HT23 (ht23-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT23 (ht23-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.89 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht23-il-1000000-n5.txt Download as CSV file: xf-ht23-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HT23
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7046 0.12044 0.11883 0.0472 1.0000 0.0041
-10.000 -0.7067 0.11480 0.11320 0.0448 1.0000 0.0043
-8.500 -0.8344 0.02641 0.02332 -0.0115 1.0000 0.0046
-8.250 -0.8160 0.02280 0.01925 -0.0116 1.0000 0.0046
-8.000 -0.7959 0.01958 0.01557 -0.0114 1.0000 0.0048
-7.750 -0.7729 0.01759 0.01327 -0.0112 1.0000 0.0050
-7.500 -0.7476 0.01655 0.01209 -0.0110 1.0000 0.0051
-7.250 -0.7218 0.01568 0.01109 -0.0108 1.0000 0.0052
-7.000 -0.6959 0.01476 0.01002 -0.0106 1.0000 0.0054
-6.750 -0.6696 0.01397 0.00911 -0.0104 1.0000 0.0055
-6.500 -0.6430 0.01323 0.00826 -0.0102 1.0000 0.0057
-6.250 -0.6163 0.01256 0.00750 -0.0100 1.0000 0.0059
-6.000 -0.5893 0.01194 0.00678 -0.0098 1.0000 0.0062
-5.750 -0.5622 0.01140 0.00615 -0.0096 1.0000 0.0064
-5.500 -0.5349 0.01090 0.00557 -0.0095 1.0000 0.0066
-5.250 -0.5074 0.01048 0.00510 -0.0093 1.0000 0.0068
-5.000 -0.4799 0.01008 0.00465 -0.0092 1.0000 0.0069
-4.750 -0.4525 0.00949 0.00400 -0.0090 1.0000 0.0074
-4.500 -0.4248 0.00911 0.00360 -0.0089 1.0000 0.0078
-4.250 -0.3969 0.00881 0.00328 -0.0088 1.0000 0.0082
-4.000 -0.3690 0.00853 0.00299 -0.0087 1.0000 0.0087
-3.750 -0.3410 0.00829 0.00273 -0.0086 1.0000 0.0094
-3.500 -0.3084 0.00803 0.00243 -0.0095 0.9636 0.0102
-3.250 -0.2837 0.00798 0.00220 -0.0084 0.8815 0.0113
-3.000 -0.2592 0.00807 0.00200 -0.0073 0.7968 0.0125
-2.750 -0.2325 0.00813 0.00178 -0.0069 0.7205 0.0144
-2.500 -0.2049 0.00815 0.00162 -0.0068 0.6588 0.0175
-2.250 -0.1770 0.00813 0.00147 -0.0067 0.6109 0.0231
-2.000 -0.1490 0.00808 0.00133 -0.0067 0.5725 0.0339
-1.750 -0.1209 0.00800 0.00121 -0.0066 0.5391 0.0504
-1.250 -0.0647 0.00773 0.00100 -0.0067 0.4828 0.1233
-1.000 -0.0367 0.00755 0.00092 -0.0068 0.4583 0.1808
-0.750 -0.0086 0.00737 0.00087 -0.0068 0.4367 0.2426
-0.500 0.0195 0.00718 0.00082 -0.0069 0.4161 0.3138
-0.250 0.0475 0.00695 0.00079 -0.0070 0.3977 0.3994
0.000 0.0754 0.00670 0.00077 -0.0071 0.3801 0.4964
0.250 0.1033 0.00647 0.00077 -0.0071 0.3636 0.5913
0.500 0.1308 0.00624 0.00079 -0.0070 0.3475 0.6876
0.750 0.1577 0.00601 0.00081 -0.0067 0.3323 0.7822
1.000 0.1824 0.00580 0.00085 -0.0057 0.3178 0.8727
1.250 0.2059 0.00568 0.00086 -0.0043 0.3039 0.9556
1.500 0.2405 0.00576 0.00088 -0.0056 0.2875 1.0000
1.750 0.2687 0.00587 0.00092 -0.0056 0.2731 1.0000
2.000 0.2968 0.00600 0.00097 -0.0056 0.2578 1.0000
2.250 0.3250 0.00613 0.00103 -0.0055 0.2423 1.0000
2.500 0.3532 0.00627 0.00110 -0.0055 0.2268 1.0000
