HT12 (ht12-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT12 (ht12-il) Reynolds number: 500,000 Max Cl/Cd: 50.15 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht12-il-500000-n5.txt Download as CSV file: xf-ht12-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7986 0.11408 0.11187 0.0513 1.0000 0.0068
-10.000 -0.8039 0.10787 0.10568 0.0484 1.0000 0.0069
-9.000 -0.9351 0.03589 0.03285 -0.0035 1.0000 0.0064
-8.750 -0.9263 0.02909 0.02530 -0.0048 1.0000 0.0067
-8.500 -0.9082 0.02554 0.02125 -0.0050 1.0000 0.0069
-8.250 -0.8861 0.02349 0.01882 -0.0049 1.0000 0.0073
-8.000 -0.8633 0.02157 0.01656 -0.0047 1.0000 0.0076
-7.750 -0.8404 0.01960 0.01431 -0.0046 1.0000 0.0081
-7.500 -0.8154 0.01850 0.01305 -0.0045 1.0000 0.0084
-7.250 -0.7900 0.01751 0.01191 -0.0043 1.0000 0.0088
-7.000 -0.7643 0.01655 0.01079 -0.0041 1.0000 0.0093
-6.750 -0.7383 0.01563 0.00969 -0.0039 1.0000 0.0099
-6.500 -0.7121 0.01478 0.00869 -0.0037 1.0000 0.0104
-6.250 -0.6855 0.01407 0.00784 -0.0035 1.0000 0.0109
-6.000 -0.6592 0.01316 0.00683 -0.0033 1.0000 0.0119
-5.750 -0.6323 0.01265 0.00629 -0.0032 1.0000 0.0130
-5.500 -0.6052 0.01218 0.00573 -0.0031 1.0000 0.0141
-5.250 -0.5780 0.01167 0.00514 -0.0029 1.0000 0.0152
-5.000 -0.5506 0.01125 0.00465 -0.0028 1.0000 0.0161
-4.750 -0.5233 0.01065 0.00401 -0.0026 1.0000 0.0185
-4.500 -0.4957 0.01033 0.00365 -0.0026 1.0000 0.0212
-4.250 -0.4680 0.01002 0.00329 -0.0024 1.0000 0.0234
-4.000 -0.4404 0.00961 0.00289 -0.0023 1.0000 0.0282
-3.750 -0.4126 0.00935 0.00261 -0.0022 1.0000 0.0329
-3.500 -0.3848 0.00904 0.00234 -0.0022 1.0000 0.0423
-3.250 -0.3570 0.00876 0.00209 -0.0021 1.0000 0.0539
-3.000 -0.3293 0.00848 0.00188 -0.0020 1.0000 0.0714
-2.750 -0.3015 0.00820 0.00170 -0.0020 1.0000 0.0941
-2.500 -0.2737 0.00791 0.00153 -0.0020 1.0000 0.1237
-2.250 -0.2459 0.00761 0.00138 -0.0020 1.0000 0.1616
-2.000 -0.2181 0.00732 0.00126 -0.0020 1.0000 0.2051
-1.750 -0.1903 0.00707 0.00117 -0.0019 1.0000 0.2477
-1.500 -0.1625 0.00684 0.00110 -0.0019 1.0000 0.2898
-1.250 -0.1346 0.00663 0.00104 -0.0019 1.0000 0.3307
-1.000 -0.1068 0.00642 0.00099 -0.0018 1.0000 0.3728
-0.750 -0.0790 0.00620 0.00096 -0.0018 1.0000 0.4193
-0.500 -0.0464 0.00596 0.00096 -0.0028 0.9608 0.4816
-0.250 -0.0218 0.00596 0.00096 -0.0015 0.8276 0.5625
0.000 0.0001 0.00601 0.00094 0.0000 0.6855 0.6873
0.250 0.0219 0.00595 0.00096 0.0015 0.5630 0.8286
0.500 0.0466 0.00596 0.00096 0.0028 0.4819 0.9606
0.750 0.0792 0.00620 0.00096 0.0018 0.4187 1.0000
1.000 0.1070 0.00642 0.00099 0.0018 0.3722 1.0000
1.250 0.1348 0.00663 0.00104 0.0019 0.3304 1.0000
1.500 0.1626 0.00684 0.00110 0.0019 0.2895 1.0000
2.000 0.2183 0.00733 0.00126 0.0020 0.2043 1.0000
2.250 0.2461 0.00761 0.00138 0.0020 0.1612 1.0000
2.500 0.2738 0.00790 0.00153 0.0020 0.1241 1.0000
2.750 0.3016 0.00820 0.00170 0.0020 0.0940 1.0000
3.000 0.3294 0.00848 0.00188 0.0020 0.0714 1.0000
3.250 0.3572 0.00876 0.00209 0.0021 0.0538 1.0000
3.500 0.3850 0.00904 0.00234 0.0022 0.0422 1.0000
3.750 0.4128 0.00935 0.00261 0.0022 0.0328 1.0000
4.000 0.4406 0.00961 0.00290 0.0023 0.0281 1.0000
4.250 0.4682 0.01001 0.00329 0.0024 0.0234 1.0000
4.500 0.4959 0.01033 0.00365 0.0025 0.0212 1.0000
4.750 0.5235 0.01066 0.00402 0.0026 0.0185 1.0000
5.000 0.5508 0.01125 0.00466 0.0027 0.0161 1.0000
5.250 0.5782 0.01168 0.00515 0.0029 0.0152 1.0000
5.500 0.6054 0.01218 0.00574 0.0030 0.0141 1.0000
5.750 0.6325 0.01267 0.00630 0.0032 0.0130 1.0000
6.000 0.6595 0.01315 0.00682 0.0033 0.0118 1.0000
6.250 0.6858 0.01407 0.00784 0.0034 0.0109 1.0000
6.500 0.7123 0.01478 0.00869 0.0036 0.0104 1.0000
6.750 0.7386 0.01564 0.00970 0.0039 0.0098 1.0000
7.000 0.7646 0.01657 0.01081 0.0041 0.0093 1.0000
7.250 0.7903 0.01753 0.01194 0.0043 0.0088 1.0000
7.500 0.8157 0.01853 0.01309 0.0044 0.0084 1.0000
7.750 0.8407 0.01961 0.01433 0.0046 0.0081 1.0000
8.000 0.8639 0.02142 0.01640 0.0047 0.0076 1.0000
8.250 0.8863 0.02355 0.01889 0.0048 0.0073 1.0000
8.500 0.9084 0.02564 0.02135 0.0049 0.0069 1.0000
8.750 0.9266 0.02911 0.02533 0.0047 0.0067 1.0000
9.000 0.9354 0.03593 0.03290 0.0034 0.0064 1.0000
9.500 0.8225 0.09413 0.09201 -0.0414 0.0070 1.0000
9.750 0.8120 0.10138 0.09923 -0.0454 0.0070 1.0000
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Polar data table (+)
Polar graphs
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