HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.93 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3510-il-1000000-n5.txt Download as CSV file: xf-hq3510-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/10 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3112 0.08920 0.08759 -0.0498 0.9827 0.0039
-9.000 -0.3000 0.08457 0.08296 -0.0543 0.9773 0.0040
-8.500 -0.4122 0.02470 0.02186 -0.1055 0.9026 0.0032
-8.250 -0.3989 0.02081 0.01751 -0.1056 0.8935 0.0033
-8.000 -0.3754 0.01995 0.01653 -0.1056 0.8873 0.0034
-7.750 -0.3533 0.01842 0.01476 -0.1056 0.8805 0.0035
-7.500 -0.3284 0.01780 0.01404 -0.1055 0.8748 0.0037
-7.250 -0.3049 0.01637 0.01236 -0.1054 0.8685 0.0038
-7.000 -0.2803 0.01533 0.01111 -0.1053 0.8628 0.0040
-6.750 -0.2549 0.01437 0.00995 -0.1052 0.8573 0.0043
-6.500 -0.2293 0.01350 0.00890 -0.1051 0.8515 0.0045
-6.250 -0.2034 0.01272 0.00795 -0.1050 0.8464 0.0047
-6.000 -0.1768 0.01210 0.00720 -0.1049 0.8408 0.0049
-5.750 -0.1503 0.01153 0.00650 -0.1048 0.8354 0.0051
-5.500 -0.1234 0.01102 0.00588 -0.1047 0.8303 0.0052
-5.250 -0.0960 0.01079 0.00559 -0.1047 0.8246 0.0054
-5.000 -0.0704 0.00975 0.00435 -0.1045 0.8194 0.0060
-4.750 -0.0431 0.00930 0.00384 -0.1045 0.8136 0.0064
-4.500 -0.0158 0.00895 0.00342 -0.1044 0.8079 0.0068
-4.250 0.0117 0.00865 0.00305 -0.1044 0.8024 0.0072
-4.000 0.0394 0.00839 0.00273 -0.1044 0.7961 0.0075
-3.750 0.0671 0.00818 0.00244 -0.1044 0.7903 0.0079
-3.500 0.0950 0.00798 0.00219 -0.1044 0.7837 0.0081
-3.250 0.1227 0.00783 0.00197 -0.1043 0.7768 0.0083
-3.000 0.1504 0.00770 0.00178 -0.1043 0.7674 0.0088
-2.750 0.1781 0.00759 0.00159 -0.1042 0.7558 0.0094
-2.500 0.2056 0.00751 0.00143 -0.1041 0.7431 0.0101
-2.250 0.2332 0.00743 0.00131 -0.1040 0.7316 0.0122
-2.000 0.2607 0.00730 0.00120 -0.1040 0.7213 0.0288
-1.750 0.2884 0.00723 0.00113 -0.1039 0.7109 0.0382
-1.500 0.3161 0.00717 0.00106 -0.1039 0.7004 0.0505
-1.250 0.3437 0.00712 0.00101 -0.1039 0.6892 0.0639
-1.000 0.3713 0.00706 0.00096 -0.1039 0.6790 0.0870
-0.500 0.4249 0.00626 0.00086 -0.1042 0.6538 0.3799
-0.250 0.4514 0.00596 0.00089 -0.1042 0.6401 0.5148
0.000 0.4785 0.00589 0.00093 -0.1041 0.6271 0.5756
0.250 0.5055 0.00587 0.00099 -0.1039 0.6134 0.6280
0.500 0.5323 0.00592 0.00105 -0.1037 0.5969 0.6590
0.750 0.5593 0.00601 0.00110 -0.1036 0.5793 0.6725
1.000 0.5863 0.00612 0.00115 -0.1034 0.5610 0.6798
1.250 0.6129 0.00626 0.00121 -0.1032 0.5399 0.6870
1.500 0.6390 0.00645 0.00129 -0.1029 0.5119 0.6941
1.750 0.6648 0.00666 0.00139 -0.1026 0.4818 0.7021
2.000 0.6907 0.00687 0.00151 -0.1023 0.4543 0.7097
2.250 0.7163 0.00711 0.00164 -0.1019 0.4253 0.7181
2.500 0.7416 0.00735 0.00178 -0.1016 0.3955 0.7264
2.750 0.7670 0.00761 0.00192 -0.1012 0.3670 0.7356
3.000 0.7919 0.00789 0.00210 -0.1007 0.3337 0.7453
3.250 0.8165 0.00820 0.00228 -0.1003 0.3022 0.7552
