HT23 (ht23-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT23 (ht23-il) Reynolds number: 500,000 Max Cl/Cd: 67.75 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht23-il-500000.txt Download as CSV file: xf-ht23-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7029 0.14650 0.14421 0.0517 1.0000 0.0133
-11.250 -0.6988 0.14222 0.13994 0.0498 1.0000 0.0133
-11.000 -0.6987 0.13713 0.13487 0.0491 1.0000 0.0135
-10.750 -0.6929 0.13384 0.13158 0.0490 1.0000 0.0137
-10.500 -0.6876 0.13042 0.12817 0.0482 1.0000 0.0140
-10.250 -0.6832 0.12685 0.12460 0.0471 1.0000 0.0142
-7.250 -0.6487 0.06285 0.06059 -0.0008 1.0000 0.0184
-5.000 -0.4741 0.01950 0.01429 -0.0116 1.0000 0.0168
-4.750 -0.4478 0.01670 0.01109 -0.0111 1.0000 0.0164
-4.500 -0.4207 0.01499 0.00913 -0.0106 1.0000 0.0167
-4.250 -0.3933 0.01378 0.00775 -0.0102 1.0000 0.0171
-4.000 -0.3657 0.01307 0.00693 -0.0099 1.0000 0.0177
-3.750 -0.3394 0.01160 0.00538 -0.0096 1.0000 0.0192
-3.500 -0.3120 0.01088 0.00464 -0.0093 1.0000 0.0203
-3.250 -0.2844 0.01027 0.00400 -0.0091 1.0000 0.0219
-3.000 -0.2566 0.00981 0.00350 -0.0089 1.0000 0.0237
-2.750 -0.2290 0.00910 0.00277 -0.0087 1.0000 0.0282
-2.500 -0.2011 0.00866 0.00235 -0.0085 1.0000 0.0373
-2.250 -0.1733 0.00812 0.00196 -0.0084 1.0000 0.0708
-2.000 -0.1461 0.00747 0.00173 -0.0085 1.0000 0.1706
-1.750 -0.1190 0.00690 0.00160 -0.0085 1.0000 0.2847
-1.500 -0.0924 0.00625 0.00150 -0.0085 1.0000 0.4353
-1.250 -0.0668 0.00554 0.00144 -0.0082 1.0000 0.6119
-1.000 -0.0447 0.00484 0.00144 -0.0067 1.0000 0.7985
-0.750 -0.0042 0.00451 0.00147 -0.0083 0.9453 0.9721
-0.500 0.0287 0.00470 0.00135 -0.0086 0.8371 1.0000
-0.250 0.0516 0.00506 0.00126 -0.0071 0.7376 1.0000
0.000 0.0773 0.00538 0.00121 -0.0064 0.6624 1.0000
0.250 0.1042 0.00563 0.00118 -0.0061 0.6070 1.0000
0.500 0.1314 0.00584 0.00117 -0.0058 0.5629 1.0000
0.750 0.1590 0.00602 0.00117 -0.0057 0.5263 1.0000
1.000 0.1866 0.00619 0.00118 -0.0055 0.4943 1.0000
1.250 0.2144 0.00636 0.00121 -0.0054 0.4662 1.0000
1.500 0.2422 0.00652 0.00125 -0.0053 0.4410 1.0000
1.750 0.2701 0.00668 0.00130 -0.0052 0.4176 1.0000
2.000 0.2980 0.00684 0.00135 -0.0051 0.3963 1.0000
2.250 0.3259 0.00699 0.00142 -0.0050 0.3757 1.0000
2.500 0.3538 0.00716 0.00151 -0.0050 0.3560 1.0000
2.750 0.3818 0.00731 0.00160 -0.0049 0.3370 1.0000
3.000 0.4097 0.00748 0.00170 -0.0048 0.3175 1.0000
3.250 0.4375 0.00767 0.00180 -0.0048 0.2979 1.0000
3.500 0.4654 0.00785 0.00194 -0.0047 0.2777 1.0000
3.750 0.4931 0.00807 0.00207 -0.0046 0.2551 1.0000
4.000 0.5209 0.00828 0.00221 -0.0046 0.2337 1.0000
4.250 0.5486 0.00852 0.00240 -0.0045 0.2133 1.0000
4.500 0.5762 0.00877 0.00258 -0.0045 0.1917 1.0000
4.750 0.6037 0.00907 0.00279 -0.0044 0.1705 1.0000
5.000 0.6312 0.00936 0.00303 -0.0044 0.1497 1.0000
5.250 0.6584 0.00973 0.00331 -0.0044 0.1267 1.0000
5.500 0.6856 0.01012 0.00362 -0.0043 0.1034 1.0000
5.750 0.7125 0.01059 0.00400 -0.0043 0.0806 1.0000
6.000 0.7392 0.01117 0.00449 -0.0042 0.0621 1.0000
6.250 0.7659 0.01177 0.00507 -0.0040 0.0512 1.0000
6.500 0.7928 0.01220 0.00555 -0.0039 0.0459 1.0000
6.750 0.8188 0.01299 0.00637 -0.0037 0.0406 1.0000
7.000 0.8455 0.01341 0.00686 -0.0035 0.0377 1.0000
7.250 0.8717 0.01397 0.00747 -0.0033 0.0348 1.0000
7.500 0.8956 0.01529 0.00888 -0.0030 0.0317 1.0000
7.750 0.9218 0.01579 0.00947 -0.0028 0.0305 1.0000
8.000 0.9475 0.01638 0.01016 -0.0025 0.0286 1.0000
8.250 0.9727 0.01705 0.01091 -0.0023 0.0270 1.0000
8.500 0.9967 0.01804 0.01196 -0.0020 0.0254 1.0000
8.750 1.0165 0.02027 0.01437 -0.0013 0.0239 1.0000
9.000 1.0413 0.02095 0.01519 -0.0010 0.0232 1.0000
9.250 1.0653 0.02178 0.01617 -0.0006 0.0220 1.0000
9.500 1.0884 0.02275 0.01726 -0.0003 0.0209 1.0000
9.750 1.1108 0.02381 0.01844 0.0001 0.0200 1.0000
10.000 1.1320 0.02504 0.01976 0.0005 0.0192 1.0000
10.250 1.1473 0.02772 0.02265 0.0011 0.0184 1.0000
10.500 1.1603 0.03075 0.02603 0.0018 0.0177 1.0000
10.750 1.1791 0.03202 0.02752 0.0022 0.0172 1.0000
11.000 1.1947 0.03380 0.02955 0.0027 0.0165 1.0000
11.250 1.2067 0.03604 0.03203 0.0032 0.0159 1.0000
11.500 1.2158 0.03845 0.03466 0.0036 0.0155 1.0000
11.750 1.2212 0.04105 0.03747 0.0038 0.0151 1.0000
12.000 1.2208 0.04392 0.04055 0.0038 0.0148 1.0000
12.250 1.2105 0.04771 0.04453 0.0026 0.0147 1.0000
12.500 1.1945 0.05455 0.05162 -0.0041 0.0147 1.0000
12.750 1.1680 0.06508 0.06241 -0.0140 0.0148 1.0000
13.000 1.1125 0.08200 0.07963 -0.0273 0.0155 1.0000
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Polar data table (+)
Polar graphs
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