HT05 (ht05-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT05 (ht05-il) Reynolds number: 50,000 Max Cl/Cd: 19.18 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht05-il-50000.txt Download as CSV file: xf-ht05-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.6933 0.09726 0.09062 0.0385 1.0000 0.2748
-7.250 -0.6955 0.09383 0.08726 0.0374 1.0000 0.2874
-7.000 -0.6905 0.08997 0.08340 0.0371 1.0000 0.3020
-6.750 -0.6829 0.08605 0.07949 0.0376 1.0000 0.3179
-6.500 -0.6825 0.08300 0.07649 0.0365 1.0000 0.3412
-6.250 -0.6734 0.07941 0.07292 0.0390 1.0000 0.3695
-5.750 -0.6242 0.05143 0.04329 -0.0061 1.0000 0.1412
-5.500 -0.6037 0.04659 0.03810 -0.0069 1.0000 0.1399
-5.250 -0.5813 0.04186 0.03285 -0.0074 1.0000 0.1374
-5.000 -0.5568 0.03726 0.02760 -0.0077 1.0000 0.1347
-4.750 -0.5311 0.03361 0.02331 -0.0075 1.0000 0.1374
-4.500 -0.5060 0.03099 0.02034 -0.0070 1.0000 0.1490
-4.250 -0.4783 0.02815 0.01689 -0.0064 1.0000 0.1581
-4.000 -0.4523 0.02607 0.01471 -0.0057 1.0000 0.1763
-3.750 -0.4253 0.02409 0.01251 -0.0049 1.0000 0.2019
-3.500 -0.3990 0.02233 0.01077 -0.0041 1.0000 0.2427
-3.250 -0.3724 0.02049 0.00922 -0.0031 1.0000 0.3037
-3.000 -0.3470 0.01869 0.00798 -0.0019 1.0000 0.4042
-2.750 -0.3286 0.01713 0.00737 0.0012 1.0000 0.5604
-2.500 -0.2469 0.01476 0.00569 -0.0066 1.0000 1.0000
-2.250 -0.2219 0.01462 0.00511 -0.0062 1.0000 1.0000
-2.000 -0.1971 0.01452 0.00467 -0.0056 1.0000 1.0000
-1.750 -0.1725 0.01443 0.00431 -0.0050 1.0000 1.0000
-1.500 -0.1478 0.01436 0.00399 -0.0043 1.0000 1.0000
-1.250 -0.1232 0.01430 0.00375 -0.0036 1.0000 1.0000
-1.000 -0.0986 0.01425 0.00356 -0.0029 1.0000 1.0000
-0.750 -0.0739 0.01422 0.00342 -0.0022 1.0000 1.0000
-0.500 -0.0493 0.01419 0.00331 -0.0014 1.0000 1.0000
-0.250 -0.0246 0.01418 0.00325 -0.0007 1.0000 1.0000
0.000 0.0001 0.01417 0.00323 0.0000 1.0000 1.0000
0.250 0.0247 0.01418 0.00325 0.0007 1.0000 1.0000
0.500 0.0494 0.01419 0.00331 0.0014 1.0000 1.0000
0.750 0.0740 0.01422 0.00342 0.0022 1.0000 1.0000
1.000 0.0987 0.01425 0.00356 0.0029 1.0000 1.0000
1.250 0.1233 0.01430 0.00375 0.0036 1.0000 1.0000
1.500 0.1480 0.01436 0.00399 0.0043 1.0000 1.0000
1.750 0.1726 0.01443 0.00431 0.0050 1.0000 1.0000
2.000 0.1972 0.01452 0.00467 0.0056 1.0000 1.0000
2.250 0.2220 0.01462 0.00511 0.0062 1.0000 1.0000
2.500 0.2471 0.01476 0.00569 0.0066 1.0000 1.0000
2.750 0.3287 0.01714 0.00737 -0.0012 0.5596 1.0000
3.000 0.3471 0.01870 0.00798 0.0019 0.4038 1.0000
3.250 0.3725 0.02050 0.00922 0.0031 0.3035 1.0000
3.500 0.3991 0.02234 0.01077 0.0041 0.2426 1.0000
3.750 0.4255 0.02410 0.01252 0.0049 0.2018 1.0000
4.000 0.4524 0.02606 0.01470 0.0057 0.1760 1.0000
4.250 0.4785 0.02817 0.01691 0.0064 0.1581 1.0000
4.500 0.5061 0.03099 0.02034 0.0070 0.1488 1.0000
4.750 0.5313 0.03362 0.02333 0.0075 0.1372 1.0000
5.000 0.5570 0.03729 0.02763 0.0077 0.1348 1.0000
5.250 0.5815 0.04191 0.03291 0.0074 0.1376 1.0000
5.500 0.6039 0.04664 0.03816 0.0068 0.1399 1.0000
5.750 0.6243 0.05149 0.04337 0.0060 0.1412 1.0000
6.000 0.6683 0.07610 0.06965 -0.0408 0.4005 1.0000
6.250 0.6706 0.07918 0.07268 -0.0397 0.3682 1.0000
6.750 0.6833 0.08609 0.07953 -0.0376 0.3180 1.0000
7.000 0.6912 0.09002 0.08345 -0.0371 0.3021 1.0000
7.500 0.6940 0.09731 0.09068 -0.0385 0.2748 1.0000
7.750 0.6929 0.10089 0.09419 -0.0393 0.2638 1.0000
8.000 0.7013 0.10529 0.09856 -0.0388 0.2542 1.0000
8.250 0.7162 0.11028 0.10357 -0.0372 0.2416 1.0000
8.500 0.7003 0.11196 0.10514 -0.0405 0.2329 1.0000
8.750 0.7037 0.11596 0.10910 -0.0409 0.2240 1.0000
9.000 0.7166 0.12087 0.11401 -0.0396 0.2124 1.0000
9.250 0.7080 0.12302 0.11608 -0.0420 0.2039 1.0000
9.500 0.7148 0.12755 0.12059 -0.0421 0.1970 1.0000
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Polar data table (+)
Polar graphs
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