XFOIL Version 6.94 Calculated polar for: DSMA-523B AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.500 0.4268 0.01467 0.01049 -0.0998 0.9116 0.7211 1.000 0.5016 0.01762 0.01027 -0.1021 0.2030 0.7279 1.500 0.5628 0.01912 0.01109 -0.1038 0.1028 0.7393 2.000 0.6020 0.01970 0.01158 -0.0993 0.0891 0.7449 2.500 0.6478 0.02041 0.01228 -0.0964 0.0800 0.7525 3.000 0.7109 0.02136 0.01316 -0.0982 0.0728 0.7589 3.500 0.7751 0.02243 0.01417 -0.1004 0.0667 0.7605 4.000 0.8327 0.02364 0.01526 -0.1010 0.0621 0.7631 4.500 0.8890 0.02444 0.01623 -0.1008 0.0580 0.7644 5.000 0.9464 0.02608 0.01780 -0.1014 0.0544 0.7655 5.500 1.0005 0.02753 0.01956 -0.1005 0.0517 0.7678 6.000 1.0571 0.02907 0.02117 -0.1009 0.0491 0.7689 6.500 1.1106 0.03175 0.02424 -0.1006 0.0466 0.7699 7.000 1.1596 0.03502 0.02802 -0.0993 0.0447 0.7709 7.500 1.2053 0.03819 0.03155 -0.0979 0.0434 0.7720 8.000 1.2473 0.04179 0.03540 -0.0963 0.0425 0.7730 9.500 0.8020 0.10703 0.10453 -0.0614 0.0633 0.7730 10.000 0.8023 0.11427 0.11176 -0.0624 0.0625 0.7735 10.500 0.7240 0.13624 0.13373 -0.0769 0.0597 0.7735 11.000 0.7112 0.14321 0.14070 -0.0799 0.0571 0.7740 11.500 0.7161 0.14737 0.14486 -0.0803 0.0556 0.7748 12.000 0.7349 0.15120 0.14870 -0.0789 0.0548 0.7764 12.500 0.6897 0.16235 0.15987 -0.0886 0.0520 0.7767 13.000 0.6938 0.16788 0.16541 -0.0912 0.0499 0.7775 13.500 0.7080 0.17273 0.17027 -0.0924 0.0487 0.7782 14.000 0.7341 0.17843 0.17597 -0.0915 0.0480 0.7790 14.500 0.7024 0.18642 0.18399 -0.1007 0.0455 0.7794 15.000 0.7108 0.19184 0.18943 -0.1032 0.0435 0.7800 15.500 0.7274 0.19679 0.19439 -0.1042 0.0424 0.7808 16.000 0.7250 0.20392 0.20153 -0.1086 0.0414 0.7813 16.500 0.7292 0.21005 0.20769 -0.1122 0.0383 0.7819 17.000 0.7416 0.21520 0.21285 -0.1139 0.0370 0.7826 17.500 0.7542 0.22194 0.21961 -0.1154 0.0364 0.7834 18.000 0.7492 0.22883 0.22653 -0.1209 0.0338 0.7841 18.500 0.7579 0.23437 0.23211 -0.1231 0.0323 0.7853 19.000 0.7702 0.23983 0.23759 -0.1243 0.0316 0.7869 19.500 0.7727 0.24692 0.24471 -0.1278 0.0311 0.7881 20.000 0.7767 0.25370 0.25152 -0.1315 0.0290 0.7891 20.500 0.7847 0.25957 0.25742 -0.1339 0.0278 0.7902 21.000 0.7943 0.26518 0.26305 -0.1358 0.0270 0.7915 21.500 0.8040 0.27221 0.27010 -0.1376 0.0267 0.7929 22.000 0.8039 0.27947 0.27741 -0.1421 0.0257 0.7940 22.500 0.8106 0.28589 0.28386 -0.1448 0.0240 0.7955 23.000 0.8180 0.29182 0.28981 -0.1472 0.0231 0.7971 23.500 0.8270 0.29789 0.29591 -0.1489 0.0226 0.7988 24.000 0.8307 0.30534 0.30338 -0.1521 0.0223 0.8002 24.500 0.8347 0.31288 0.31095 -0.1555 0.0213 0.8016 25.000 0.8405 0.31957 0.31766 -0.1582 0.0200 0.8030 25.500 0.8464 0.32563 0.32376 -0.1606 0.0191 0.8050 26.000 0.8532 0.33174 0.32991 -0.1624 0.0186 0.8072 26.500 0.8560 0.33929 0.33749 -0.1653 0.0184 0.8095 27.000 0.8594 0.34699 0.34523 -0.1683 0.0177 0.8123 27.500 0.8637 0.35391 0.35219 -0.1709 0.0165 0.8153 28.000 0.8681 0.36030 0.35861 -0.1733 0.0156 0.8181 28.500 0.8726 0.36645 0.36479 -0.1756 0.0151 0.8210 29.000 0.8761 0.37385 0.37221 -0.1779 0.0149 0.8239 29.500 0.8782 0.38185 0.38027 -0.1809 0.0145 0.8271 30.000 0.8812 0.38900 0.38746 -0.1834 0.0133 0.8310 30.500 0.8840 0.39546 0.39395 -0.1858 0.0124 0.8355 31.000 0.8867 0.40143 0.39996 -0.1880 0.0119 0.8408 31.500 0.8884 0.40867 0.40724 -0.1902 0.0117 0.8465 32.000 0.8897 0.41676 0.41537 -0.1928 0.0114 0.8531 32.500 0.8913 0.42393 0.42259 -0.1951 0.0105 0.8619 33.000 0.8925 0.43013 0.42885 -0.1973 0.0096 0.8761 33.500 0.8925 0.43510 0.43391 -0.1991 0.0091 0.9344 34.500 0.8944 0.45008 0.44891 -0.2042 0.0087 1.0000 35.000 0.8952 0.45784 0.45668 -0.2066 0.0083 1.0000 35.500 0.8955 0.46459 0.46344 -0.2089 0.0074 1.0000 36.000 0.8954 0.47062 0.46948 -0.2112 0.0068 1.0000 36.500 0.8947 0.47606 0.47494 -0.2134 0.0065 1.0000 37.500 0.8928 0.49060 0.48950 -0.2178 0.0063 1.0000 38.000 0.8917 0.49736 0.49628 -0.2198 0.0058 1.0000 38.500 0.8902 0.50348 0.50242 -0.2219 0.0053 1.0000 39.000 0.8883 0.50905 0.50801 -0.2240 0.0049 1.0000 39.500 0.8860 0.51385 0.51283 -0.2261 0.0046 1.0000 40.500 0.8808 0.52626 0.52528 -0.2301 0.0044 1.0000 41.000 0.8783 0.53276 0.53180 -0.2320 0.0042 1.0000 41.500 0.8753 0.53853 0.53759 -0.2339 0.0037 1.0000 42.000 0.8720 0.54366 0.54275 -0.2359 0.0033 1.0000 42.500 0.8684 0.54798 0.54709 -0.2378 0.0029 1.0000 43.500 0.8604 0.55870 0.55785 -0.2415 0.0027 1.0000 44.000 0.8566 0.56459 0.56377 -0.2432 0.0024 1.0000 44.500 0.8522 0.56927 0.56846 -0.2450 0.0020 1.0000 45.000 0.8475 0.57308 0.57230 -0.2468 0.0017 1.0000 45.500 0.8420 0.57596 0.57520 -0.2487 0.0015 1.0000 46.000 0.8373 0.58187 0.58112 -0.2503 0.0015 1.0000 46.500 0.8324 0.58705 0.58632 -0.2518 0.0014 1.0000 47.000 0.8271 0.59115 0.59045 -0.2534 0.0012 1.0000 47.500 0.8213 0.59455 0.59386 -0.2551 0.0010 1.0000 48.000 0.8154 0.59739 0.59672 -0.2567 0.0008 1.0000 48.500 0.8090 0.59952 0.59888 -0.2584 0.0007 1.0000 50.000 0.7895 0.60813 0.60755 -0.2629 0.0006 1.0000 50.500 0.7828 0.61079 0.61023 -0.2643 0.0006 1.0000 51.000 0.7759 0.61292 0.61239 -0.2657 0.0004 1.0000 51.500 0.7687 0.61460 0.61408 -0.2672 0.0003 1.0000 52.000 0.7613 0.61572 0.61523 -0.2686 0.0003 1.0000 52.500 0.7536 0.61629 0.61582 -0.2700 0.0002 1.0000 53.000 0.7455 0.61623 0.61577 -0.2716 0.0002 1.0000 53.500 0.7379 0.61810 0.61767 -0.2728 0.0001 1.0000 54.000 0.7302 0.61948 0.61906 -0.2739 0.0001 1.0000 54.500 0.7221 0.61970 0.61930 -0.2752 0.0001 1.0000 55.000 0.7137 0.61914 0.61876 -0.2765 0.0000 1.0000 56.000 0.6969 0.61940 0.61906 -0.2788 0.0000 1.0000 56.500 0.6882 0.61881 0.61849 -0.2799 0.0000 1.0000 57.000 0.6794 0.61761 0.61731 -0.2810 0.0000 1.0000 58.500 0.6524 0.61417 0.61392 -0.2842 0.0000 1.0000 59.000 0.6433 0.61270 0.61247 -0.2852 0.0000 1.0000 59.500 0.6340 0.61098 0.61076 -0.2861 0.0000 1.0000 60.000 0.6246 0.60884 0.60864 -0.2870 0.0000 1.0000