HT23 (ht23-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT23 (ht23-il) Reynolds number: 100,000 Max Cl/Cd: 39.77 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht23-il-100000-n5.txt Download as CSV file: xf-ht23-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5278 0.11026 0.10559 0.0228 1.0000 0.0506
-9.250 -0.5395 0.10617 0.10155 0.0185 1.0000 0.0527
-9.000 -0.5433 0.10179 0.09721 0.0162 1.0000 0.0529
-8.750 -0.5397 0.09328 0.08865 0.0165 1.0000 0.0307
-8.500 -0.5385 0.08914 0.08453 0.0161 1.0000 0.0297
-8.250 -0.5402 0.08454 0.07996 0.0149 1.0000 0.0288
-8.000 -0.5440 0.07962 0.07508 0.0130 1.0000 0.0281
-7.750 -0.5494 0.07444 0.06995 0.0106 1.0000 0.0275
-7.250 -0.6347 0.06703 0.06206 -0.0013 1.0000 0.0236
-7.000 -0.6250 0.06194 0.05686 -0.0040 1.0000 0.0233
-6.750 -0.6130 0.05619 0.05089 -0.0070 1.0000 0.0231
-6.500 -0.5984 0.05000 0.04432 -0.0099 1.0000 0.0234
-6.000 -0.5637 0.04086 0.03447 -0.0126 1.0000 0.0249
-5.750 -0.5426 0.03662 0.02974 -0.0132 1.0000 0.0250
-5.500 -0.5195 0.03263 0.02515 -0.0135 1.0000 0.0249
-5.250 -0.4952 0.02955 0.02161 -0.0134 1.0000 0.0251
-5.000 -0.4698 0.02699 0.01862 -0.0132 1.0000 0.0256
-4.750 -0.4437 0.02482 0.01609 -0.0129 1.0000 0.0264
-4.500 -0.4171 0.02299 0.01397 -0.0126 1.0000 0.0277
-4.250 -0.3900 0.02158 0.01226 -0.0121 1.0000 0.0305
-4.000 -0.3634 0.01996 0.01044 -0.0117 1.0000 0.0326
-3.750 -0.3371 0.01860 0.00906 -0.0113 1.0000 0.0348
-3.500 -0.3106 0.01754 0.00793 -0.0108 1.0000 0.0385
-3.250 -0.2843 0.01655 0.00691 -0.0104 1.0000 0.0446
-3.000 -0.2575 0.01571 0.00600 -0.0100 1.0000 0.0523
-2.750 -0.2309 0.01484 0.00517 -0.0097 1.0000 0.0682
-2.500 -0.2045 0.01390 0.00449 -0.0095 1.0000 0.1101
-2.250 -0.1790 0.01283 0.00406 -0.0093 1.0000 0.2371
-2.000 -0.1548 0.01175 0.00380 -0.0089 1.0000 0.4270
-1.750 -0.1349 0.01065 0.00368 -0.0067 1.0000 0.6673
-1.500 -0.1002 0.00996 0.00358 -0.0061 1.0000 0.9388
-1.250 -0.0604 0.00984 0.00329 -0.0084 1.0000 1.0000
-1.000 -0.0344 0.00981 0.00311 -0.0081 1.0000 1.0000
-0.750 -0.0084 0.00979 0.00298 -0.0077 1.0000 1.0000
-0.500 0.0176 0.00979 0.00289 -0.0074 1.0000 1.0000
-0.250 0.0436 0.00980 0.00284 -0.0071 1.0000 1.0000
0.000 0.0839 0.00989 0.00284 -0.0096 0.9358 1.0000
0.250 0.1234 0.01007 0.00279 -0.0113 0.8332 1.0000
0.500 0.1486 0.01037 0.00273 -0.0099 0.7456 1.0000
0.750 0.1725 0.01070 0.00272 -0.0084 0.6790 1.0000
1.000 0.1977 0.01101 0.00274 -0.0075 0.6267 1.0000
1.250 0.2236 0.01130 0.00279 -0.0068 0.5842 1.0000
1.500 0.2498 0.01158 0.00288 -0.0062 0.5479 1.0000
1.750 0.2762 0.01186 0.00298 -0.0058 0.5162 1.0000
2.000 0.3030 0.01214 0.00311 -0.0054 0.4873 1.0000
2.250 0.3298 0.01241 0.00326 -0.0051 0.4607 1.0000
2.500 0.3567 0.01268 0.00346 -0.0047 0.4361 1.0000
3.000 0.4104 0.01325 0.00386 -0.0042 0.3904 1.0000
3.250 0.4373 0.01356 0.00409 -0.0039 0.3693 1.0000
3.500 0.4643 0.01385 0.00439 -0.0036 0.3473 1.0000
3.750 0.4911 0.01418 0.00466 -0.0034 0.3264 1.0000
4.000 0.5180 0.01449 0.00497 -0.0032 0.3045 1.0000
4.250 0.5447 0.01485 0.00528 -0.0029 0.2829 1.0000
4.500 0.5715 0.01520 0.00568 -0.0027 0.2596 1.0000
4.750 0.5981 0.01559 0.00604 -0.0025 0.2360 1.0000
5.000 0.6246 0.01603 0.00644 -0.0024 0.2113 1.0000
5.250 0.6510 0.01649 0.00693 -0.0022 0.1851 1.0000
5.500 0.6771 0.01704 0.00745 -0.0021 0.1588 1.0000
5.750 0.7031 0.01768 0.00806 -0.0020 0.1340 1.0000
6.000 0.7286 0.01845 0.00878 -0.0018 0.1128 1.0000
6.250 0.7540 0.01929 0.00968 -0.0016 0.0944 1.0000
6.500 0.7789 0.02024 0.01064 -0.0014 0.0805 1.0000
6.750 0.8033 0.02132 0.01178 -0.0011 0.0716 1.0000
7.000 0.8271 0.02242 0.01291 -0.0008 0.0638 1.0000
7.250 0.8513 0.02353 0.01423 -0.0004 0.0578 1.0000
7.500 0.8746 0.02479 0.01558 0.0000 0.0537 1.0000
7.750 0.8970 0.02630 0.01722 0.0004 0.0502 1.0000
8.000 0.9201 0.02767 0.01884 0.0009 0.0462 1.0000
8.250 0.9421 0.02919 0.02050 0.0013 0.0434 1.0000
8.500 0.9625 0.03115 0.02258 0.0017 0.0415 1.0000
8.750 0.9826 0.03340 0.02518 0.0022 0.0396 1.0000
9.000 1.0015 0.03564 0.02785 0.0026 0.0372 1.0000
9.250 1.0187 0.03797 0.03053 0.0029 0.0352 1.0000
9.500 1.0336 0.04066 0.03354 0.0032 0.0340 1.0000
9.750 1.0463 0.04353 0.03669 0.0034 0.0330 1.0000
10.000 1.0556 0.04684 0.04027 0.0035 0.0322 1.0000
10.250 1.0567 0.05121 0.04502 0.0032 0.0315 1.0000
10.500 1.0490 0.05615 0.05046 0.0020 0.0310 1.0000
10.750 1.0327 0.06152 0.05617 -0.0003 0.0309 1.0000
11.000 1.0121 0.06840 0.06327 -0.0065 0.0311 1.0000
11.250 0.9904 0.07745 0.07243 -0.0150 0.0314 1.0000
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Polar data table (+)
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