HT08 (ht08-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT08 (ht08-il) Reynolds number: 500,000 Max Cl/Cd: 48.86 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht08-il-500000-n5.txt Download as CSV file: xf-ht08-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.8048 0.09437 0.09223 0.0363 1.0000 0.0068
-9.250 -0.8161 0.08705 0.08495 0.0316 1.0000 0.0068
-8.750 -0.9114 0.03370 0.03040 -0.0044 1.0000 0.0064
-8.500 -0.9010 0.02757 0.02353 -0.0047 1.0000 0.0067
-8.250 -0.8811 0.02477 0.02027 -0.0045 1.0000 0.0070
-8.000 -0.8591 0.02270 0.01782 -0.0043 1.0000 0.0073
-7.750 -0.8374 0.02039 0.01517 -0.0041 1.0000 0.0077
-7.500 -0.8129 0.01920 0.01382 -0.0039 1.0000 0.0081
-7.250 -0.7878 0.01814 0.01258 -0.0037 1.0000 0.0084
-7.000 -0.7624 0.01710 0.01137 -0.0035 1.0000 0.0089
-6.750 -0.7367 0.01610 0.01017 -0.0032 1.0000 0.0094
-6.500 -0.7107 0.01518 0.00909 -0.0030 1.0000 0.0100
-6.250 -0.6844 0.01441 0.00817 -0.0028 1.0000 0.0105
-6.000 -0.6582 0.01351 0.00715 -0.0026 1.0000 0.0112
-5.750 -0.6316 0.01293 0.00653 -0.0025 1.0000 0.0124
-5.500 -0.6046 0.01245 0.00597 -0.0023 1.0000 0.0135
-5.250 -0.5775 0.01192 0.00536 -0.0022 1.0000 0.0145
-5.000 -0.5502 0.01147 0.00483 -0.0021 1.0000 0.0155
-4.750 -0.5231 0.01086 0.00417 -0.0019 1.0000 0.0174
-4.500 -0.4956 0.01051 0.00381 -0.0019 1.0000 0.0199
-4.250 -0.4680 0.01020 0.00344 -0.0018 1.0000 0.0222
-4.000 -0.4404 0.00979 0.00302 -0.0017 1.0000 0.0260
-3.750 -0.4128 0.00951 0.00273 -0.0016 1.0000 0.0308
-3.500 -0.3851 0.00920 0.00245 -0.0016 1.0000 0.0387
-3.250 -0.3573 0.00893 0.00220 -0.0015 1.0000 0.0484
-3.000 -0.3296 0.00866 0.00199 -0.0015 1.0000 0.0635
-2.750 -0.3019 0.00838 0.00180 -0.0015 1.0000 0.0846
-2.500 -0.2741 0.00811 0.00164 -0.0015 1.0000 0.1118
-2.250 -0.2465 0.00782 0.00148 -0.0015 1.0000 0.1472
-2.000 -0.2188 0.00753 0.00136 -0.0015 1.0000 0.1886
-1.750 -0.1911 0.00723 0.00125 -0.0015 1.0000 0.2387
-1.500 -0.1635 0.00693 0.00117 -0.0015 1.0000 0.2955
-1.250 -0.1360 0.00663 0.00109 -0.0015 1.0000 0.3599
-1.000 -0.1087 0.00628 0.00104 -0.0015 1.0000 0.4359
-0.750 -0.0816 0.00589 0.00100 -0.0014 1.0000 0.5296
-0.500 -0.0553 0.00546 0.00099 -0.0011 1.0000 0.6385
-0.250 -0.0213 0.00504 0.00103 -0.0024 0.9536 0.7610
0.000 0.0001 0.00490 0.00107 0.0000 0.8630 0.8632
0.250 0.0215 0.00505 0.00103 0.0023 0.7602 0.9541
0.500 0.0554 0.00546 0.00099 0.0011 0.6385 1.0000
0.750 0.0818 0.00589 0.00100 0.0014 0.5298 1.0000
1.000 0.1088 0.00629 0.00104 0.0015 0.4356 1.0000
1.250 0.1362 0.00663 0.00109 0.0015 0.3598 1.0000
1.500 0.1637 0.00693 0.00117 0.0015 0.2957 1.0000
1.750 0.1913 0.00724 0.00125 0.0015 0.2384 1.0000
2.000 0.2189 0.00753 0.00136 0.0015 0.1886 1.0000
2.250 0.2466 0.00782 0.00148 0.0015 0.1470 1.0000
2.500 0.2743 0.00811 0.00164 0.0015 0.1115 1.0000
2.750 0.3020 0.00838 0.00180 0.0015 0.0846 1.0000
3.000 0.3297 0.00866 0.00199 0.0015 0.0637 1.0000
3.250 0.3575 0.00893 0.00220 0.0015 0.0483 1.0000
3.500 0.3852 0.00920 0.00245 0.0016 0.0386 1.0000
3.750 0.4129 0.00951 0.00273 0.0016 0.0307 1.0000
4.000 0.4406 0.00980 0.00302 0.0017 0.0260 1.0000
4.250 0.4682 0.01020 0.00344 0.0018 0.0222 1.0000
4.500 0.4958 0.01051 0.00381 0.0019 0.0199 1.0000
4.750 0.5232 0.01086 0.00417 0.0019 0.0174 1.0000
5.000 0.5504 0.01147 0.00484 0.0021 0.0155 1.0000
5.250 0.5777 0.01192 0.00537 0.0022 0.0145 1.0000
5.500 0.6048 0.01245 0.00598 0.0023 0.0134 1.0000
5.750 0.6318 0.01293 0.00653 0.0025 0.0124 1.0000
6.000 0.6584 0.01351 0.00715 0.0026 0.0112 1.0000
6.250 0.6846 0.01442 0.00818 0.0027 0.0105 1.0000
6.500 0.7110 0.01519 0.00910 0.0030 0.0100 1.0000
6.750 0.7370 0.01611 0.01019 0.0032 0.0094 1.0000
7.000 0.7626 0.01712 0.01139 0.0034 0.0089 1.0000
7.250 0.7881 0.01816 0.01261 0.0037 0.0084 1.0000
7.500 0.8131 0.01923 0.01384 0.0039 0.0081 1.0000
7.750 0.8377 0.02039 0.01518 0.0040 0.0077 1.0000
8.000 0.8593 0.02276 0.01789 0.0043 0.0072 1.0000
8.250 0.8815 0.02476 0.02024 0.0045 0.0070 1.0000
8.500 0.9014 0.02755 0.02351 0.0047 0.0066 1.0000
8.750 0.9118 0.03372 0.03042 0.0043 0.0064 1.0000
9.250 0.8163 0.08725 0.08515 -0.0319 0.0068 1.0000
9.500 0.8052 0.09454 0.09240 -0.0366 0.0068 1.0000
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Polar data table (+)
Polar graphs
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