HT23 (ht23-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT23 (ht23-il) Reynolds number: 100,000 Max Cl/Cd: 37.2 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht23-il-100000.txt Download as CSV file: xf-ht23-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6420 0.10367 0.09897 0.0315 1.0000 0.0872
-8.000 -0.6431 0.09985 0.09520 0.0275 1.0000 0.0907
-7.750 -0.6532 0.09485 0.09023 0.0108 1.0000 0.0931
-7.500 -0.6441 0.08973 0.08519 0.0145 1.0000 0.0949
-7.250 -0.6316 0.08670 0.08218 0.0185 1.0000 0.0984
-7.000 -0.6233 0.08216 0.07760 0.0132 1.0000 0.1040
-6.750 -0.6165 0.07569 0.07106 0.0035 1.0000 0.1090
-6.500 -0.6028 0.07302 0.06844 0.0068 1.0000 0.1148
-6.250 -0.5907 0.06745 0.06273 0.0000 1.0000 0.1240
-6.000 -0.5755 0.06314 0.05822 -0.0046 1.0000 0.1369
-5.750 -0.5596 0.06019 0.05540 -0.0019 1.0000 0.1438
-5.500 -0.5423 0.05605 0.05115 -0.0042 1.0000 0.1556
-5.250 -0.5235 0.05234 0.04735 -0.0057 1.0000 0.1699
-5.000 -0.5037 0.04894 0.04386 -0.0067 1.0000 0.1858
-4.750 -0.4552 0.03475 0.02782 -0.0150 1.0000 0.0833
-4.500 -0.4234 0.02976 0.02177 -0.0144 1.0000 0.0649
-4.250 -0.3966 0.02647 0.01808 -0.0141 1.0000 0.0630
-4.000 -0.3683 0.02435 0.01546 -0.0136 1.0000 0.0650
-3.750 -0.3397 0.02243 0.01312 -0.0130 1.0000 0.0664
-3.500 -0.3125 0.01988 0.01049 -0.0125 1.0000 0.0688
-3.250 -0.2850 0.01844 0.00900 -0.0120 1.0000 0.0755
-3.000 -0.2581 0.01695 0.00753 -0.0114 1.0000 0.0856
-2.750 -0.2315 0.01565 0.00633 -0.0107 1.0000 0.1041
-2.500 -0.2058 0.01407 0.00514 -0.0101 1.0000 0.1573
-2.250 -0.1905 0.01093 0.00448 -0.0076 1.0000 0.6302
-2.000 -0.1376 0.01003 0.00414 -0.0096 1.0000 1.0000
-1.750 -0.1120 0.00995 0.00379 -0.0092 1.0000 1.0000
-1.500 -0.0863 0.00989 0.00351 -0.0088 1.0000 1.0000
-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 0.0696 0.00982 0.00284 -0.0068 1.0000 1.0000
0.250 0.0954 0.00986 0.00288 -0.0065 1.0000 1.0000
0.500 0.1210 0.00992 0.00299 -0.0064 1.0000 1.0000
0.750 0.1459 0.01003 0.00319 -0.0064 1.0000 1.0000
1.000 0.2134 0.01021 0.00337 -0.0142 0.9008 1.0000
1.250 0.2426 0.01057 0.00340 -0.0128 0.7903 1.0000
1.500 0.2643 0.01104 0.00350 -0.0105 0.7162 1.0000
1.750 0.2877 0.01152 0.00365 -0.0089 0.6622 1.0000
2.000 0.3125 0.01199 0.00385 -0.0079 0.6183 1.0000
2.250 0.3382 0.01243 0.00409 -0.0071 0.5798 1.0000
2.500 0.3640 0.01287 0.00437 -0.0064 0.5470 1.0000
2.750 0.3901 0.01331 0.00464 -0.0058 0.5167 1.0000
3.000 0.4164 0.01373 0.00495 -0.0053 0.4880 1.0000
3.250 0.4429 0.01415 0.00528 -0.0049 0.4604 1.0000
3.500 0.4694 0.01458 0.00566 -0.0044 0.4337 1.0000
3.750 0.4958 0.01502 0.00603 -0.0040 0.4079 1.0000
4.000 0.5221 0.01547 0.00638 -0.0035 0.3830 1.0000
4.250 0.5485 0.01590 0.00677 -0.0031 0.3567 1.0000
4.500 0.5748 0.01632 0.00721 -0.0027 0.3298 1.0000
4.750 0.6010 0.01675 0.00761 -0.0023 0.3022 1.0000
5.000 0.6270 0.01719 0.00802 -0.0019 0.2736 1.0000
5.250 0.6527 0.01766 0.00846 -0.0016 0.2435 1.0000
5.500 0.6781 0.01823 0.00892 -0.0012 0.2122 1.0000
5.750 0.7035 0.01900 0.00966 -0.0009 0.1789 1.0000
6.000 0.7286 0.02009 0.01068 -0.0004 0.1503 1.0000
6.250 0.7532 0.02129 0.01174 -0.0001 0.1285 1.0000
6.500 0.7782 0.02287 0.01329 0.0004 0.1140 1.0000
6.750 0.8033 0.02423 0.01476 0.0009 0.1023 1.0000
7.000 0.8284 0.02598 0.01681 0.0014 0.0938 1.0000
7.250 0.8524 0.02834 0.01910 0.0017 0.0881 1.0000
7.500 0.8763 0.03026 0.02164 0.0023 0.0824 1.0000
7.750 0.8993 0.03228 0.02382 0.0027 0.0777 1.0000
8.000 0.9193 0.03610 0.02789 0.0030 0.0753 1.0000
8.250 0.9365 0.03978 0.03236 0.0034 0.0738 1.0000
8.500 0.9489 0.04423 0.03754 0.0034 0.0716 1.0000
8.750 0.9556 0.04967 0.04360 0.0028 0.0705 1.0000
9.000 0.9533 0.05666 0.05114 0.0012 0.0715 1.0000
9.250 0.9453 0.06394 0.05878 -0.0014 0.0728 1.0000
9.500 0.9367 0.07074 0.06577 -0.0042 0.0742 1.0000
9.750 0.9331 0.07691 0.07206 -0.0065 0.0763 1.0000
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Polar data table (+)
Polar graphs
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