HT12 (ht12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT12 (ht12-il) Reynolds number: 1,000,000 Max Cl/Cd: 58.34 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht12-il-1000000.txt Download as CSV file: xf-ht12-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7997 0.16223 0.16062 0.0711 1.0000 0.0085
-12.250 -0.7948 0.15850 0.15689 0.0696 1.0000 0.0088
-8.750 -0.9061 0.03752 0.03531 -0.0021 1.0000 0.0073
-8.500 -0.8944 0.03199 0.02929 -0.0037 1.0000 0.0074
-8.250 -0.8853 0.02474 0.02123 -0.0045 1.0000 0.0076
-8.000 -0.8686 0.02000 0.01589 -0.0044 1.0000 0.0079
-7.750 -0.8455 0.01803 0.01366 -0.0042 1.0000 0.0082
-7.500 -0.8205 0.01687 0.01236 -0.0041 1.0000 0.0085
-7.250 -0.7948 0.01594 0.01129 -0.0039 1.0000 0.0089
-7.000 -0.7686 0.01521 0.01046 -0.0037 1.0000 0.0094
-6.750 -0.7421 0.01457 0.00972 -0.0035 1.0000 0.0101
-6.500 -0.7155 0.01390 0.00893 -0.0033 1.0000 0.0106
-6.250 -0.6885 0.01338 0.00833 -0.0031 1.0000 0.0110
-6.000 -0.6631 0.01161 0.00632 -0.0028 1.0000 0.0119
-5.750 -0.6362 0.01090 0.00554 -0.0027 1.0000 0.0128
-5.500 -0.6089 0.01047 0.00507 -0.0026 1.0000 0.0138
-5.250 -0.5814 0.01007 0.00462 -0.0024 1.0000 0.0150
-5.000 -0.5537 0.00984 0.00437 -0.0023 1.0000 0.0159
-4.750 -0.5263 0.00906 0.00348 -0.0022 1.0000 0.0182
-4.500 -0.4985 0.00872 0.00313 -0.0021 1.0000 0.0205
-4.250 -0.4706 0.00847 0.00285 -0.0020 1.0000 0.0226
-4.000 -0.4427 0.00805 0.00240 -0.0019 1.0000 0.0273
-3.750 -0.4148 0.00782 0.00218 -0.0018 1.0000 0.0319
-3.500 -0.3868 0.00750 0.00189 -0.0017 1.0000 0.0421
-3.250 -0.3588 0.00723 0.00167 -0.0017 1.0000 0.0568
-3.000 -0.3308 0.00694 0.00149 -0.0017 1.0000 0.0812
-2.750 -0.3029 0.00666 0.00134 -0.0017 1.0000 0.1106
-2.500 -0.2749 0.00636 0.00120 -0.0017 1.0000 0.1497
-2.250 -0.2469 0.00607 0.00107 -0.0017 1.0000 0.1956
-2.000 -0.2189 0.00581 0.00098 -0.0017 1.0000 0.2412
-1.750 -0.1909 0.00558 0.00091 -0.0017 1.0000 0.2859
-1.500 -0.1628 0.00536 0.00086 -0.0017 1.0000 0.3312
-1.250 -0.1348 0.00515 0.00081 -0.0017 1.0000 0.3761
-1.000 -0.1068 0.00493 0.00077 -0.0017 1.0000 0.4297
-0.750 -0.0789 0.00467 0.00074 -0.0017 1.0000 0.4917
-0.500 -0.0514 0.00429 0.00072 -0.0017 1.0000 0.5938
-0.250 -0.0251 0.00375 0.00072 -0.0013 1.0000 0.7452
0.000 0.0001 0.00338 0.00080 0.0000 0.9090 0.9093
0.250 0.0252 0.00376 0.00072 0.0013 0.7429 1.0000
0.500 0.0515 0.00429 0.00072 0.0017 0.5925 1.0000
0.750 0.0791 0.00468 0.00074 0.0017 0.4914 1.0000
1.000 0.1070 0.00493 0.00077 0.0017 0.4294 1.0000
1.250 0.1350 0.00515 0.00081 0.0017 0.3760 1.0000
1.500 0.1630 0.00536 0.00086 0.0017 0.3309 1.0000
1.750 0.1911 0.00558 0.00092 0.0017 0.2856 1.0000
2.000 0.2191 0.00580 0.00099 0.0017 0.2422 1.0000
2.250 0.2471 0.00607 0.00107 0.0017 0.1953 1.0000
2.500 0.2751 0.00636 0.00120 0.0017 0.1498 1.0000
2.750 0.3030 0.00666 0.00134 0.0017 0.1104 1.0000
3.000 0.3310 0.00694 0.00150 0.0017 0.0809 1.0000
3.250 0.3590 0.00723 0.00167 0.0017 0.0570 1.0000
3.500 0.3870 0.00750 0.00190 0.0017 0.0420 1.0000
3.750 0.4150 0.00783 0.00218 0.0018 0.0319 1.0000
4.000 0.4429 0.00805 0.00240 0.0019 0.0273 1.0000
4.250 0.4708 0.00847 0.00284 0.0020 0.0225 1.0000
4.500 0.4987 0.00872 0.00313 0.0021 0.0205 1.0000
4.750 0.5265 0.00907 0.00349 0.0022 0.0182 1.0000
5.000 0.5539 0.00985 0.00438 0.0023 0.0159 1.0000
5.250 0.5816 0.01008 0.00463 0.0024 0.0149 1.0000
5.500 0.6091 0.01048 0.00507 0.0025 0.0138 1.0000
5.750 0.6365 0.01091 0.00556 0.0027 0.0128 1.0000
6.000 0.6634 0.01161 0.00631 0.0028 0.0118 1.0000
6.250 0.6888 0.01334 0.00828 0.0031 0.0110 1.0000
6.500 0.7158 0.01388 0.00891 0.0033 0.0106 1.0000
6.750 0.7424 0.01460 0.00975 0.0035 0.0101 1.0000
7.000 0.7689 0.01525 0.01051 0.0037 0.0094 1.0000
7.250 0.7951 0.01599 0.01136 0.0038 0.0089 1.0000
7.500 0.8207 0.01692 0.01241 0.0040 0.0085 1.0000
7.750 0.8458 0.01801 0.01364 0.0042 0.0082 1.0000
8.000 0.8691 0.01993 0.01581 0.0044 0.0079 1.0000
8.250 0.8865 0.02439 0.02084 0.0045 0.0076 1.0000
8.500 0.8922 0.03299 0.03036 0.0034 0.0074 1.0000
8.750 0.9049 0.03816 0.03598 0.0018 0.0073 1.0000
13.250 0.6212 0.15622 0.15469 -0.0490 0.0097 1.0000
13.500 0.6207 0.15866 0.15714 -0.0497 0.0092 1.0000
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Polar data table (+)
Polar graphs
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