HT12 (ht12-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT12 (ht12-il) Reynolds number: 200,000 Max Cl/Cd: 35.1 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht12-il-200000-n5.txt Download as CSV file: xf-ht12-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HT12
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.7742 0.09642 0.09301 0.0386 1.0000 0.0147
-8.750 -0.7777 0.09079 0.08742 0.0352 1.0000 0.0146
-8.500 -0.7823 0.08477 0.08144 0.0307 1.0000 0.0145
-8.250 -0.7848 0.07726 0.07396 0.0229 1.0000 0.0143
-8.000 -0.7833 0.06714 0.06377 0.0125 1.0000 0.0141
-7.750 -0.7829 0.05305 0.04936 0.0018 1.0000 0.0138
-7.500 -0.7802 0.04103 0.03662 -0.0035 1.0000 0.0138
-7.250 -0.7672 0.03368 0.02848 -0.0052 1.0000 0.0141
-7.000 -0.7479 0.02890 0.02298 -0.0056 1.0000 0.0147
-6.750 -0.7250 0.02589 0.01938 -0.0055 1.0000 0.0156
-6.500 -0.7014 0.02345 0.01652 -0.0055 1.0000 0.0169
-6.250 -0.6765 0.02192 0.01479 -0.0054 1.0000 0.0179
-6.000 -0.6510 0.02034 0.01297 -0.0051 1.0000 0.0189
-5.750 -0.6250 0.01891 0.01127 -0.0048 1.0000 0.0201
-5.500 -0.5988 0.01764 0.00980 -0.0045 1.0000 0.0216
-5.250 -0.5724 0.01659 0.00859 -0.0042 1.0000 0.0238
-5.000 -0.5461 0.01562 0.00757 -0.0041 1.0000 0.0265
-4.750 -0.5193 0.01480 0.00665 -0.0038 1.0000 0.0291
-4.500 -0.4922 0.01415 0.00585 -0.0036 1.0000 0.0322
-4.250 -0.4654 0.01339 0.00510 -0.0035 1.0000 0.0384
-4.000 -0.4380 0.01283 0.00445 -0.0033 1.0000 0.0444
-3.750 -0.4107 0.01230 0.00392 -0.0031 1.0000 0.0554
-3.500 -0.3833 0.01176 0.00343 -0.0031 1.0000 0.0721
-3.250 -0.3560 0.01128 0.00305 -0.0030 1.0000 0.0981
-3.000 -0.3287 0.01082 0.00273 -0.0029 1.0000 0.1357
-2.750 -0.3015 0.01035 0.00248 -0.0029 1.0000 0.1864
-2.500 -0.2743 0.00993 0.00229 -0.0029 1.0000 0.2421
-2.250 -0.2470 0.00957 0.00210 -0.0028 1.0000 0.2962
-2.000 -0.2198 0.00924 0.00196 -0.0027 1.0000 0.3493
-1.750 -0.1927 0.00890 0.00184 -0.0025 1.0000 0.4053
-1.500 -0.1659 0.00853 0.00173 -0.0023 1.0000 0.4695
-1.250 -0.1399 0.00806 0.00162 -0.0019 1.0000 0.5569
-1.000 -0.1172 0.00741 0.00159 -0.0004 1.0000 0.7037
-0.750 -0.0961 0.00687 0.00160 0.0022 1.0000 0.8869
-0.500 -0.0542 0.00673 0.00152 -0.0005 1.0000 1.0000
-0.250 -0.0271 0.00672 0.00148 -0.0002 1.0000 1.0000
0.000 0.0001 0.00672 0.00147 0.0000 1.0000 1.0000
0.250 0.0272 0.00672 0.00148 0.0002 1.0000 1.0000
0.500 0.0544 0.00673 0.00152 0.0005 1.0000 1.0000
0.750 0.0964 0.00687 0.00160 -0.0022 0.8850 1.0000
1.000 0.1173 0.00741 0.00159 0.0004 0.7027 1.0000
1.250 0.1401 0.00806 0.00162 0.0019 0.5564 1.0000
1.500 0.1660 0.00854 0.00173 0.0023 0.4690 1.0000
1.750 0.1929 0.00890 0.00184 0.0025 0.4048 1.0000
2.000 0.2200 0.00924 0.00196 0.0027 0.3490 1.0000
2.250 0.2472 0.00958 0.00210 0.0028 0.2961 1.0000
2.500 0.2745 0.00994 0.00229 0.0029 0.2416 1.0000
2.750 0.3017 0.01035 0.00249 0.0029 0.1861 1.0000
3.000 0.3289 0.01082 0.00274 0.0029 0.1355 1.0000
3.250 0.3562 0.01129 0.00305 0.0030 0.0981 1.0000
3.500 0.3835 0.01177 0.00343 0.0031 0.0719 1.0000
3.750 0.4108 0.01231 0.00392 0.0031 0.0554 1.0000
4.000 0.4382 0.01283 0.00445 0.0033 0.0444 1.0000
4.250 0.4655 0.01339 0.00510 0.0035 0.0383 1.0000
4.500 0.4924 0.01416 0.00585 0.0036 0.0322 1.0000
4.750 0.5195 0.01480 0.00666 0.0038 0.0291 1.0000
5.000 0.5463 0.01563 0.00758 0.0040 0.0264 1.0000
5.250 0.5726 0.01659 0.00859 0.0042 0.0238 1.0000
5.500 0.5990 0.01765 0.00981 0.0045 0.0216 1.0000
5.750 0.6252 0.01892 0.01128 0.0048 0.0201 1.0000
6.000 0.6512 0.02036 0.01298 0.0051 0.0189 1.0000
6.250 0.6768 0.02194 0.01482 0.0053 0.0179 1.0000
6.500 0.7017 0.02346 0.01654 0.0055 0.0168 1.0000
6.750 0.7252 0.02593 0.01941 0.0055 0.0156 1.0000
7.000 0.7482 0.02891 0.02298 0.0056 0.0146 1.0000
7.250 0.7674 0.03369 0.02849 0.0052 0.0141 1.0000
7.500 0.7805 0.04106 0.03666 0.0035 0.0137 1.0000
7.750 0.7832 0.05311 0.04942 -0.0019 0.0138 1.0000
8.000 0.7837 0.06722 0.06385 -0.0126 0.0141 1.0000
8.250 0.7852 0.07733 0.07403 -0.0231 0.0143 1.0000
8.500 0.7829 0.08482 0.08150 -0.0308 0.0145 1.0000
8.750 0.7783 0.09085 0.08748 -0.0353 0.0146 1.0000
9.000 0.7749 0.09647 0.09307 -0.0388 0.0147 1.0000
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Polar data table (+)
Polar graphs
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