HT12 (ht12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT12 (ht12-il) Reynolds number: 1,000,000 Max Cl/Cd: 64.68 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht12-il-1000000-n5.txt Download as CSV file: xf-ht12-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -1.1394 0.04050 0.03852 -0.0022 1.0000 0.0039
-11.000 -1.1384 0.03403 0.03160 -0.0045 1.0000 0.0040
-10.750 -1.1266 0.03027 0.02749 -0.0051 1.0000 0.0041
-10.500 -1.1104 0.02748 0.02438 -0.0053 1.0000 0.0042
-10.250 -1.0917 0.02520 0.02183 -0.0052 1.0000 0.0043
-10.000 -1.0711 0.02333 0.01970 -0.0051 1.0000 0.0044
-9.750 -1.0493 0.02174 0.01787 -0.0050 1.0000 0.0045
-9.500 -1.0263 0.02039 0.01631 -0.0048 1.0000 0.0046
-9.250 -1.0026 0.01920 0.01494 -0.0046 1.0000 0.0047
-9.000 -0.9783 0.01818 0.01375 -0.0044 1.0000 0.0048
-8.750 -0.9547 0.01671 0.01205 -0.0041 1.0000 0.0050
-8.500 -0.9300 0.01560 0.01077 -0.0040 1.0000 0.0053
-8.250 -0.9043 0.01487 0.00995 -0.0038 1.0000 0.0055
-8.000 -0.8782 0.01428 0.00926 -0.0036 1.0000 0.0058
-7.750 -0.8518 0.01377 0.00868 -0.0035 1.0000 0.0062
-7.500 -0.8253 0.01327 0.00812 -0.0033 1.0000 0.0065
-7.250 -0.7987 0.01278 0.00754 -0.0032 1.0000 0.0069
-7.000 -0.7719 0.01228 0.00697 -0.0030 1.0000 0.0072
-6.750 -0.7450 0.01183 0.00642 -0.0029 1.0000 0.0074
-6.500 -0.7182 0.01115 0.00564 -0.0028 1.0000 0.0080
-6.250 -0.6911 0.01068 0.00513 -0.0026 1.0000 0.0086
-6.000 -0.6638 0.01032 0.00474 -0.0025 1.0000 0.0093
-5.750 -0.6364 0.00998 0.00436 -0.0024 1.0000 0.0100
-5.500 -0.6089 0.00967 0.00400 -0.0023 1.0000 0.0106
-5.250 -0.5813 0.00938 0.00367 -0.0022 1.0000 0.0114
-5.000 -0.5537 0.00901 0.00329 -0.0021 1.0000 0.0131
-4.750 -0.5260 0.00874 0.00300 -0.0020 1.0000 0.0144
-4.500 -0.4982 0.00851 0.00275 -0.0019 1.0000 0.0157
-4.250 -0.4703 0.00825 0.00247 -0.0019 1.0000 0.0178
-4.000 -0.4424 0.00801 0.00224 -0.0018 1.0000 0.0212
-3.750 -0.4145 0.00781 0.00204 -0.0017 1.0000 0.0243
-3.500 -0.3865 0.00758 0.00185 -0.0017 1.0000 0.0300
-3.250 -0.3585 0.00739 0.00167 -0.0016 1.0000 0.0366
-3.000 -0.3305 0.00717 0.00151 -0.0015 1.0000 0.0474
-2.750 -0.3025 0.00697 0.00137 -0.0015 1.0000 0.0600
-2.500 -0.2744 0.00676 0.00124 -0.0015 1.0000 0.0781
-2.250 -0.2464 0.00655 0.00112 -0.0015 1.0000 0.0997
-2.000 -0.2183 0.00633 0.00101 -0.0014 1.0000 0.1262
-1.750 -0.1902 0.00611 0.00093 -0.0014 1.0000 0.1595
-1.500 -0.1580 0.00592 0.00087 -0.0024 0.9501 0.2006
-1.250 -0.1366 0.00608 0.00083 -0.0005 0.8428 0.2319
-1.000 -0.1111 0.00628 0.00077 0.0001 0.7316 0.2662
-0.750 -0.0838 0.00651 0.00073 0.0002 0.6152 0.2999
