HT23 (ht23-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT23 (ht23-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.77 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht23-il-1000000.txt Download as CSV file: xf-ht23-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HT23
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5504 0.10847 0.10696 0.0276 1.0000 0.0097
-9.750 -0.5521 0.10368 0.10218 0.0263 1.0000 0.0098
-6.000 -0.5810 0.02019 0.01614 -0.0111 1.0000 0.0100
-5.750 -0.5553 0.01864 0.01438 -0.0108 1.0000 0.0098
-5.500 -0.5311 0.01532 0.01069 -0.0105 1.0000 0.0094
-5.250 -0.5046 0.01376 0.00888 -0.0101 1.0000 0.0095
-5.000 -0.4773 0.01291 0.00789 -0.0098 1.0000 0.0097
-4.750 -0.4515 0.01097 0.00576 -0.0095 1.0000 0.0104
-4.500 -0.4242 0.01039 0.00514 -0.0093 1.0000 0.0109
-4.250 -0.3966 0.00989 0.00461 -0.0091 1.0000 0.0114
-4.000 -0.3689 0.00942 0.00410 -0.0090 1.0000 0.0120
-3.750 -0.3411 0.00896 0.00360 -0.0088 1.0000 0.0126
-3.500 -0.3131 0.00866 0.00327 -0.0087 1.0000 0.0132
-3.250 -0.2853 0.00805 0.00262 -0.0085 1.0000 0.0149
-3.000 -0.2572 0.00776 0.00233 -0.0084 1.0000 0.0165
-2.750 -0.2291 0.00745 0.00199 -0.0083 1.0000 0.0189
-2.500 -0.2009 0.00719 0.00175 -0.0082 1.0000 0.0236
-2.250 -0.1729 0.00686 0.00150 -0.0081 1.0000 0.0398
-2.000 -0.1449 0.00653 0.00133 -0.0081 1.0000 0.0779
-1.750 -0.1086 0.00616 0.00121 -0.0099 0.9545 0.1463
-1.500 -0.0867 0.00607 0.00112 -0.0082 0.8594 0.2193
-1.250 -0.0623 0.00603 0.00102 -0.0074 0.7633 0.3055
-1.000 -0.0358 0.00585 0.00094 -0.0072 0.6837 0.4249
-0.750 -0.0089 0.00559 0.00090 -0.0072 0.6248 0.5590
-0.500 0.0177 0.00524 0.00088 -0.0070 0.5794 0.7089
-0.250 0.0417 0.00489 0.00089 -0.0059 0.5433 0.8515
0.000 0.0647 0.00472 0.00087 -0.0041 0.5117 0.9684
0.250 0.1007 0.00483 0.00084 -0.0058 0.4797 1.0000
0.500 0.1287 0.00495 0.00083 -0.0058 0.4537 1.0000
0.750 0.1568 0.00507 0.00083 -0.0057 0.4300 1.0000
1.000 0.1849 0.00518 0.00085 -0.0056 0.4087 1.0000
1.250 0.2131 0.00530 0.00087 -0.0056 0.3885 1.0000
1.750 0.2695 0.00554 0.00094 -0.0055 0.3519 1.0000
2.000 0.2977 0.00566 0.00098 -0.0054 0.3341 1.0000
2.250 0.3259 0.00579 0.00103 -0.0054 0.3164 1.0000
2.500 0.3540 0.00592 0.00110 -0.0054 0.2991 1.0000
2.750 0.3822 0.00607 0.00117 -0.0053 0.2812 1.0000
3.000 0.4103 0.00622 0.00125 -0.0053 0.2627 1.0000
3.250 0.4383 0.00641 0.00134 -0.0053 0.2402 1.0000
3.500 0.4664 0.00658 0.00145 -0.0053 0.2217 1.0000
3.750 0.4944 0.00677 0.00157 -0.0053 0.2025 1.0000
4.000 0.5223 0.00699 0.00170 -0.0052 0.1827 1.0000
4.250 0.5503 0.00719 0.00185 -0.0052 0.1653 1.0000
4.500 0.5781 0.00743 0.00202 -0.0052 0.1462 1.0000
