HT08 (ht08-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT08 (ht08-il) Reynolds number: 500,000 Max Cl/Cd: 44.07 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht08-il-500000.txt Download as CSV file: xf-ht08-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HT08
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.7526 0.10138 0.09921 0.0385 1.0000 0.0193
-8.750 -0.7534 0.09645 0.09431 0.0355 1.0000 0.0200
-8.500 -0.7552 0.09111 0.08899 0.0317 1.0000 0.0207
-7.000 -0.7423 0.03206 0.02811 -0.0050 1.0000 0.0161
-6.750 -0.7215 0.02875 0.02441 -0.0048 1.0000 0.0159
-6.500 -0.6989 0.02593 0.02125 -0.0045 1.0000 0.0156
-6.250 -0.6774 0.02173 0.01648 -0.0041 1.0000 0.0158
-6.000 -0.6549 0.01746 0.01166 -0.0037 1.0000 0.0164
-5.750 -0.6294 0.01580 0.00984 -0.0034 1.0000 0.0174
-5.500 -0.6029 0.01493 0.00886 -0.0032 1.0000 0.0187
-5.250 -0.5759 0.01429 0.00814 -0.0030 1.0000 0.0205
-5.000 -0.5489 0.01344 0.00717 -0.0028 1.0000 0.0219
-4.750 -0.5221 0.01244 0.00604 -0.0025 1.0000 0.0231
-4.500 -0.4957 0.01125 0.00478 -0.0022 1.0000 0.0263
-4.250 -0.4682 0.01085 0.00434 -0.0021 1.0000 0.0299
-4.000 -0.4407 0.01025 0.00366 -0.0019 1.0000 0.0336
-3.750 -0.4132 0.00971 0.00312 -0.0018 1.0000 0.0405
-3.500 -0.3855 0.00925 0.00267 -0.0017 1.0000 0.0516
-3.250 -0.3578 0.00881 0.00229 -0.0017 1.0000 0.0713
-3.000 -0.3302 0.00838 0.00202 -0.0017 1.0000 0.1080
-2.750 -0.3027 0.00795 0.00181 -0.0017 1.0000 0.1593
-2.500 -0.2752 0.00754 0.00164 -0.0017 1.0000 0.2206
-2.250 -0.2479 0.00711 0.00148 -0.0018 1.0000 0.2959
-2.000 -0.2206 0.00666 0.00136 -0.0018 1.0000 0.3839
-1.750 -0.1938 0.00613 0.00126 -0.0018 1.0000 0.4979
-1.500 -0.1680 0.00551 0.00119 -0.0014 1.0000 0.6428
-1.250 -0.1452 0.00490 0.00116 0.0000 1.0000 0.7948
-0.750 -0.0806 0.00446 0.00114 -0.0008 1.0000 1.0000
-0.500 -0.0538 0.00444 0.00110 -0.0005 1.0000 1.0000
-0.250 -0.0269 0.00443 0.00107 -0.0003 1.0000 1.0000
0.000 0.0001 0.00443 0.00106 0.0000 1.0000 1.0000
0.250 0.0270 0.00443 0.00107 0.0003 1.0000 1.0000
0.500 0.0539 0.00444 0.00110 0.0005 1.0000 1.0000
0.750 0.0808 0.00446 0.00114 0.0008 1.0000 1.0000
1.000 0.1258 0.00452 0.00118 -0.0027 0.9267 1.0000
1.250 0.1453 0.00490 0.00117 0.0001 0.7945 1.0000
1.500 0.1682 0.00551 0.00119 0.0014 0.6430 1.0000
1.750 0.1939 0.00613 0.00126 0.0018 0.4972 1.0000
2.000 0.2207 0.00666 0.00136 0.0018 0.3839 1.0000
2.250 0.2480 0.00711 0.00148 0.0018 0.2955 1.0000
2.750 0.3029 0.00795 0.00181 0.0017 0.1591 1.0000
3.000 0.3304 0.00838 0.00202 0.0017 0.1081 1.0000
3.250 0.3579 0.00882 0.00229 0.0016 0.0710 1.0000
3.500 0.3856 0.00925 0.00268 0.0017 0.0515 1.0000
3.750 0.4133 0.00971 0.00312 0.0018 0.0405 1.0000
4.000 0.4409 0.01025 0.00366 0.0019 0.0335 1.0000
4.250 0.4683 0.01086 0.00434 0.0021 0.0299 1.0000
4.500 0.4958 0.01125 0.00477 0.0022 0.0262 1.0000
4.750 0.5222 0.01246 0.00606 0.0024 0.0231 1.0000
5.000 0.5491 0.01345 0.00718 0.0027 0.0219 1.0000
5.250 0.5761 0.01432 0.00817 0.0030 0.0205 1.0000
5.500 0.6031 0.01496 0.00890 0.0032 0.0187 1.0000
5.750 0.6296 0.01582 0.00986 0.0034 0.0174 1.0000
6.000 0.6552 0.01743 0.01164 0.0037 0.0165 1.0000
6.250 0.6777 0.02164 0.01638 0.0041 0.0158 1.0000
6.500 0.6988 0.02619 0.02152 0.0045 0.0157 1.0000
6.750 0.7217 0.02876 0.02442 0.0048 0.0159 1.0000
7.000 0.7420 0.03231 0.02838 0.0049 0.0160 1.0000
7.250 0.7591 0.03692 0.03345 0.0048 0.0162 1.0000
8.250 0.7582 0.08527 0.08318 -0.0264 0.0213 1.0000
8.500 0.7557 0.09123 0.08911 -0.0319 0.0206 1.0000
8.750 0.7540 0.09654 0.09440 -0.0357 0.0199 1.0000
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Polar data table (+)
Polar graphs
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