-0.500 -0.0560 0.00669 0.00071 0.0001 0.5180 0.3335
-0.250 -0.0280 0.00675 0.00069 0.0001 0.4613 0.3684
0.000 0.0001 0.00676 0.00069 0.0000 0.4110 0.4111
0.250 0.0281 0.00675 0.00069 -0.0001 0.3674 0.4607
0.500 0.0562 0.00668 0.00071 -0.0002 0.3330 0.5206
0.750 0.0840 0.00651 0.00073 -0.0002 0.2998 0.6167
1.000 0.1113 0.00628 0.00077 -0.0002 0.2664 0.7307
1.250 0.1368 0.00608 0.00083 0.0005 0.2318 0.8427
1.500 0.1582 0.00592 0.00087 0.0024 0.2005 0.9500
1.750 0.1904 0.00611 0.00093 0.0014 0.1591 1.0000
2.000 0.2185 0.00633 0.00101 0.0014 0.1275 1.0000
2.250 0.2466 0.00655 0.00112 0.0015 0.0996 1.0000
2.500 0.2746 0.00676 0.00124 0.0015 0.0783 1.0000
2.750 0.3027 0.00697 0.00137 0.0015 0.0601 1.0000
3.000 0.3307 0.00718 0.00152 0.0015 0.0471 1.0000
3.250 0.3587 0.00739 0.00167 0.0016 0.0366 1.0000
3.500 0.3867 0.00758 0.00185 0.0016 0.0299 1.0000
3.750 0.4147 0.00781 0.00204 0.0017 0.0243 1.0000
4.000 0.4426 0.00801 0.00225 0.0018 0.0213 1.0000
4.250 0.4705 0.00825 0.00247 0.0018 0.0178 1.0000
4.500 0.4984 0.00851 0.00275 0.0019 0.0157 1.0000
4.750 0.5262 0.00875 0.00301 0.0020 0.0144 1.0000
5.000 0.5539 0.00902 0.00329 0.0021 0.0130 1.0000
5.250 0.5815 0.00939 0.00368 0.0022 0.0113 1.0000
5.500 0.6091 0.00968 0.00400 0.0023 0.0106 1.0000
5.750 0.6366 0.00999 0.00436 0.0024 0.0099 1.0000
6.000 0.6641 0.01032 0.00474 0.0025 0.0093 1.0000
6.250 0.6914 0.01069 0.00513 0.0026 0.0086 1.0000
6.500 0.7185 0.01115 0.00564 0.0027 0.0080 1.0000
6.750 0.7452 0.01184 0.00643 0.0029 0.0074 1.0000
7.000 0.7722 0.01229 0.00697 0.0030 0.0072 1.0000
7.250 0.7989 0.01280 0.00757 0.0032 0.0069 1.0000
7.500 0.8256 0.01329 0.00814 0.0033 0.0066 1.0000
7.750 0.8522 0.01376 0.00867 0.0035 0.0061 1.0000
8.000 0.8785 0.01430 0.00929 0.0036 0.0058 1.0000
8.250 0.9046 0.01489 0.00997 0.0038 0.0056 1.0000
8.500 0.9303 0.01561 0.01079 0.0039 0.0053 1.0000
8.750 0.9551 0.01668 0.01202 0.0041 0.0050 1.0000
9.000 0.9786 0.01818 0.01375 0.0043 0.0048 1.0000
9.250 1.0030 0.01919 0.01493 0.0045 0.0047 1.0000
9.500 1.0267 0.02038 0.01630 0.0047 0.0046 1.0000
9.750 1.0496 0.02174 0.01787 0.0049 0.0045 1.0000
10.000 1.0715 0.02332 0.01970 0.0051 0.0044 1.0000
10.250 1.0921 0.02520 0.02182 0.0052 0.0043 1.0000
10.500 1.1108 0.02749 0.02439 0.0052 0.0042 1.0000
10.750 1.1269 0.03032 0.02754 0.0050 0.0041 1.0000
11.000 1.1386 0.03412 0.03170 0.0044 0.0040 1.0000
11.250 1.1394 0.04065 0.03868 0.0021 0.0039 1.0000
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Polar data table (+)
Polar graphs
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