4.750 0.6058 0.00770 0.00220 -0.0052 0.1265 1.0000
5.000 0.6335 0.00797 0.00240 -0.0052 0.1088 1.0000
5.250 0.6610 0.00830 0.00264 -0.0051 0.0896 1.0000
5.500 0.6884 0.00863 0.00290 -0.0051 0.0715 1.0000
5.750 0.7157 0.00901 0.00320 -0.0051 0.0557 1.0000
6.000 0.7430 0.00939 0.00353 -0.0050 0.0451 1.0000
6.250 0.7704 0.00973 0.00387 -0.0049 0.0389 1.0000
6.500 0.7975 0.01013 0.00425 -0.0048 0.0337 1.0000
6.750 0.8247 0.01050 0.00467 -0.0047 0.0309 1.0000
7.000 0.8519 0.01081 0.00503 -0.0046 0.0290 1.0000
7.250 0.8787 0.01122 0.00545 -0.0045 0.0267 1.0000
7.500 0.9048 0.01192 0.00622 -0.0043 0.0239 1.0000
7.750 0.9318 0.01220 0.00655 -0.0042 0.0231 1.0000
8.000 0.9585 0.01259 0.00700 -0.0040 0.0219 1.0000
8.250 0.9849 0.01302 0.00747 -0.0039 0.0207 1.0000
8.500 1.0106 0.01360 0.00809 -0.0037 0.0193 1.0000
8.750 1.0348 0.01463 0.00924 -0.0034 0.0178 1.0000
9.000 1.0610 0.01500 0.00967 -0.0033 0.0173 1.0000
9.250 1.0866 0.01550 0.01026 -0.0030 0.0166 1.0000
9.500 1.1119 0.01605 0.01087 -0.0028 0.0158 1.0000
9.750 1.1370 0.01660 0.01148 -0.0026 0.0151 1.0000
10.000 1.1612 0.01733 0.01225 -0.0024 0.0143 1.0000
10.250 1.1808 0.01908 0.01418 -0.0018 0.0133 1.0000
10.500 1.2056 0.01955 0.01474 -0.0016 0.0130 1.0000
10.750 1.2293 0.02025 0.01554 -0.0013 0.0125 1.0000
11.000 1.2522 0.02104 0.01644 -0.0009 0.0120 1.0000
11.250 1.2748 0.02185 0.01734 -0.0006 0.0115 1.0000
11.500 1.2973 0.02259 0.01815 -0.0003 0.0111 1.0000
11.750 1.3192 0.02338 0.01900 0.0000 0.0106 1.0000
12.000 1.3339 0.02537 0.02116 0.0006 0.0100 1.0000
12.250 1.3471 0.02744 0.02345 0.0013 0.0096 1.0000
12.500 1.3658 0.02851 0.02464 0.0017 0.0094 1.0000
12.750 1.3821 0.02983 0.02611 0.0022 0.0092 1.0000
13.000 1.3959 0.03138 0.02780 0.0027 0.0089 1.0000
13.250 1.4070 0.03315 0.02972 0.0031 0.0086 1.0000
13.500 1.4150 0.03512 0.03183 0.0035 0.0084 1.0000
13.750 1.4141 0.03753 0.03438 0.0040 0.0083 1.0000
14.000 1.4058 0.04204 0.03908 0.0006 0.0082 1.0000
14.250 1.3920 0.05039 0.04765 -0.0082 0.0082 1.0000
14.500 1.3664 0.06041 0.05788 -0.0162 0.0082 1.0000
14.750 1.3320 0.07099 0.06862 -0.0230 0.0083 1.0000
15.000 1.2939 0.08187 0.07964 -0.0293 0.0085 1.0000
15.250 1.2532 0.09327 0.09118 -0.0356 0.0086 1.0000
15.500 1.2154 0.10447 0.10249 -0.0416 0.0088 1.0000
15.750 1.1768 0.11659 0.11474 -0.0480 0.0090 1.0000
16.000 1.1338 0.13055 0.12883 -0.0553 0.0092 1.0000
16.250 0.9229 0.20288 0.20130 -0.0893 0.0102 1.0000
16.500 0.9294 0.20600 0.20443 -0.0911 0.0100 1.0000
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Polar data table (+)
Polar graphs
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