HT23 (ht23-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT23 (ht23-il) Reynolds number: 500,000 Max Cl/Cd: 65.81 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht23-il-500000-n5.txt Download as CSV file: xf-ht23-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6988 0.09148 0.08931 0.0311 1.0000 0.0070
-8.500 -0.7015 0.08603 0.08389 0.0274 1.0000 0.0070
-8.250 -0.7045 0.08002 0.07790 0.0220 1.0000 0.0070
-8.000 -0.7021 0.07186 0.06972 0.0123 1.0000 0.0070
-7.750 -0.6965 0.06248 0.06025 0.0027 1.0000 0.0071
-7.500 -0.6883 0.05287 0.05044 -0.0045 1.0000 0.0072
-7.250 -0.6972 0.03010 0.02645 -0.0114 1.0000 0.0071
-7.000 -0.6803 0.02433 0.01994 -0.0117 1.0000 0.0071
-6.750 -0.6581 0.02139 0.01656 -0.0116 1.0000 0.0072
-6.500 -0.6338 0.01952 0.01440 -0.0114 1.0000 0.0074
-6.250 -0.6084 0.01810 0.01276 -0.0112 1.0000 0.0076
-6.000 -0.5825 0.01685 0.01130 -0.0110 1.0000 0.0079
-5.750 -0.5563 0.01573 0.00998 -0.0107 1.0000 0.0083
-5.500 -0.5298 0.01470 0.00877 -0.0105 1.0000 0.0086
-5.250 -0.5030 0.01380 0.00773 -0.0102 1.0000 0.0090
-5.000 -0.4761 0.01302 0.00683 -0.0099 1.0000 0.0094
-4.750 -0.4490 0.01238 0.00608 -0.0097 1.0000 0.0097
-4.500 -0.4221 0.01164 0.00529 -0.0095 1.0000 0.0104
-4.250 -0.3947 0.01122 0.00486 -0.0094 1.0000 0.0112
-4.000 -0.3672 0.01077 0.00437 -0.0092 1.0000 0.0120
-3.750 -0.3396 0.01030 0.00384 -0.0091 1.0000 0.0127
-3.500 -0.3119 0.00985 0.00336 -0.0089 1.0000 0.0137
-3.250 -0.2842 0.00946 0.00297 -0.0088 1.0000 0.0152
-3.000 -0.2563 0.00917 0.00266 -0.0086 1.0000 0.0172
-2.750 -0.2285 0.00886 0.00237 -0.0085 1.0000 0.0211
-2.500 -0.2007 0.00859 0.00212 -0.0084 1.0000 0.0276
-2.250 -0.1633 0.00836 0.00191 -0.0103 0.9324 0.0416
-2.000 -0.1399 0.00832 0.00174 -0.0088 0.8398 0.0669
-1.750 -0.1160 0.00831 0.00158 -0.0077 0.7535 0.1091
-1.500 -0.0900 0.00821 0.00144 -0.0073 0.6819 0.1737
-1.250 -0.0630 0.00806 0.00133 -0.0072 0.6274 0.2473
-1.000 -0.0358 0.00784 0.00124 -0.0072 0.5847 0.3388
-0.750 -0.0086 0.00754 0.00118 -0.0072 0.5482 0.4518
-0.500 0.0182 0.00719 0.00114 -0.0071 0.5171 0.5796
-0.250 0.0439 0.00681 0.00112 -0.0066 0.4887 0.7148
0.000 0.0672 0.00650 0.00113 -0.0052 0.4649 0.8329
0.250 0.0908 0.00634 0.00112 -0.0036 0.4428 0.9406
0.500 0.1292 0.00642 0.00109 -0.0057 0.4181 1.0000
0.750 0.1571 0.00654 0.00109 -0.0056 0.3985 1.0000
1.000 0.1850 0.00665 0.00110 -0.0055 0.3800 1.0000
1.250 0.2129 0.00677 0.00112 -0.0054 0.3621 1.0000
1.500 0.2409 0.00690 0.00116 -0.0053 0.3448 1.0000
1.750 0.2688 0.00703 0.00120 -0.0053 0.3279 1.0000
2.250 0.3248 0.00731 0.00133 -0.0051 0.2953 1.0000
2.500 0.3527 0.00746 0.00141 -0.0051 0.2787 1.0000
2.750 0.3807 0.00762 0.00150 -0.0050 0.2622 1.0000
3.000 0.4086 0.00779 0.00160 -0.0049 0.2445 1.0000
3.250 0.4364 0.00799 0.00172 -0.0049 0.2262 1.0000
