HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/8 AIRFOIL (hq358-il) Reynolds number: 500,000 Max Cl/Cd: 106.04 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq358-il-500000-n5.txt Download as CSV file: xf-hq358-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/8 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3375 0.10140 0.09914 -0.0336 1.0000 0.0052
-8.750 -0.3358 0.09876 0.09654 -0.0337 1.0000 0.0052
-8.500 -0.3363 0.09611 0.09393 -0.0334 1.0000 0.0052
-8.250 -0.3285 0.09236 0.09019 -0.0358 0.9984 0.0052
-8.000 -0.3149 0.08832 0.08613 -0.0397 0.9938 0.0052
-7.750 -0.3011 0.08429 0.08211 -0.0439 0.9889 0.0052
-7.500 -0.2869 0.07999 0.07782 -0.0486 0.9834 0.0052
-7.250 -0.2717 0.07551 0.07334 -0.0540 0.9769 0.0052
-7.000 -0.2509 0.07062 0.06845 -0.0613 0.9716 0.0052
-6.750 -0.2280 0.06534 0.06316 -0.0698 0.9647 0.0052
-6.250 -0.1818 0.05291 0.05060 -0.0888 0.9486 0.0047
-6.000 -0.1609 0.04800 0.04557 -0.0945 0.9388 0.0044
-5.750 -0.1384 0.04305 0.04046 -0.0992 0.9300 0.0042
-5.500 -0.1150 0.03831 0.03551 -0.1027 0.9219 0.0040
-5.250 -0.0916 0.03383 0.03078 -0.1049 0.9137 0.0038
-5.000 -0.0660 0.02931 0.02593 -0.1065 0.9072 0.0037
-4.750 -0.0401 0.02495 0.02121 -0.1073 0.9000 0.0038
-4.500 -0.0126 0.02057 0.01637 -0.1076 0.8944 0.0041
-4.250 0.0148 0.01695 0.01229 -0.1074 0.8880 0.0046
-4.000 0.0425 0.01560 0.01065 -0.1072 0.8825 0.0052
-3.750 0.0691 0.01367 0.00838 -0.1073 0.8769 0.0065
-3.500 0.0963 0.01266 0.00715 -0.1072 0.8710 0.0071
-3.250 0.1238 0.01138 0.00563 -0.1069 0.8657 0.0072
-3.000 0.1510 0.01045 0.00455 -0.1066 0.8595 0.0074
-2.750 0.1785 0.00974 0.00370 -0.1064 0.8541 0.0081
-2.500 0.2060 0.00923 0.00309 -0.1063 0.8476 0.0091
-2.250 0.2337 0.00893 0.00271 -0.1062 0.8415 0.0104
-2.000 0.2613 0.00857 0.00222 -0.1061 0.8333 0.0110
-1.750 0.2888 0.00836 0.00186 -0.1059 0.8227 0.0113
-1.500 0.3160 0.00823 0.00160 -0.1056 0.8099 0.0122
-1.250 0.3434 0.00813 0.00143 -0.1054 0.7978 0.0153
-1.000 0.3708 0.00800 0.00131 -0.1053 0.7867 0.0373
-0.750 0.3982 0.00784 0.00120 -0.1052 0.7756 0.0789
-0.500 0.4252 0.00719 0.00112 -0.1056 0.7645 0.3060
-0.250 0.4507 0.00651 0.00121 -0.1056 0.7524 0.5886
0.000 0.4753 0.00631 0.00133 -0.1048 0.7383 0.7176
0.250 0.5013 0.00630 0.00136 -0.1043 0.7244 0.7541
0.500 0.5282 0.00634 0.00135 -0.1040 0.7107 0.7665
0.750 0.5549 0.00639 0.00136 -0.1037 0.6964 0.7789
1.000 0.5814 0.00644 0.00138 -0.1034 0.6822 0.7924
1.250 0.6076 0.00650 0.00141 -0.1030 0.6661 0.8075
1.750 0.6584 0.00660 0.00150 -0.1019 0.6283 0.8497
