HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.53 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3015-il-1000000-n5.txt Download as CSV file: xf-hq3015-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/15 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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.7819 0.10658 0.10399 -0.0519 1.0000 0.0066
-17.500 -0.8786 0.08544 0.08255 -0.0636 1.0000 0.0064
-17.250 -0.9367 0.07136 0.06822 -0.0719 1.0000 0.0063
-17.000 -0.9718 0.06152 0.05817 -0.0781 1.0000 0.0062
-16.750 -0.9935 0.05474 0.05124 -0.0823 1.0000 0.0062
-16.500 -1.0105 0.04925 0.04562 -0.0855 1.0000 0.0063
-16.250 -1.0228 0.04476 0.04101 -0.0877 1.0000 0.0063
-16.000 -1.0287 0.04131 0.03746 -0.0892 1.0000 0.0064
-15.750 -1.0335 0.03817 0.03422 -0.0903 1.0000 0.0064
-15.500 -1.0379 0.03526 0.03121 -0.0910 1.0000 0.0064
-15.250 -1.0377 0.03298 0.02885 -0.0913 1.0000 0.0065
-15.000 -1.0369 0.03090 0.02669 -0.0912 1.0000 0.0066
-14.750 -1.0359 0.02901 0.02472 -0.0908 1.0000 0.0066
-14.500 -1.0333 0.02745 0.02309 -0.0900 1.0000 0.0067
-14.250 -1.0224 0.02581 0.02138 -0.0905 0.9902 0.0068
-14.000 -0.9992 0.02424 0.01972 -0.0932 0.9820 0.0069
-13.750 -0.9709 0.02292 0.01831 -0.0963 0.9743 0.0071
-13.500 -0.9389 0.02162 0.01692 -0.1000 0.9668 0.0073
-13.000 -0.8815 0.01956 0.01465 -0.1048 0.9330 0.0076
-12.750 -0.8683 0.01890 0.01384 -0.1034 0.9110 0.0077
-12.500 -0.8573 0.01839 0.01321 -0.1012 0.8963 0.0078
-12.250 -0.8424 0.01785 0.01257 -0.0997 0.8851 0.0079
-12.000 -0.8277 0.01722 0.01185 -0.0981 0.8752 0.0082
-11.750 -0.8103 0.01668 0.01123 -0.0969 0.8663 0.0084
-11.500 -0.7917 0.01618 0.01066 -0.0958 0.8592 0.0087
-11.250 -0.7719 0.01570 0.01012 -0.0948 0.8523 0.0091
-11.000 -0.7514 0.01526 0.00961 -0.0939 0.8460 0.0095
-10.750 -0.7295 0.01484 0.00913 -0.0933 0.8399 0.0098
-10.500 -0.7073 0.01446 0.00868 -0.0926 0.8337 0.0102
-10.250 -0.6854 0.01401 0.00819 -0.0919 0.8284 0.0111
-10.000 -0.6624 0.01360 0.00776 -0.0913 0.8225 0.0122
-9.750 -0.6392 0.01324 0.00734 -0.0907 0.8166 0.0135
-9.500 -0.6156 0.01285 0.00694 -0.0903 0.8115 0.0155
-9.250 -0.5913 0.01251 0.00659 -0.0898 0.8059 0.0182
-9.000 -0.5667 0.01222 0.00629 -0.0895 0.8004 0.0208
-8.750 -0.5412 0.01197 0.00601 -0.0892 0.7952 0.0230
-8.500 -0.5153 0.01175 0.00575 -0.0889 0.7896 0.0242
-8.250 -0.4899 0.01149 0.00547 -0.0886 0.7844 0.0258
-8.000 -0.4638 0.01126 0.00522 -0.0884 0.7795 0.0274
-7.750 -0.4374 0.01106 0.00498 -0.0883 0.7739 0.0286
-7.500 -0.4110 0.01089 0.00475 -0.0881 0.7687 0.0294
-7.250 -0.3847 0.01065 0.00450 -0.0879 0.7640 0.0310
