HT05 (ht05-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT05 (ht05-il) Reynolds number: 1,000,000 Max Cl/Cd: 63.49 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht05-il-1000000-n5.txt Download as CSV file: xf-ht05-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HT05
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 -0.7797 0.15220 0.15055 0.0551 1.0000 0.0039
-12.250 -0.7793 0.14704 0.14539 0.0532 1.0000 0.0039
-11.250 -1.1296 0.03518 0.03282 -0.0115 1.0000 0.0039
-11.000 -1.1210 0.03137 0.02868 -0.0115 1.0000 0.0040
-10.750 -1.1074 0.02857 0.02560 -0.0111 1.0000 0.0041
-10.500 -1.0912 0.02625 0.02298 -0.0106 1.0000 0.0043
-10.250 -1.0729 0.02429 0.02077 -0.0101 1.0000 0.0044
-10.000 -1.0531 0.02261 0.01886 -0.0095 1.0000 0.0045
-9.750 -1.0320 0.02118 0.01722 -0.0090 1.0000 0.0046
-9.500 -1.0100 0.01990 0.01574 -0.0085 1.0000 0.0048
-9.250 -0.9871 0.01880 0.01445 -0.0080 1.0000 0.0049
-9.000 -0.9635 0.01786 0.01336 -0.0076 1.0000 0.0050
-8.750 -0.9394 0.01699 0.01234 -0.0072 1.0000 0.0050
-8.500 -0.9166 0.01562 0.01073 -0.0066 1.0000 0.0053
-8.250 -0.8921 0.01475 0.00974 -0.0062 1.0000 0.0057
-8.000 -0.8667 0.01415 0.00907 -0.0059 1.0000 0.0060
-7.750 -0.8410 0.01365 0.00850 -0.0056 1.0000 0.0063
-7.500 -0.8150 0.01321 0.00801 -0.0053 1.0000 0.0067
-7.250 -0.7889 0.01277 0.00749 -0.0051 1.0000 0.0072
-7.000 -0.7628 0.01231 0.00694 -0.0048 1.0000 0.0075
-6.750 -0.7365 0.01187 0.00642 -0.0045 1.0000 0.0078
-6.500 -0.7103 0.01139 0.00587 -0.0042 1.0000 0.0080
-6.250 -0.6843 0.01078 0.00517 -0.0038 1.0000 0.0089
-6.000 -0.6577 0.01040 0.00477 -0.0036 1.0000 0.0096
-5.750 -0.6310 0.01008 0.00441 -0.0033 1.0000 0.0104
-5.500 -0.6042 0.00978 0.00407 -0.0031 1.0000 0.0111
-5.250 -0.5773 0.00954 0.00380 -0.0028 1.0000 0.0118
-5.000 -0.5506 0.00917 0.00340 -0.0025 1.0000 0.0133
-4.750 -0.5238 0.00888 0.00311 -0.0022 1.0000 0.0149
-4.500 -0.4970 0.00865 0.00285 -0.0020 1.0000 0.0165
-4.250 -0.4701 0.00845 0.00263 -0.0017 1.0000 0.0176
-4.000 -0.4434 0.00819 0.00238 -0.0014 1.0000 0.0216
-3.750 -0.4166 0.00799 0.00220 -0.0010 0.9999 0.0250
-3.500 -0.3856 0.00777 0.00199 -0.0017 0.9951 0.0306
-3.250 -0.3551 0.00758 0.00182 -0.0022 0.9886 0.0362
-3.000 -0.3237 0.00737 0.00166 -0.0030 0.9780 0.0473
-2.750 -0.2944 0.00729 0.00152 -0.0030 0.9103 0.0601
-2.500 -0.2750 0.00805 0.00142 -0.0010 0.6481 0.0740
-2.250 -0.2476 0.00795 0.00134 -0.0009 0.6382 0.0949
-2.000 -0.2200 0.00786 0.00127 -0.0008 0.6331 0.1137
-1.750 -0.1923 0.00769 0.00120 -0.0007 0.6280 0.1406
-1.500 -0.1646 0.00755 0.00115 -0.0006 0.6225 0.1666
-1.250 -0.1368 0.00738 0.00108 -0.0005 0.6152 0.1959
-1.000 -0.1090 0.00721 0.00102 -0.0004 0.6062 0.2291
