0179 1.0000
9.500 1.1695 0.01491 0.00864 -0.0308 0.0158 1.0000
9.750 1.1901 0.01535 0.00909 -0.0298 0.0134 1.0000
10.000 1.2093 0.01586 0.00960 -0.0286 0.0102 1.0000
10.250 1.2231 0.01672 0.01042 -0.0267 0.0042 1.0000
10.500 1.2403 0.01729 0.01102 -0.0252 0.0038 1.0000
10.750 1.2550 0.01784 0.01162 -0.0232 0.0035 1.0000
11.000 1.2687 0.01840 0.01223 -0.0211 0.0032 1.0000
11.250 1.2814 0.01902 0.01290 -0.0190 0.0030 1.0000
11.500 1.2947 0.01963 0.01356 -0.0170 0.0028 1.0000
11.750 1.3073 0.02030 0.01431 -0.0151 0.0028 1.0000
12.000 1.3197 0.02100 0.01507 -0.0133 0.0026 1.0000
12.250 1.3312 0.02180 0.01592 -0.0115 0.0026 1.0000
12.500 1.3424 0.02263 0.01682 -0.0098 0.0025 1.0000
12.750 1.3525 0.02358 0.01784 -0.0081 0.0024 1.0000
13.000 1.3620 0.02460 0.01894 -0.0065 0.0024 1.0000
13.250 1.3706 0.02574 0.02015 -0.0049 0.0023 1.0000
13.500 1.3792 0.02691 0.02140 -0.0035 0.0023 1.0000
13.750 1.3858 0.02828 0.02285 -0.0021 0.0022 1.0000
14.000 1.3916 0.02979 0.02446 -0.0008 0.0021 1.0000
14.250 1.3971 0.03137 0.02612 0.0003 0.0021 1.0000
14.500 1.4015 0.03312 0.02795 0.0013 0.0021 1.0000
14.750 1.4044 0.03507 0.03000 0.0021 0.0020 1.0000
15.000 1.4066 0.03718 0.03221 0.0028 0.0020 1.0000
15.250 1.4071 0.03953 0.03465 0.0033 0.0020 1.0000
15.500 1.4060 0.04216 0.03739 0.0036 0.0019 1.0000
15.750 1.4010 0.04533 0.04068 0.0036 0.0019 1.0000
16.000 1.3946 0.04884 0.04432 0.0033 0.0018 1.0000
16.250 1.3923 0.05205 0.04763 0.0027 0.0019 1.0000
16.500 1.3814 0.05655 0.05226 0.0015 0.0018 1.0000
16.750 1.3687 0.06163 0.05748 -0.0002 0.0018 1.0000
17.000 1.3614 0.06616 0.06213 -0.0020 0.0018 1.0000
17.250 1.3477 0.07196 0.06806 -0.0045 0.0018 1.0000
17.500 1.3235 0.07991 0.07619 -0.0084 0.0017 1.0000
17.750 1.3108 0.08614 0.08255 -0.0116 0.0018 1.0000
18.000 1.2945 0.09329 0.08983 -0.0153 0.0018 1.0000
18.250 1.2726 0.10179 0.09848 -0.0200 0.0018 1.0000
18.500 1.2470 0.11123 0.10807 -0.0252 0.0018 1.0000
18.750 1.2207 0.12105 0.11804 -0.0307 0.0018 1.0000
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