2.000 0.6815 0.00657 0.00154 -0.1008 0.6061 0.9031
2.250 0.7126 0.00672 0.00159 -0.1016 0.5753 1.0000
2.500 0.7379 0.00698 0.00171 -0.1011 0.5423 1.0000
2.750 0.7627 0.00730 0.00187 -0.1007 0.5036 1.0000
3.000 0.7869 0.00768 0.00205 -0.1001 0.4612 1.0000
3.250 0.8110 0.00808 0.00226 -0.0996 0.4193 1.0000
3.500 0.8351 0.00850 0.00249 -0.0991 0.3778 1.0000
3.750 0.8597 0.00887 0.00272 -0.0986 0.3423 1.0000
4.250 0.9087 0.00963 0.00326 -0.0978 0.2836 1.0000
4.500 0.9314 0.01020 0.00359 -0.0971 0.2398 1.0000
4.750 0.9555 0.01062 0.00387 -0.0966 0.2091 1.0000
5.000 0.9800 0.01099 0.00414 -0.0962 0.1854 1.0000
5.250 1.0031 0.01151 0.00453 -0.0956 0.1482 1.0000
5.500 1.0241 0.01228 0.00503 -0.0947 0.0982 1.0000
5.750 1.0393 0.01377 0.00598 -0.0930 0.0148 1.0000
6.000 1.0619 0.01438 0.00658 -0.0922 0.0044 1.0000
6.250 1.0855 0.01485 0.00713 -0.0915 0.0037 1.0000
6.500 1.1085 0.01538 0.00776 -0.0907 0.0033 1.0000
6.750 1.1310 0.01597 0.00846 -0.0899 0.0030 1.0000
7.000 1.1527 0.01664 0.00928 -0.0889 0.0029 1.0000
7.250 1.1735 0.01741 0.01017 -0.0878 0.0028 1.0000
7.500 1.1931 0.01828 0.01117 -0.0865 0.0027 1.0000
7.750 1.2114 0.01926 0.01228 -0.0850 0.0027 1.0000
8.000 1.2281 0.02037 0.01351 -0.0833 0.0026 1.0000
8.250 1.2420 0.02173 0.01500 -0.0813 0.0023 1.0000
8.500 1.2496 0.02385 0.01731 -0.0784 0.0019 1.0000
8.750 1.2682 0.02457 0.01813 -0.0771 0.0018 1.0000
9.000 1.2819 0.02586 0.01957 -0.0752 0.0017 1.0000
9.250 1.2935 0.02724 0.02110 -0.0729 0.0016 1.0000
9.500 1.3029 0.02874 0.02278 -0.0703 0.0016 1.0000
9.750 1.3110 0.03036 0.02457 -0.0677 0.0015 1.0000
10.000 1.3176 0.03211 0.02656 -0.0650 0.0014 1.0000
10.250 1.3223 0.03402 0.02868 -0.0623 0.0013 1.0000
10.500 1.3247 0.03617 0.03104 -0.0596 0.0012 1.0000
10.750 1.3255 0.03841 0.03349 -0.0570 0.0011 1.0000
11.000 1.3232 0.04105 0.03636 -0.0545 0.0011 1.0000
11.250 1.3192 0.04382 0.03935 -0.0523 0.0011 1.0000
11.500 1.3126 0.04699 0.04275 -0.0504 0.0010 1.0000
11.750 1.3041 0.05052 0.04650 -0.0490 0.0010 1.0000
12.000 1.2934 0.05451 0.05071 -0.0481 0.0010 1.0000
12.250 1.2806 0.05904 0.05546 -0.0480 0.0010 1.0000
12.500 1.2668 0.06407 0.06071 -0.0487 0.0010 1.0000
12.750 1.2508 0.06991 0.06675 -0.0504 0.0010 1.0000
13.000 1.2342 0.07641 0.07345 -0.0530 0.0010 1.0000
13.250 1.2167 0.08376 0.08099 -0.0568 0.0010 1.0000
13.500 1.1988 0.09206 0.08947 -0.0616 0.0010 1.0000
13.750 1.1805 0.10130 0.09889 -0.0672 0.0010 1.0000
14.000 1.1629 0.11111 0.10885 -0.0734 0.0010 1.0000
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