3.500 0.4642 0.00819 0.00186 -0.0048 0.2071 1.0000
3.750 0.4919 0.00844 0.00201 -0.0048 0.1838 1.0000
4.000 0.5196 0.00869 0.00217 -0.0048 0.1636 1.0000
4.250 0.5472 0.00894 0.00237 -0.0047 0.1462 1.0000
4.500 0.5748 0.00923 0.00258 -0.0047 0.1272 1.0000
4.750 0.6023 0.00951 0.00281 -0.0046 0.1107 1.0000
5.000 0.6297 0.00982 0.00306 -0.0046 0.0946 1.0000
5.250 0.6570 0.01018 0.00336 -0.0045 0.0776 1.0000
5.500 0.6841 0.01055 0.00367 -0.0045 0.0636 1.0000
5.750 0.7113 0.01091 0.00400 -0.0044 0.0531 1.0000
6.000 0.7384 0.01127 0.00436 -0.0043 0.0450 1.0000
6.250 0.7655 0.01165 0.00475 -0.0042 0.0389 1.0000
6.500 0.7924 0.01204 0.00515 -0.0041 0.0347 1.0000
6.750 0.8192 0.01249 0.00563 -0.0040 0.0313 1.0000
7.000 0.8460 0.01286 0.00607 -0.0039 0.0291 1.0000
7.250 0.8726 0.01330 0.00654 -0.0038 0.0267 1.0000
7.500 0.8986 0.01390 0.00719 -0.0036 0.0243 1.0000
7.750 0.9249 0.01437 0.00774 -0.0034 0.0232 1.0000
8.000 0.9510 0.01486 0.00832 -0.0033 0.0220 1.0000
8.250 0.9769 0.01536 0.00889 -0.0031 0.0206 1.0000
8.500 1.0024 0.01594 0.00952 -0.0029 0.0192 1.0000
8.750 1.0268 0.01683 0.01049 -0.0027 0.0179 1.0000
9.000 1.0519 0.01742 0.01120 -0.0025 0.0173 1.0000
9.250 1.0767 0.01809 0.01200 -0.0022 0.0166 1.0000
9.500 1.1012 0.01876 0.01276 -0.0020 0.0157 1.0000
9.750 1.1255 0.01942 0.01350 -0.0017 0.0149 1.0000
10.000 1.1491 0.02021 0.01437 -0.0015 0.0141 1.0000
10.250 1.1701 0.02151 0.01578 -0.0011 0.0133 1.0000
10.500 1.1928 0.02239 0.01684 -0.0008 0.0130 1.0000
10.750 1.2145 0.02341 0.01801 -0.0004 0.0125 1.0000
11.000 1.2357 0.02446 0.01921 0.0000 0.0120 1.0000
11.250 1.2565 0.02549 0.02038 0.0003 0.0114 1.0000
11.500 1.2769 0.02649 0.02151 0.0007 0.0109 1.0000
11.750 1.2963 0.02760 0.02272 0.0010 0.0105 1.0000
12.000 1.3126 0.02912 0.02437 0.0014 0.0101 1.0000
12.250 1.3239 0.03127 0.02672 0.0019 0.0097 1.0000
12.500 1.3366 0.03306 0.02872 0.0023 0.0095 1.0000
12.750 1.3457 0.03516 0.03103 0.0027 0.0093 1.0000
13.000 1.3503 0.03762 0.03371 0.0028 0.0091 1.0000
13.250 1.3447 0.04081 0.03711 0.0025 0.0089 1.0000
13.500 1.3345 0.04674 0.04328 -0.0032 0.0089 1.0000
13.750 1.3200 0.05512 0.05188 -0.0113 0.0088 1.0000
14.000 1.2977 0.06419 0.06113 -0.0182 0.0089 1.0000
14.250 1.2701 0.07362 0.07070 -0.0242 0.0090 1.0000
14.500 1.2403 0.08321 0.08041 -0.0298 0.0091 1.0000
14.750 1.2102 0.09291 0.09023 -0.0352 0.0092 1.0000
15.000 1.1801 0.10281 0.10022 -0.0405 0.0093 1.0000
15.250 1.1500 0.11308 0.11057 -0.0459 0.0094 1.0000
15.500 1.1205 0.12398 0.12157 -0.0516 0.0094 1.0000
15.750 1.0880 0.13611 0.13380 -0.0578 0.0095 1.0000
16.000 1.0112 0.16168 0.15951 -0.0709 0.0097 1.0000
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Polar data table (+)
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