-7.000 -0.3580 0.01044 0.00428 -0.0878 0.7587 0.0324
-6.750 -0.3314 0.01026 0.00407 -0.0876 0.7536 0.0341
-6.500 -0.3042 0.01011 0.00388 -0.0875 0.7490 0.0355
-6.250 -0.2774 0.00989 0.00368 -0.0874 0.7439 0.0387
-6.000 -0.2504 0.00973 0.00350 -0.0873 0.7387 0.0410
-5.750 -0.2231 0.00959 0.00332 -0.0872 0.7341 0.0428
-5.500 -0.1958 0.00940 0.00314 -0.0872 0.7291 0.0464
-5.250 -0.1685 0.00925 0.00299 -0.0871 0.7239 0.0501
-5.000 -0.1410 0.00913 0.00283 -0.0871 0.7191 0.0536
-4.750 -0.1134 0.00896 0.00268 -0.0871 0.7142 0.0583
-4.500 -0.0857 0.00885 0.00255 -0.0870 0.7087 0.0621
-4.250 -0.0584 0.00871 0.00242 -0.0870 0.7033 0.0689
-4.000 -0.0306 0.00859 0.00229 -0.0870 0.6972 0.0753
-3.750 -0.0032 0.00846 0.00218 -0.0869 0.6910 0.0851
-3.500 0.0244 0.00833 0.00207 -0.0869 0.6858 0.0972
-3.250 0.0522 0.00818 0.00196 -0.0870 0.6807 0.1127
-3.000 0.0795 0.00802 0.00185 -0.0869 0.6757 0.1350
-2.750 0.1069 0.00784 0.00176 -0.0869 0.6711 0.1648
-2.500 0.1344 0.00763 0.00167 -0.0870 0.6663 0.2011
-2.250 0.1615 0.00743 0.00158 -0.0870 0.6610 0.2431
-2.000 0.1885 0.00721 0.00149 -0.0869 0.6550 0.2902
-1.750 0.2142 0.00677 0.00137 -0.0868 0.6479 0.3885
-1.500 0.2410 0.00661 0.00133 -0.0867 0.6408 0.4448
-1.250 0.2690 0.00654 0.00131 -0.0867 0.6330 0.4717
-1.000 0.2966 0.00652 0.00131 -0.0867 0.6254 0.4956
-0.750 0.3245 0.00646 0.00132 -0.0867 0.6173 0.5257
-0.500 0.3520 0.00646 0.00134 -0.0866 0.6086 0.5463
-0.250 0.3803 0.00647 0.00135 -0.0866 0.6005 0.5585
0.000 0.4081 0.00650 0.00137 -0.0866 0.5934 0.5670
0.250 0.4364 0.00654 0.00139 -0.0866 0.5851 0.5741
0.500 0.4640 0.00659 0.00142 -0.0866 0.5758 0.5814
0.750 0.4917 0.00665 0.00145 -0.0865 0.5657 0.5892
1.000 0.5190 0.00671 0.00150 -0.0864 0.5535 0.5977
1.250 0.5456 0.00683 0.00156 -0.0861 0.5363 0.6067
1.500 0.5716 0.00696 0.00163 -0.0858 0.5175 0.6139
1.750 0.5982 0.00709 0.00170 -0.0855 0.5018 0.6199
2.000 0.6245 0.00723 0.00178 -0.0853 0.4857 0.6250
2.250 0.6504 0.00738 0.00188 -0.0849 0.4674 0.6302
2.500 0.6762 0.00754 0.00198 -0.0846 0.4501 0.6355
2.750 0.7020 0.00772 0.00209 -0.0842 0.4334 0.6400
3.000 0.7271 0.00790 0.00222 -0.0837 0.4147 0.6448
3.250 0.7517 0.00812 0.00236 -0.0832 0.3944 0.6501
3.500 0.7762 0.00835 0.00251 -0.0826 0.3744 0.6552
3.750 0.8003 0.00858 0.00267 -0.0820 0.3532 0.6605
4.000 0.8240 0.00883 0.00284 -0.0813 0.3322 0.6663
4.250 0.8471 0.00912 0.00303 -0.0806 0.3111 0.6716
4.500 0.8709 0.00934 0.00321 -0.0799 0.2967 0.6771
4.750 0.8949 0.00955 0.00339 -0.0793 0.2847 0.6834
5.250 0.9424 0.00996 0.00376 -0.0779 0.2632 0.6952
5.500 0.9654 0.01019 0.00396 -0.0771 0.2527 0.7019
5.750 0.9893 0.01036 0.00414 -0.0765 0.2449 0.7081
