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 = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.6475 0.09371 0.08705 0.0129 1.0000 0.0540 -7.750 -0.6373 0.09013 0.08345 0.0143 1.0000 0.0513 -7.500 -0.6308 0.08527 0.07860 0.0113 1.0000 0.0497 -7.250 -0.6239 0.07983 0.07314 0.0070 1.0000 0.0481 -7.000 -0.6157 0.07383 0.06708 0.0022 1.0000 0.0464 -6.750 -0.6060 0.06705 0.06012 -0.0031 1.0000 0.0444 -6.500 -0.5929 0.05883 0.05118 -0.0095 1.0000 0.0417 -6.250 -0.5772 0.05415 0.04624 -0.0109 1.0000 0.0415 -6.000 -0.5595 0.04948 0.04119 -0.0124 1.0000 0.0419 -5.750 -0.5412 0.04628 0.03794 -0.0129 1.0000 0.0438 -5.500 -0.5200 0.04287 0.03418 -0.0136 1.0000 0.0455 -5.250 -0.4967 0.03920 0.03002 -0.0141 1.0000 0.0464 -5.000 -0.4719 0.03571 0.02600 -0.0143 1.0000 0.0469 -4.750 -0.4458 0.03265 0.02242 -0.0143 1.0000 0.0479 -4.500 -0.4189 0.03008 0.01934 -0.0140 1.0000 0.0503 -4.250 -0.3915 0.02788 0.01668 -0.0135 1.0000 0.0542 -4.000 -0.3654 0.02600 0.01467 -0.0131 1.0000 0.0583 -3.750 -0.3383 0.02432 0.01274 -0.0124 1.0000 0.0634 -3.500 -0.3119 0.02285 0.01123 -0.0118 1.0000 0.0721 -3.250 -0.2848 0.02149 0.00974 -0.0112 1.0000 0.0832 -3.000 -0.2580 0.02025 0.00846 -0.0108 1.0000 0.1037 -2.750 -0.2314 0.01885 0.00732 -0.0105 1.0000 0.1507 -2.500 -0.2074 0.01695 0.00647 -0.0104 1.0000 0.3207 -2.250 -0.1924 0.01513 0.00618 -0.0070 1.0000 0.6263 -2.000 -0.1357 0.01413 0.00558 -0.0098 1.0000 1.0000 -1.750 -0.1104 0.01403 0.00514 -0.0094 1.0000 1.0000 -1.500 -0.0850 0.01396 0.00478 -0.0090 1.0000 1.0000 -1.250 -0.0595 0.01390 0.00449 -0.0087 1.0000 1.0000 -1.000 -0.0339 0.01386 0.00425 -0.0083 1.0000 1.0000 -0.750 -0.0083 0.01384 0.00407 -0.0080 1.0000 1.0000 -0.500 0.0173 0.01383 0.00396 -0.0076 1.0000 1.0000 -0.250 0.0429 0.01384 0.00388 -0.0073 1.0000 1.0000 0.000 0.0684 0.01387 0.00386 -0.0070 1.0000 1.0000 0.250 0.0937 0.01392 0.00390 -0.0068 1.0000 1.0000 0.500 0.1187 0.01399 0.00401 -0.0066 1.0000 1.0000 0.750 0.1542 0.01414 0.00420 -0.0085 0.9678 1.0000 1.000 0.2053 0.01439 0.00439 -0.0128 0.8699 1.0000 1.250 0.2403 0.01473 0.00450 -0.0131 0.7811 1.0000 1.500 0.2650 0.01516 0.00463 -0.0114 0.7135 1.0000 1.750 0.2885 0.01562 0.00479 -0.0098 0.6610 1.0000 2.000 0.3128 0.01608 0.00501 -0.0086 0.6174 1.0000 2.250 0.3377 0.01654 0.00528 -0.0076 0.5794 1.0000 2.500 0.3631 0.01700 0.00561 -0.0068 0.5463 1.0000 2.750 0.3888 0.01745 0.00594 -0.0061 0.5158 1.0000 3.000 0.4147 0.01791 0.00631 -0.0055 0.4870 1.0000 3.250 0.4409 0.01837 0.00673 -0.0050 0.4595 1.0000 3.500 0.4672 0.01884 0.00721 -0.0045 0.4332 1.0000 3.750 0.4934 0.01933 0.00769 -0.0041 0.4079 1.0000 4.000 0.5193 0.01983 0.00816 -0.0036 0.3836 1.0000 4.250 0.5454 0.02034 0.00872 -0.0032 0.3581 1.0000 4.500 0.5715 0.02088 0.00935 -0.0028 0.3328 1.0000 4.750 0.5974 0.02144 0.00993 -0.0024 0.3076 1.0000 5.000 0.6229 0.02201 0.01051 -0.0019 0.2818 1.0000 5.250 0.6482 0.02262 0.01116 -0.0015 0.2543 1.0000 5.500 0.6733 0.02329 0.01191 -0.0012 0.2260 1.0000 5.750 0.6980 0.02408 0.01272 -0.0009 0.1979 1.0000 6.000 0.7225 0.02501 0.01369 -0.0006 0.1708 1.0000 6.250 0.7466 0.02615 0.01488 -0.0003 0.1466 1.0000 6.500 0.7699 0.02740 0.01610 0.0001 0.1278 1.0000 6.750 0.7933 0.02891 0.01774 0.0005 0.1129 1.0000 7.000 0.8161 0.03049 0.01941 0.0009 0.1016 1.0000 7.250 0.8389 0.03221 0.02140 0.0013 0.0910 1.0000 7.500 0.8610 0.03437 0.02383 0.0018 0.0849 1.0000 7.750 0.8823 0.03654 0.02631 0.0022 0.0788 1.0000 8.000 0.9022 0.03882 0.02880 0.0025 0.0734 1.0000 8.250 0.9202 0.04199 0.03251 0.0027 0.0693 1.0000 8.500 0.9365 0.04520 0.03611 0.0029 0.0665 1.0000 8.750 0.9527 0.04785 0.03890 0.0031 0.0637 1.0000 9.000 0.9584 0.05281 0.04452 0.0023 0.0614 1.0000 9.250 0.9564 0.05856 0.05087 0.0006 0.0597 1.0000 9.500 0.9466 0.06502 0.05775 -0.0022 0.0589 1.0000 9.750 0.9269 0.07265 0.06562 -0.0071 0.0591 1.0000 10.000 0.9006 0.08225 0.07529 -0.0158 0.0603 1.0000 10.250 0.8796 0.09265 0.08566 -0.0240 0.0611 1.0000