HT22 (ht22-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT22 (ht22-il) Reynolds number: 100,000 Max Cl/Cd: 34.97 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht22-il-100000.txt Download as CSV file: xf-ht22-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HT22
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6506 0.10712 0.10233 0.0347 1.0001 0.0721
-8.000 -0.6531 0.10395 0.09923 0.0285 1.0001 0.0741
-7.750 -0.6513 0.10000 0.09529 0.0153 1.0001 0.0750
-7.500 -0.6448 0.09407 0.08941 0.0154 1.0001 0.0761
-7.250 -0.6347 0.09037 0.08574 0.0219 1.0001 0.0787
-7.000 -0.6247 0.08643 0.08181 0.0200 1.0001 0.0821
-6.750 -0.6119 0.08162 0.07695 0.0117 1.0001 0.0871
-6.500 -0.5978 0.07553 0.07072 0.0020 1.0001 0.0903
-6.250 -0.5868 0.07206 0.06734 0.0056 1.0001 0.0935
-6.000 -0.5624 0.06757 0.06235 -0.0064 1.0001 0.1036
-5.750 -0.5515 0.06270 0.05777 -0.0029 1.0001 0.1062
-5.500 -0.5291 0.05862 0.05337 -0.0080 1.0001 0.1185
-5.000 -0.4938 0.05169 0.04648 -0.0076 1.0001 0.1409
-4.750 -0.4700 0.04805 0.04253 -0.0109 1.0001 0.1619
-4.500 -0.4500 0.04466 0.03916 -0.0108 1.0001 0.1777
-4.250 -0.4287 0.04176 0.03625 -0.0106 1.0001 0.1973
-4.000 -0.4073 0.03903 0.03346 -0.0106 1.0001 0.2266
-3.750 -0.3401 0.02781 0.01979 -0.0160 1.0001 0.0774
-3.500 -0.3097 0.02592 0.01727 -0.0154 1.0001 0.0754
-3.250 -0.2815 0.02296 0.01400 -0.0150 1.0001 0.0739
-3.000 -0.2527 0.02085 0.01152 -0.0145 1.0001 0.0743
-2.750 -0.2254 0.01889 0.00951 -0.0142 1.0001 0.0808
-2.500 -0.1971 0.01749 0.00794 -0.0135 1.0001 0.0866
-2.250 -0.1700 0.01608 0.00657 -0.0130 1.0001 0.0972
-2.000 -0.1433 0.01483 0.00543 -0.0123 1.0001 0.1122
-1.750 -0.1171 0.01369 0.00447 -0.0117 1.0001 0.1450
-1.500 -0.0852 0.00962 0.00350 -0.0109 1.0001 0.9999
-1.250 -0.0584 0.00958 0.00313 -0.0104 1.0001 0.9999
-1.000 -0.0318 0.00955 0.00286 -0.0100 1.0001 0.9999
-0.750 -0.0052 0.00953 0.00268 -0.0096 1.0001 0.9999
-0.500 0.0214 0.00953 0.00254 -0.0093 1.0001 0.9999
-0.250 0.0479 0.00953 0.00245 -0.0089 1.0001 0.9999
0.000 0.0744 0.00954 0.00240 -0.0086 1.0001 0.9999
0.250 0.1007 0.00956 0.00239 -0.0083 1.0001 0.9999
0.500 0.1270 0.00959 0.00242 -0.0080 1.0001 0.9999
0.750 0.1532 0.00964 0.00249 -0.0077 1.0001 0.9999
1.000 0.1793 0.00970 0.00260 -0.0074 1.0001 0.9999
1.250 0.2051 0.00978 0.00277 -0.0072 1.0001 0.9999
1.500 0.2307 0.00990 0.00303 -0.0072 1.0001 0.9999
1.750 0.2957 0.01009 0.00334 -0.0145 0.9000 0.9999
2.000 0.3242 0.01053 0.00340 -0.0126 0.7598 0.9999
2.250 0.3453 0.01112 0.00354 -0.0100 0.6662 0.9999
2.500 0.3685 0.01170 0.00379 -0.0084 0.5969 0.9999
2.750 0.3931 0.01225 0.00405 -0.0074 0.5402 0.9999
3.000 0.4182 0.01278 0.00434 -0.0065 0.4903 0.9999
3.250 0.4436 0.01329 0.00466 -0.0058 0.4424 0.9999
3.500 0.4691 0.01379 0.00498 -0.0052 0.3951 0.9999
3.750 0.4947 0.01432 0.00535 -0.0046 0.3461 0.9999
4.000 0.5203 0.01489 0.00572 -0.0042 0.2935 0.9999
4.250 0.5459 0.01561 0.00622 -0.0038 0.2390 0.9999
4.500 0.5712 0.01658 0.00689 -0.0034 0.1932 0.9999
4.750 0.5970 0.01768 0.00791 -0.0029 0.1592 0.9999
5.000 0.6223 0.01893 0.00893 -0.0026 0.1368 0.9999
5.250 0.6485 0.02018 0.01024 -0.0021 0.1207 0.9999
5.500 0.6743 0.02180 0.01177 -0.0017 0.1100 0.9999
5.750 0.7008 0.02299 0.01326 -0.0012 0.0999 0.9999
6.000 0.7266 0.02500 0.01544 -0.0008 0.0939 0.9999
6.250 0.7526 0.02712 0.01798 -0.0003 0.0896 0.9999
6.500 0.7774 0.02914 0.02014 0.0000 0.0851 0.9999
6.750 0.8005 0.03207 0.02357 0.0002 0.0811 0.9999
7.000 0.8224 0.03575 0.02795 0.0005 0.0799 0.9999
7.250 0.8414 0.04042 0.03327 0.0004 0.0800 0.9999
7.500 0.8571 0.04582 0.03922 -0.0001 0.0809 0.9999
7.750 0.8686 0.05178 0.04571 -0.0013 0.0813 0.9999
8.000 0.8780 0.05788 0.05214 -0.0027 0.0822 0.9999
8.250 0.8118 0.09388 0.08901 -0.0410 0.1567 0.9999
8.500 0.8507 0.09482 0.09001 -0.0256 0.1507 0.9999
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Polar data table (+)
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