HT08 (ht08-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT08 (ht08-il) Reynolds number: 100,000 Max Cl/Cd: 26.08 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht08-il-100000-n5.txt Download as CSV file: xf-ht08-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HT08
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.7415 0.09735 0.09251 0.0306 1.0000 0.0270
-8.500 -0.7433 0.09212 0.08732 0.0271 1.0000 0.0271
-8.250 -0.7462 0.08646 0.08172 0.0224 1.0000 0.0270
-8.000 -0.7454 0.07968 0.07493 0.0157 1.0000 0.0268
-7.750 -0.7423 0.07218 0.06736 0.0089 1.0000 0.0266
-7.500 -0.7373 0.06428 0.05929 0.0031 1.0000 0.0264
-7.250 -0.7300 0.05651 0.05123 -0.0012 1.0000 0.0262
-7.000 -0.7200 0.04898 0.04325 -0.0041 1.0000 0.0259
-6.750 -0.7060 0.04253 0.03621 -0.0057 1.0000 0.0258
-6.500 -0.6879 0.03733 0.03039 -0.0064 1.0000 0.0262
-6.250 -0.6669 0.03313 0.02556 -0.0066 1.0000 0.0269
-6.000 -0.6435 0.02987 0.02172 -0.0064 1.0000 0.0285
-5.750 -0.6182 0.02743 0.01861 -0.0061 1.0000 0.0313
-5.500 -0.5931 0.02476 0.01552 -0.0058 1.0000 0.0328
-5.250 -0.5677 0.02284 0.01343 -0.0055 1.0000 0.0349
-5.000 -0.5416 0.02142 0.01182 -0.0051 1.0000 0.0383
-4.750 -0.5148 0.02028 0.01039 -0.0047 1.0000 0.0431
-4.500 -0.4895 0.01876 0.00885 -0.0043 1.0000 0.0474
-4.250 -0.4631 0.01780 0.00775 -0.0039 1.0000 0.0545
-4.000 -0.4370 0.01683 0.00679 -0.0037 1.0000 0.0644
-3.750 -0.4106 0.01594 0.00588 -0.0034 1.0000 0.0779
-3.500 -0.3842 0.01512 0.00516 -0.0032 1.0000 0.1014
-3.250 -0.3579 0.01434 0.00452 -0.0030 1.0000 0.1407
-3.000 -0.3317 0.01360 0.00405 -0.0028 1.0000 0.2024
-2.750 -0.3058 0.01288 0.00369 -0.0026 1.0000 0.2877
-2.500 -0.2804 0.01214 0.00339 -0.0023 1.0000 0.3949
-2.250 -0.2565 0.01134 0.00314 -0.0014 1.0000 0.5335
-2.000 -0.2360 0.01054 0.00302 0.0009 1.0000 0.7051
-1.750 -0.2068 0.01003 0.00294 0.0023 1.0000 0.8919
-1.500 -0.1559 0.00986 0.00266 -0.0022 1.0000 1.0000
-1.250 -0.1301 0.00981 0.00247 -0.0018 1.0000 1.0000
-1.000 -0.1042 0.00976 0.00232 -0.0014 1.0000 1.0000
-0.750 -0.0782 0.00973 0.00220 -0.0011 1.0000 1.0000
-0.500 -0.0522 0.00970 0.00213 -0.0007 1.0000 1.0000
-0.250 -0.0261 0.00969 0.00207 -0.0004 1.0000 1.0000
0.000 0.0001 0.00968 0.00205 0.0000 1.0000 1.0000
0.250 0.0262 0.00969 0.00207 0.0004 1.0000 1.0000
0.500 0.0523 0.00970 0.00213 0.0007 1.0000 1.0000
0.750 0.0784 0.00973 0.00220 0.0011 1.0000 1.0000
1.000 0.1044 0.00976 0.00232 0.0014 1.0000 1.0000
1.250 0.1302 0.00981 0.00247 0.0018 1.0000 1.0000
1.500 0.1560 0.00986 0.00268 0.0022 1.0000 1.0000
1.750 0.2070 0.01003 0.00294 -0.0023 0.8911 1.0000
2.000 0.2361 0.01054 0.00302 -0.0009 0.7044 1.0000
2.250 0.2566 0.01134 0.00314 0.0014 0.5329 1.0000
2.500 0.2805 0.01214 0.00339 0.0023 0.3944 1.0000
2.750 0.3060 0.01288 0.00369 0.0026 0.2873 1.0000
3.000 0.3318 0.01361 0.00406 0.0028 0.2021 1.0000
3.250 0.3580 0.01435 0.00452 0.0030 0.1404 1.0000
3.500 0.3844 0.01512 0.00516 0.0032 0.1013 1.0000
3.750 0.4108 0.01594 0.00588 0.0034 0.0778 1.0000
4.000 0.4372 0.01683 0.00679 0.0037 0.0644 1.0000
4.250 0.4632 0.01781 0.00776 0.0039 0.0545 1.0000
4.500 0.4896 0.01877 0.00886 0.0043 0.0473 1.0000
4.750 0.5150 0.02029 0.01039 0.0047 0.0431 1.0000
5.000 0.5418 0.02142 0.01182 0.0051 0.0382 1.0000
5.250 0.5679 0.02285 0.01344 0.0055 0.0349 1.0000
5.500 0.5932 0.02477 0.01554 0.0057 0.0328 1.0000
5.750 0.6184 0.02744 0.01862 0.0061 0.0312 1.0000
6.000 0.6437 0.02989 0.02173 0.0064 0.0285 1.0000
6.250 0.6671 0.03315 0.02559 0.0065 0.0269 1.0000
6.500 0.6881 0.03736 0.03042 0.0064 0.0262 1.0000
6.750 0.7062 0.04257 0.03626 0.0057 0.0258 1.0000
7.000 0.7202 0.04903 0.04330 0.0041 0.0259 1.0000
7.250 0.7302 0.05657 0.05129 0.0011 0.0262 1.0000
7.500 0.7375 0.06436 0.05937 -0.0032 0.0264 1.0000
7.750 0.7425 0.07226 0.06744 -0.0090 0.0266 1.0000
8.000 0.7457 0.07976 0.07502 -0.0158 0.0268 1.0000
8.250 0.7466 0.08653 0.08179 -0.0226 0.0270 1.0000
8.500 0.7438 0.09219 0.08740 -0.0272 0.0271 1.0000
8.750 0.7420 0.09742 0.09258 -0.0308 0.0270 1.0000
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Polar data table (+)
Polar graphs
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