6.000 1.0117 0.01059 0.00436 -0.0756 0.2353 0.7149
6.500 1.0555 0.01105 0.00479 -0.0736 0.2150 0.7286
6.750 1.0758 0.01134 0.00504 -0.0724 0.2034 0.7363
7.000 1.0941 0.01160 0.00529 -0.0707 0.1931 0.7439
7.250 1.1122 0.01184 0.00553 -0.0690 0.1842 0.7518
7.500 1.1287 0.01215 0.00582 -0.0671 0.1746 0.7600
8.000 1.1620 0.01279 0.00646 -0.0633 0.1572 0.7792
8.250 1.1764 0.01321 0.00685 -0.0612 0.1457 0.7893
8.500 1.1924 0.01358 0.00722 -0.0593 0.1378 0.8007
8.750 1.2087 0.01391 0.00759 -0.0576 0.1322 0.8145
9.000 1.2229 0.01432 0.00802 -0.0555 0.1236 0.8313
9.250 1.2361 0.01472 0.00847 -0.0533 0.1151 0.8561
9.750 1.2760 0.01568 0.00957 -0.0521 0.0967 1.0000
10.000 1.2911 0.01623 0.01010 -0.0505 0.0903 1.0000
10.250 1.3036 0.01693 0.01076 -0.0487 0.0818 1.0000
10.500 1.3160 0.01766 0.01145 -0.0469 0.0734 1.0000
10.750 1.3281 0.01844 0.01220 -0.0452 0.0655 1.0000
11.000 1.3393 0.01930 0.01302 -0.0434 0.0583 1.0000
11.250 1.3502 0.02020 0.01389 -0.0418 0.0517 1.0000
11.500 1.3616 0.02110 0.01478 -0.0402 0.0458 1.0000
11.750 1.3707 0.02217 0.01582 -0.0385 0.0393 1.0000
12.250 1.3922 0.02421 0.01785 -0.0356 0.0316 1.0000
12.500 1.4016 0.02535 0.01900 -0.0342 0.0282 1.0000
12.750 1.4123 0.02643 0.02010 -0.0330 0.0255 1.0000
13.000 1.4188 0.02786 0.02152 -0.0315 0.0206 1.0000
13.250 1.4252 0.02932 0.02298 -0.0301 0.0167 1.0000
13.500 1.4326 0.03076 0.02443 -0.0290 0.0144 1.0000
13.750 1.4372 0.03247 0.02616 -0.0277 0.0106 1.0000
14.000 1.4360 0.03472 0.02841 -0.0262 0.0050 1.0000
14.250 1.4405 0.03657 0.03032 -0.0253 0.0041 1.0000
14.500 1.4455 0.03844 0.03224 -0.0244 0.0036 1.0000
14.750 1.4502 0.04040 0.03427 -0.0237 0.0033 1.0000
15.000 1.4561 0.04228 0.03621 -0.0231 0.0032 1.0000
15.250 1.4618 0.04424 0.03823 -0.0226 0.0032 1.0000
15.500 1.4642 0.04662 0.04068 -0.0221 0.0029 1.0000
16.000 1.4719 0.05120 0.04540 -0.0217 0.0029 1.0000
16.250 1.4747 0.05370 0.04799 -0.0216 0.0028 1.0000
16.500 1.4765 0.05638 0.05075 -0.0216 0.0027 1.0000
16.750 1.4779 0.05919 0.05364 -0.0218 0.0027 1.0000
17.000 1.4774 0.06229 0.05682 -0.0221 0.0027 1.0000
17.250 1.4767 0.06549 0.06011 -0.0225 0.0026 1.0000
17.500 1.4752 0.06889 0.06359 -0.0232 0.0026 1.0000
17.750 1.4713 0.07271 0.06751 -0.0240 0.0025 1.0000
18.000 1.4674 0.07662 0.07152 -0.0250 0.0025 1.0000
18.250 1.4607 0.08104 0.07604 -0.0263 0.0024 1.0000
18.500 1.4558 0.08529 0.08039 -0.0276 0.0024 1.0000
18.750 1.4488 0.08999 0.08520 -0.0293 0.0024 1.0000
19.000 1.4384 0.09529 0.09061 -0.0313 0.0023 1.0000
19.250 1.4309 0.10023 0.09566 -0.0333 0.0023 1.0000
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