3.500 0.8416 0.00845 0.00246 -0.0999 0.2796 0.7657
3.750 0.8674 0.00864 0.00262 -0.0996 0.2660 0.7768
4.000 0.8931 0.00880 0.00280 -0.0993 0.2549 0.7884
4.250 0.9187 0.00897 0.00297 -0.0989 0.2456 0.8013
4.500 0.9443 0.00912 0.00313 -0.0986 0.2361 0.8164
4.750 0.9692 0.00927 0.00331 -0.0981 0.2246 0.8355
5.000 0.9921 0.00949 0.00353 -0.0973 0.2039 0.8652
5.250 1.0190 0.00953 0.00371 -0.0973 0.1910 1.0000
5.500 1.0437 0.00983 0.00393 -0.0968 0.1730 1.0000
5.750 1.0668 0.01026 0.00422 -0.0962 0.1463 1.0000
6.000 1.0888 0.01077 0.00457 -0.0954 0.1173 1.0000
6.250 1.1080 0.01153 0.00509 -0.0942 0.0765 1.0000
6.500 1.1237 0.01262 0.00584 -0.0924 0.0243 1.0000
6.750 1.1431 0.01337 0.00647 -0.0911 0.0046 1.0000
7.000 1.1662 0.01375 0.00686 -0.0904 0.0034 1.0000
7.250 1.1894 0.01410 0.00723 -0.0897 0.0031 1.0000
7.500 1.2121 0.01448 0.00765 -0.0890 0.0029 1.0000
7.750 1.2342 0.01489 0.00813 -0.0881 0.0026 1.0000
8.000 1.2557 0.01534 0.00862 -0.0872 0.0024 1.0000
8.250 1.2765 0.01583 0.00917 -0.0862 0.0023 1.0000
8.500 1.2964 0.01636 0.00975 -0.0850 0.0021 1.0000
8.750 1.3150 0.01698 0.01044 -0.0836 0.0019 1.0000
9.000 1.3300 0.01787 0.01142 -0.0817 0.0017 1.0000
9.250 1.3458 0.01850 0.01212 -0.0798 0.0016 1.0000
9.500 1.3615 0.01905 0.01274 -0.0780 0.0016 1.0000
9.750 1.3752 0.01972 0.01348 -0.0759 0.0016 1.0000
10.000 1.3886 0.02041 0.01423 -0.0738 0.0015 1.0000
10.250 1.4016 0.02114 0.01502 -0.0717 0.0015 1.0000
10.500 1.4128 0.02199 0.01595 -0.0695 0.0014 1.0000
10.750 1.4228 0.02294 0.01699 -0.0672 0.0014 1.0000
11.000 1.4321 0.02395 0.01808 -0.0649 0.0014 1.0000
11.250 1.4398 0.02510 0.01933 -0.0626 0.0013 1.0000
11.500 1.4492 0.02616 0.02047 -0.0607 0.0013 1.0000
11.750 1.4556 0.02749 0.02190 -0.0585 0.0012 1.0000
12.000 1.4613 0.02891 0.02342 -0.0564 0.0012 1.0000
12.500 1.4726 0.03194 0.02665 -0.0529 0.0011 1.0000
12.750 1.4745 0.03387 0.02869 -0.0511 0.0011 1.0000
13.000 1.4796 0.03559 0.03050 -0.0497 0.0010 1.0000
13.250 1.4808 0.03774 0.03277 -0.0483 0.0010 1.0000
13.500 1.4807 0.04013 0.03528 -0.0471 0.0009 1.0000
13.750 1.4797 0.04274 0.03800 -0.0462 0.0009 1.0000
14.000 1.4770 0.04565 0.04103 -0.0455 0.0009 1.0000
14.250 1.4725 0.04893 0.04444 -0.0450 0.0009 1.0000
14.500 1.4731 0.05177 0.04737 -0.0450 0.0008 1.0000
14.750 1.4663 0.05571 0.05144 -0.0452 0.0008 1.0000
15.000 1.4576 0.06016 0.05603 -0.0459 0.0008 1.0000
15.250 1.4479 0.06505 0.06106 -0.0470 0.0008 1.0000
15.500 1.4430 0.06947 0.06559 -0.0484 0.0008 1.0000
15.750 1.4306 0.07534 0.07161 -0.0506 0.0008 1.0000
16.000 1.4167 0.08184 0.07826 -0.0532 0.0008 1.0000
16.250 1.4048 0.08829 0.08484 -0.0562 0.0008 1.0000
16.500 1.3905 0.09546 0.09216 -0.0597 0.0008 1.0000
16.750 1.3741 0.10329 0.10013 -0.0636 0.0008 1.0000
17.000 1.3596 0.11097 0.10794 -0.0676 0.0008 1.0000
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