HT22 (ht22-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT22 (ht22-il) Reynolds number: 200,000 Max Cl/Cd: 46.48 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht22-il-200000-n5.txt Download as CSV file: xf-ht22-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6668 0.10793 0.10445 0.0334 1.0001 0.0200
-8.500 -0.6635 0.10362 0.10017 0.0311 1.0001 0.0201
-8.000 -0.6567 0.09471 0.09131 0.0252 1.0001 0.0201
-7.000 -0.6276 0.07850 0.07513 0.0157 1.0001 0.0235
-6.500 -0.5968 0.06418 0.06061 0.0016 1.0001 0.0187
-6.000 -0.5555 0.04556 0.04131 -0.0097 1.0001 0.0146
-5.750 -0.5349 0.04010 0.03554 -0.0116 1.0001 0.0145
-5.500 -0.5125 0.03431 0.02930 -0.0130 1.0001 0.0144
-5.250 -0.4884 0.02863 0.02297 -0.0137 1.0001 0.0145
-5.000 -0.4631 0.02425 0.01790 -0.0138 1.0001 0.0148
-4.750 -0.4377 0.02244 0.01587 -0.0140 1.0001 0.0157
-4.500 -0.4115 0.02148 0.01476 -0.0139 1.0001 0.0172
-4.250 -0.3843 0.01941 0.01225 -0.0136 1.0001 0.0184
-4.000 -0.3569 0.01751 0.00997 -0.0132 1.0001 0.0192
-3.750 -0.3295 0.01615 0.00833 -0.0128 1.0001 0.0200
-3.500 -0.3029 0.01479 0.00690 -0.0125 1.0001 0.0214
-3.250 -0.2758 0.01422 0.00631 -0.0123 1.0001 0.0242
-3.000 -0.2486 0.01346 0.00544 -0.0119 1.0001 0.0266
-2.750 -0.2217 0.01253 0.00449 -0.0116 1.0001 0.0290
-2.500 -0.1945 0.01203 0.00401 -0.0114 1.0001 0.0334
-2.250 -0.1672 0.01148 0.00343 -0.0112 1.0001 0.0386
-2.000 -0.1399 0.01105 0.00299 -0.0110 1.0001 0.0465
-1.750 -0.1125 0.01062 0.00261 -0.0108 1.0001 0.0591
-1.500 -0.0852 0.01020 0.00232 -0.0106 1.0001 0.0851
-1.250 -0.0582 0.00966 0.00210 -0.0106 1.0001 0.1574
-1.000 -0.0324 0.00871 0.00195 -0.0107 1.0001 0.3684
-0.750 -0.0112 0.00749 0.00190 -0.0093 1.0001 0.6720
-0.500 0.0221 0.00675 0.00185 -0.0092 1.0001 0.9999
-0.250 0.0495 0.00675 0.00178 -0.0090 0.9976 0.9999
0.000 0.0924 0.00684 0.00174 -0.0120 0.9139 0.9999
0.250 0.1216 0.00706 0.00165 -0.0114 0.8056 0.9999
0.500 0.1440 0.00742 0.00160 -0.0095 0.7094 0.9999
0.750 0.1684 0.00779 0.00157 -0.0084 0.6295 0.9999
1.000 0.1941 0.00812 0.00158 -0.0078 0.5664 0.9999
1.250 0.2206 0.00842 0.00161 -0.0074 0.5154 0.9999
1.500 0.2473 0.00869 0.00167 -0.0070 0.4730 0.9999
1.750 0.2743 0.00895 0.00175 -0.0068 0.4362 0.9999
2.000 0.3015 0.00919 0.00184 -0.0066 0.4025 0.9999
2.250 0.3286 0.00944 0.00194 -0.0064 0.3703 0.9999
2.500 0.3558 0.00969 0.00206 -0.0062 0.3386 0.9999
2.750 0.3830 0.00995 0.00221 -0.0060 0.3064 0.9999
3.000 0.4102 0.01023 0.00237 -0.0059 0.2736 0.9999
3.250 0.4373 0.01054 0.00255 -0.0057 0.2392 0.9999
3.500 0.4644 0.01088 0.00275 -0.0056 0.2054 0.9999
3.750 0.4914 0.01125 0.00303 -0.0055 0.1729 0.9999
4.000 0.5183 0.01167 0.00331 -0.0054 0.1421 0.9999
4.250 0.5452 0.01210 0.00365 -0.0053 0.1168 0.9999
4.500 0.5719 0.01257 0.00403 -0.0052 0.0952 0.9999
4.750 0.5987 0.01304 0.00448 -0.0051 0.0795 0.9999
5.000 0.6254 0.01355 0.00497 -0.0049 0.0683 0.9999
5.250 0.6520 0.01409 0.00551 -0.0048 0.0589 0.9999
5.500 0.6786 0.01460 0.00611 -0.0045 0.0524 0.9999
5.750 0.7047 0.01527 0.00679 -0.0044 0.0475 0.9999
6.000 0.7308 0.01598 0.00759 -0.0041 0.0441 0.9999
6.250 0.7568 0.01661 0.00833 -0.0039 0.0406 0.9999
6.500 0.7825 0.01732 0.00911 -0.0037 0.0374 0.9999
6.750 0.8071 0.01842 0.01028 -0.0033 0.0352 0.9999
7.000 0.8324 0.01934 0.01136 -0.0030 0.0337 0.9999
7.250 0.8573 0.02035 0.01254 -0.0026 0.0319 0.9999
7.500 0.8821 0.02124 0.01357 -0.0023 0.0299 0.9999
7.750 0.9064 0.02220 0.01464 -0.0021 0.0282 0.9999
8.000 0.9284 0.02410 0.01668 -0.0017 0.0268 0.9999
8.250 0.9517 0.02558 0.01846 -0.0013 0.0260 0.9999
8.500 0.9740 0.02727 0.02049 -0.0009 0.0248 0.9999
8.750 0.9957 0.02891 0.02244 -0.0006 0.0234 0.9999
9.000 1.0168 0.03044 0.02424 -0.0004 0.0221 0.9999
9.250 1.0364 0.03225 0.02629 -0.0001 0.0213 0.9999
9.500 1.0541 0.03435 0.02861 0.0001 0.0205 0.9999
10.000 1.0731 0.04203 0.03719 -0.0002 0.0194 0.9999
10.250 1.0725 0.04721 0.04294 -0.0013 0.0188 0.9999
10.500 1.0604 0.05380 0.05001 -0.0043 0.0185 0.9999
10.750 1.0369 0.06266 0.05917 -0.0132 0.0188 0.9999
11.000 1.0062 0.07717 0.07380 -0.0278 0.0194 0.9999
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Polar data table (+)
Polar graphs
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