HT23 (ht23-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT23 (ht23-il) Reynolds number: 200,000 Max Cl/Cd: 50.52 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht23-il-200000-n5.txt Download as CSV file: xf-ht23-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6651 0.08463 0.08128 0.0194 1.0000 0.0175
-7.750 -0.6603 0.08059 0.07724 0.0163 1.0000 0.0170
-7.500 -0.6536 0.07505 0.07169 0.0109 1.0000 0.0165
-7.250 -0.6450 0.06838 0.06496 0.0045 1.0000 0.0158
-6.750 -0.6268 0.04363 0.03932 -0.0100 1.0000 0.0132
-6.500 -0.6110 0.03789 0.03311 -0.0114 1.0000 0.0131
-6.250 -0.5924 0.03258 0.02721 -0.0122 1.0000 0.0131
-6.000 -0.5708 0.02827 0.02226 -0.0123 1.0000 0.0132
-5.750 -0.5478 0.02503 0.01854 -0.0123 1.0000 0.0135
-5.500 -0.5231 0.02298 0.01620 -0.0122 1.0000 0.0140
-5.250 -0.4974 0.02186 0.01492 -0.0121 1.0000 0.0150
-5.000 -0.4711 0.02046 0.01324 -0.0118 1.0000 0.0163
-4.750 -0.4444 0.01881 0.01126 -0.0114 1.0000 0.0170
-4.500 -0.4175 0.01738 0.00959 -0.0110 1.0000 0.0175
-4.250 -0.3910 0.01604 0.00812 -0.0106 1.0000 0.0182
-4.000 -0.3646 0.01500 0.00706 -0.0103 1.0000 0.0193
-3.750 -0.3377 0.01421 0.00621 -0.0100 1.0000 0.0207
-3.500 -0.3105 0.01364 0.00557 -0.0098 1.0000 0.0234
-3.250 -0.2836 0.01287 0.00481 -0.0096 1.0000 0.0266
-3.000 -0.2563 0.01231 0.00420 -0.0093 1.0000 0.0304
-2.750 -0.2289 0.01177 0.00366 -0.0092 1.0000 0.0385
-2.500 -0.2015 0.01127 0.00320 -0.0090 1.0000 0.0535
-2.250 -0.1744 0.01068 0.00285 -0.0089 1.0000 0.0966
-2.000 -0.1476 0.01005 0.00259 -0.0089 1.0000 0.1835
-1.750 -0.1212 0.00941 0.00242 -0.0089 1.0000 0.2980
-1.500 -0.0957 0.00869 0.00230 -0.0087 1.0000 0.4458
-1.250 -0.0723 0.00791 0.00224 -0.0077 1.0000 0.6225
-1.000 -0.0479 0.00725 0.00226 -0.0060 0.9676 0.8162
-0.750 0.0051 0.00710 0.00217 -0.0101 0.8771 0.9825
-0.500 0.0335 0.00732 0.00201 -0.0094 0.7768 1.0000
-0.250 0.0569 0.00762 0.00190 -0.0079 0.6997 1.0000
0.000 0.0820 0.00789 0.00183 -0.0071 0.6406 1.0000
0.250 0.1081 0.00813 0.00179 -0.0065 0.5942 1.0000
0.500 0.1347 0.00835 0.00177 -0.0061 0.5559 1.0000
0.750 0.1616 0.00855 0.00177 -0.0058 0.5224 1.0000
1.000 0.1888 0.00874 0.00178 -0.0055 0.4928 1.0000
1.250 0.2160 0.00893 0.00181 -0.0053 0.4664 1.0000
1.500 0.2433 0.00912 0.00187 -0.0051 0.4421 1.0000
1.750 0.2708 0.00930 0.00193 -0.0049 0.4193 1.0000
2.000 0.2982 0.00950 0.00201 -0.0048 0.3985 1.0000
2.250 0.3257 0.00968 0.00211 -0.0046 0.3779 1.0000
2.500 0.3532 0.00988 0.00223 -0.0045 0.3584 1.0000
2.750 0.3807 0.01008 0.00236 -0.0043 0.3395 1.0000
3.000 0.4082 0.01028 0.00250 -0.0042 0.3203 1.0000
3.250 0.4357 0.01050 0.00266 -0.0041 0.3014 1.0000
3.500 0.4631 0.01074 0.00286 -0.0039 0.2824 1.0000
3.750 0.4906 0.01097 0.00305 -0.0038 0.2624 1.0000
4.000 0.5179 0.01124 0.00326 -0.0037 0.2417 1.0000
4.250 0.5452 0.01152 0.00349 -0.0036 0.2202 1.0000
4.750 0.5994 0.01220 0.00405 -0.0034 0.1730 1.0000
5.000 0.6264 0.01258 0.00438 -0.0034 0.1511 1.0000
5.250 0.6532 0.01300 0.00476 -0.0033 0.1303 1.0000
5.500 0.6800 0.01346 0.00517 -0.0032 0.1094 1.0000
5.750 0.7065 0.01399 0.00564 -0.0031 0.0901 1.0000
6.000 0.7328 0.01456 0.00619 -0.0030 0.0748 1.0000
6.250 0.7590 0.01518 0.00681 -0.0029 0.0624 1.0000
6.500 0.7851 0.01581 0.00747 -0.0027 0.0537 1.0000
6.750 0.8109 0.01649 0.00823 -0.0025 0.0482 1.0000
7.000 0.8365 0.01720 0.00900 -0.0023 0.0433 1.0000
7.250 0.8616 0.01803 0.00993 -0.0021 0.0395 1.0000
7.500 0.8867 0.01880 0.01084 -0.0018 0.0366 1.0000
7.750 0.9113 0.01966 0.01180 -0.0016 0.0342 1.0000
8.000 0.9341 0.02095 0.01312 -0.0013 0.0317 1.0000
8.250 0.9585 0.02180 0.01418 -0.0009 0.0299 1.0000
8.500 0.9819 0.02287 0.01542 -0.0006 0.0282 1.0000
8.750 1.0047 0.02403 0.01673 -0.0002 0.0268 1.0000
9.000 1.0268 0.02525 0.01807 0.0002 0.0255 1.0000
9.250 1.0461 0.02711 0.02003 0.0006 0.0241 1.0000
9.500 1.0675 0.02843 0.02165 0.0010 0.0230 1.0000
9.750 1.0870 0.03012 0.02361 0.0015 0.0219 1.0000
10.000 1.1049 0.03204 0.02581 0.0020 0.0210 1.0000
10.250 1.1213 0.03406 0.02809 0.0024 0.0203 1.0000
10.500 1.1367 0.03600 0.03025 0.0028 0.0195 1.0000
10.750 1.1507 0.03786 0.03227 0.0030 0.0188 1.0000
11.000 1.1593 0.04053 0.03511 0.0033 0.0181 1.0000
11.250 1.1624 0.04380 0.03876 0.0034 0.0177 1.0000
11.500 1.1594 0.04748 0.04282 0.0029 0.0173 1.0000
11.750 1.1465 0.05190 0.04752 0.0013 0.0171 1.0000
12.000 1.1307 0.05862 0.05451 -0.0051 0.0171 1.0000
12.250 1.1121 0.06724 0.06336 -0.0132 0.0172 1.0000
12.500 1.0891 0.07687 0.07313 -0.0211 0.0173 1.0000
12.750 1.0625 0.08716 0.08354 -0.0284 0.0176 1.0000
13.000 1.0329 0.09814 0.09459 -0.0353 0.0179 1.0000
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Polar data table (+)
Polar graphs
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