HT08 (ht08-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT08 (ht08-il) Reynolds number: 1,000,000 Max Cl/Cd: 63.45 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht08-il-1000000-n5.txt Download as CSV file: xf-ht08-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7973 0.15645 0.15483 0.0647 1.0000 0.0039
-12.250 -0.7958 0.15146 0.14985 0.0628 1.0000 0.0038
-10.750 -1.1096 0.03377 0.03131 -0.0048 1.0000 0.0039
-10.500 -1.0994 0.02966 0.02679 -0.0050 1.0000 0.0040
-10.250 -1.0837 0.02676 0.02356 -0.0048 1.0000 0.0042
-10.000 -1.0651 0.02449 0.02100 -0.0046 1.0000 0.0043
-9.750 -1.0445 0.02267 0.01890 -0.0043 1.0000 0.0044
-9.500 -1.0224 0.02118 0.01718 -0.0040 1.0000 0.0045
-9.250 -0.9994 0.01987 0.01567 -0.0038 1.0000 0.0045
-9.000 -0.9755 0.01878 0.01440 -0.0035 1.0000 0.0046
-8.750 -0.9526 0.01717 0.01254 -0.0032 1.0000 0.0048
-8.500 -0.9283 0.01599 0.01119 -0.0030 1.0000 0.0051
-8.250 -0.9029 0.01523 0.01032 -0.0028 1.0000 0.0053
-8.000 -0.8769 0.01462 0.00961 -0.0027 1.0000 0.0056
-7.750 -0.8507 0.01407 0.00899 -0.0025 1.0000 0.0059
-7.500 -0.8243 0.01357 0.00841 -0.0024 1.0000 0.0062
-7.250 -0.7978 0.01306 0.00782 -0.0022 1.0000 0.0066
-7.000 -0.7712 0.01253 0.00720 -0.0021 1.0000 0.0069
-6.750 -0.7443 0.01206 0.00665 -0.0020 1.0000 0.0071
-6.500 -0.7177 0.01140 0.00587 -0.0018 1.0000 0.0076
-6.250 -0.6908 0.01088 0.00530 -0.0017 1.0000 0.0082
-6.000 -0.6635 0.01050 0.00489 -0.0016 1.0000 0.0088
-5.750 -0.6362 0.01016 0.00452 -0.0016 1.0000 0.0095
-5.500 -0.6087 0.00984 0.00415 -0.0015 1.0000 0.0101
-5.250 -0.5811 0.00958 0.00385 -0.0014 1.0000 0.0107
-5.000 -0.5536 0.00917 0.00341 -0.0013 1.0000 0.0124
-4.750 -0.5260 0.00889 0.00312 -0.0013 1.0000 0.0137
-4.500 -0.4982 0.00865 0.00286 -0.0012 1.0000 0.0150
-4.250 -0.4703 0.00841 0.00259 -0.0012 1.0000 0.0163
-4.000 -0.4425 0.00815 0.00235 -0.0011 1.0000 0.0198
-3.750 -0.4146 0.00795 0.00215 -0.0011 1.0000 0.0224
-3.500 -0.3866 0.00772 0.00195 -0.0011 1.0000 0.0277
-3.250 -0.3587 0.00754 0.00177 -0.0010 1.0000 0.0327
-3.000 -0.3307 0.00733 0.00161 -0.0010 1.0000 0.0425
-2.750 -0.3027 0.00713 0.00147 -0.0010 1.0000 0.0541
-2.500 -0.2747 0.00693 0.00134 -0.0010 1.0000 0.0696
-2.250 -0.2467 0.00671 0.00121 -0.0010 1.0000 0.0921
-2.000 -0.2186 0.00650 0.00111 -0.0011 1.0000 0.1179
-1.750 -0.1906 0.00629 0.00102 -0.0011 1.0000 0.1477
-1.500 -0.1627 0.00607 0.00095 -0.0011 1.0000 0.1847
-1.250 -0.1291 0.00589 0.00090 -0.0024 0.9582 0.2293
-1.000 -0.1063 0.00593 0.00088 -0.0009 0.8718 0.2715
-0.750 -0.0817 0.00605 0.00083 0.0000 0.7777 0.3187