2.750 0.3813 0.00643 0.00118 -0.0055 0.2101 1.0000
3.000 0.4094 0.00659 0.00127 -0.0054 0.1925 1.0000
3.500 0.4653 0.00701 0.00151 -0.0054 0.1523 1.0000
3.750 0.4933 0.00721 0.00163 -0.0054 0.1361 1.0000
4.000 0.5212 0.00743 0.00178 -0.0054 0.1192 1.0000
4.250 0.5491 0.00765 0.00195 -0.0054 0.1053 1.0000
4.500 0.5769 0.00790 0.00213 -0.0053 0.0903 1.0000
4.750 0.6046 0.00818 0.00233 -0.0053 0.0749 1.0000
5.000 0.6322 0.00844 0.00254 -0.0053 0.0629 1.0000
5.500 0.6874 0.00901 0.00302 -0.0052 0.0430 1.0000
5.750 0.7149 0.00926 0.00327 -0.0051 0.0375 1.0000
6.000 0.7424 0.00956 0.00355 -0.0051 0.0322 1.0000
6.250 0.7699 0.00981 0.00381 -0.0050 0.0297 1.0000
6.500 0.7972 0.01011 0.00410 -0.0049 0.0267 1.0000
6.750 0.8244 0.01044 0.00444 -0.0048 0.0239 1.0000
7.000 0.8517 0.01070 0.00475 -0.0048 0.0229 1.0000
7.250 0.8788 0.01100 0.00508 -0.0047 0.0215 1.0000
7.500 0.9057 0.01135 0.00543 -0.0046 0.0198 1.0000
7.750 0.9323 0.01177 0.00589 -0.0044 0.0180 1.0000
8.000 0.9592 0.01209 0.00626 -0.0043 0.0174 1.0000
8.250 0.9858 0.01244 0.00666 -0.0042 0.0166 1.0000
8.500 1.0123 0.01282 0.00708 -0.0041 0.0156 1.0000
8.750 1.0385 0.01324 0.00752 -0.0039 0.0146 1.0000
9.000 1.0642 0.01380 0.00814 -0.0038 0.0134 1.0000
9.250 1.0902 0.01422 0.00862 -0.0036 0.0130 1.0000
9.500 1.1160 0.01467 0.00914 -0.0034 0.0125 1.0000
9.750 1.1415 0.01515 0.00968 -0.0032 0.0120 1.0000
10.000 1.1668 0.01565 0.01025 -0.0030 0.0114 1.0000
10.250 1.1918 0.01620 0.01084 -0.0028 0.0108 1.0000
10.500 1.2161 0.01687 0.01158 -0.0026 0.0101 1.0000
10.750 1.2402 0.01757 0.01237 -0.0023 0.0096 1.0000
11.000 1.2644 0.01817 0.01306 -0.0021 0.0093 1.0000
11.250 1.2882 0.01883 0.01382 -0.0018 0.0090 1.0000
11.500 1.3115 0.01953 0.01460 -0.0015 0.0086 1.0000
11.750 1.3346 0.02025 0.01540 -0.0012 0.0083 1.0000
12.000 1.3571 0.02099 0.01624 -0.0009 0.0079 1.0000
12.250 1.3789 0.02185 0.01716 -0.0005 0.0074 1.0000
12.500 1.3985 0.02303 0.01846 -0.0001 0.0070 1.0000
12.750 1.4188 0.02400 0.01955 0.0003 0.0068 1.0000
13.000 1.4385 0.02501 0.02068 0.0008 0.0066 1.0000
13.250 1.4570 0.02612 0.02191 0.0013 0.0064 1.0000
13.500 1.4743 0.02732 0.02324 0.0018 0.0062 1.0000
13.750 1.4901 0.02863 0.02468 0.0023 0.0060 1.0000
14.000 1.5042 0.03006 0.02624 0.0029 0.0058 1.0000
14.250 1.5158 0.03167 0.02798 0.0034 0.0057 1.0000
14.500 1.5239 0.03354 0.02998 0.0040 0.0055 1.0000
14.750 1.5238 0.03581 0.03239 0.0048 0.0054 1.0000
15.000 1.5141 0.03973 0.03649 0.0031 0.0053 1.0000
15.250 1.4964 0.04831 0.04531 -0.0058 0.0053 1.0000
15.500 1.4622 0.06022 0.05746 -0.0154 0.0054 1.0000
15.750 1.4091 0.07396 0.07141 -0.0239 0.0056 1.0000
16.000 1.3511 0.08814 0.08576 -0.0318 0.0058 1.0000
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Polar data table (+)
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