-0.750 -0.0812 0.00705 0.00097 -0.0004 0.5920 0.2615
-0.500 -0.0536 0.00688 0.00090 -0.0003 0.5653 0.3100
-0.250 -0.0265 0.00676 0.00083 -0.0001 0.5142 0.3719
0.000 0.0001 0.00672 0.00081 0.0000 0.4446 0.4460
0.250 0.0267 0.00677 0.00083 0.0001 0.3700 0.5141
0.500 0.0538 0.00688 0.00090 0.0003 0.3095 0.5653
0.750 0.0814 0.00705 0.00097 0.0003 0.2620 0.5923
1.000 0.1092 0.00721 0.00102 0.0004 0.2293 0.6061
1.250 0.1370 0.00738 0.00108 0.0005 0.1960 0.6152
1.500 0.1648 0.00755 0.00115 0.0006 0.1658 0.6227
1.750 0.1925 0.00769 0.00120 0.0007 0.1409 0.6279
2.000 0.2202 0.00786 0.00127 0.0008 0.1140 0.6331
2.250 0.2478 0.00795 0.00134 0.0009 0.0951 0.6382
2.500 0.2751 0.00805 0.00142 0.0010 0.0735 0.6483
2.750 0.2945 0.00729 0.00152 0.0030 0.0602 0.9110
3.000 0.3239 0.00737 0.00166 0.0030 0.0472 0.9780
3.250 0.3553 0.00758 0.00182 0.0022 0.0361 0.9887
3.500 0.3859 0.00777 0.00199 0.0017 0.0305 0.9952
3.750 0.4167 0.00799 0.00220 0.0010 0.0250 1.0000
4.000 0.4435 0.00819 0.00238 0.0013 0.0216 1.0000
4.250 0.4702 0.00845 0.00263 0.0017 0.0177 1.0000
4.500 0.4971 0.00865 0.00285 0.0019 0.0165 1.0000
4.750 0.5240 0.00889 0.00311 0.0022 0.0149 1.0000
5.000 0.5508 0.00918 0.00340 0.0025 0.0133 1.0000
5.250 0.5775 0.00954 0.00380 0.0028 0.0118 1.0000
5.500 0.6044 0.00978 0.00407 0.0030 0.0111 1.0000
5.750 0.6312 0.01008 0.00441 0.0033 0.0104 1.0000
6.000 0.6578 0.01041 0.00478 0.0036 0.0096 1.0000
6.250 0.6844 0.01078 0.00518 0.0038 0.0089 1.0000
6.500 0.7104 0.01143 0.00592 0.0042 0.0080 1.0000
6.750 0.7367 0.01187 0.00643 0.0045 0.0078 1.0000
7.000 0.7629 0.01231 0.00695 0.0048 0.0075 1.0000
7.250 0.7891 0.01276 0.00748 0.0051 0.0072 1.0000
7.500 0.8151 0.01320 0.00799 0.0053 0.0067 1.0000
7.750 0.8411 0.01365 0.00849 0.0056 0.0063 1.0000
8.000 0.8668 0.01415 0.00906 0.0059 0.0060 1.0000
8.250 0.8922 0.01476 0.00975 0.0062 0.0057 1.0000
8.500 0.9166 0.01566 0.01078 0.0066 0.0053 1.0000
8.750 0.9396 0.01698 0.01233 0.0072 0.0051 1.0000
9.000 0.9637 0.01783 0.01333 0.0076 0.0050 1.0000
9.250 0.9873 0.01880 0.01446 0.0080 0.0049 1.0000
9.500 1.0101 0.01991 0.01575 0.0085 0.0048 1.0000
9.750 1.0322 0.02117 0.01720 0.0090 0.0046 1.0000
10.000 1.0533 0.02261 0.01885 0.0095 0.0045 1.0000
10.250 1.0731 0.02429 0.02077 0.0101 0.0044 1.0000
10.500 1.0915 0.02621 0.02294 0.0106 0.0043 1.0000
10.750 1.1080 0.02848 0.02549 0.0111 0.0041 1.0000
11.000 1.1218 0.03122 0.02852 0.0114 0.0040 1.0000
11.250 1.1311 0.03488 0.03250 0.0115 0.0039 1.0000
11.500 1.1240 0.04259 0.04070 0.0098 0.0039 1.0000
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Polar data table (+)
Polar graphs
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