-0.500 -0.0550 0.00615 0.00079 0.0002 0.6863 0.3740
-0.250 -0.0275 0.00620 0.00076 0.0001 0.5968 0.4402
0.000 0.0001 0.00621 0.00076 0.0000 0.5152 0.5155
0.250 0.0277 0.00619 0.00076 -0.0001 0.4412 0.5975
0.500 0.0551 0.00615 0.00079 -0.0002 0.3735 0.6868
0.750 0.0819 0.00605 0.00083 0.0000 0.3191 0.7779
1.000 0.1065 0.00593 0.00088 0.0009 0.2713 0.8720
1.250 0.1292 0.00589 0.00090 0.0024 0.2299 0.9580
1.500 0.1628 0.00607 0.00095 0.0011 0.1844 1.0000
1.750 0.1908 0.00630 0.00102 0.0011 0.1477 1.0000
2.000 0.2188 0.00651 0.00111 0.0010 0.1168 1.0000
2.250 0.2468 0.00671 0.00121 0.0010 0.0922 1.0000
2.500 0.2748 0.00693 0.00134 0.0010 0.0696 1.0000
2.750 0.3028 0.00713 0.00147 0.0010 0.0541 1.0000
3.000 0.3308 0.00733 0.00161 0.0010 0.0424 1.0000
3.250 0.3588 0.00754 0.00177 0.0010 0.0325 1.0000
3.500 0.3868 0.00773 0.00195 0.0011 0.0277 1.0000
3.750 0.4148 0.00795 0.00215 0.0011 0.0224 1.0000
4.000 0.4427 0.00815 0.00235 0.0011 0.0198 1.0000
4.250 0.4705 0.00841 0.00259 0.0012 0.0164 1.0000
4.500 0.4984 0.00865 0.00286 0.0012 0.0149 1.0000
4.750 0.5261 0.00889 0.00313 0.0013 0.0137 1.0000
5.000 0.5538 0.00918 0.00341 0.0013 0.0123 1.0000
5.250 0.5813 0.00959 0.00386 0.0014 0.0107 1.0000
5.500 0.6089 0.00984 0.00415 0.0015 0.0101 1.0000
5.750 0.6364 0.01016 0.00452 0.0015 0.0095 1.0000
6.000 0.6638 0.01051 0.00490 0.0016 0.0088 1.0000
6.250 0.6910 0.01089 0.00531 0.0017 0.0082 1.0000
6.500 0.7180 0.01140 0.00587 0.0018 0.0076 1.0000
6.750 0.7446 0.01207 0.00667 0.0019 0.0071 1.0000
7.000 0.7714 0.01256 0.00723 0.0021 0.0069 1.0000
7.250 0.7981 0.01307 0.00783 0.0022 0.0066 1.0000
7.500 0.8246 0.01357 0.00841 0.0023 0.0062 1.0000
7.750 0.8510 0.01407 0.00898 0.0025 0.0059 1.0000
8.000 0.8772 0.01463 0.00962 0.0026 0.0056 1.0000
8.250 0.9031 0.01525 0.01034 0.0028 0.0053 1.0000
8.500 0.9287 0.01599 0.01119 0.0029 0.0051 1.0000
8.750 0.9530 0.01716 0.01254 0.0032 0.0048 1.0000
9.000 0.9759 0.01875 0.01437 0.0035 0.0046 1.0000
9.250 0.9998 0.01985 0.01564 0.0037 0.0045 1.0000
9.500 1.0229 0.02113 0.01712 0.0040 0.0045 1.0000
9.750 1.0450 0.02264 0.01887 0.0042 0.0044 1.0000
10.000 1.0657 0.02445 0.02095 0.0045 0.0043 1.0000
10.250 1.0845 0.02668 0.02347 0.0047 0.0041 1.0000
10.500 1.1004 0.02953 0.02665 0.0049 0.0040 1.0000
10.750 1.1109 0.03357 0.03109 0.0047 0.0039 1.0000
12.250 0.7967 0.15166 0.15004 -0.0631 0.0038 1.0000
12.500 0.7982 0.15666 0.15504 -0.0650 0.0038 1.0000
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Polar data table (+)
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