XFOIL Version 6.94 Calculated polar for: HQ 3.5/10 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 ------- -------- --------- --------- -------- ------- ------- 0.000 0.4683 0.00870 0.00375 -0.1031 0.8134 0.8207 0.500 0.5222 0.00851 0.00348 -0.1022 0.7968 0.8460 1.000 0.5728 0.00829 0.00330 -0.1006 0.7788 0.8776 1.500 0.6302 0.00806 0.00318 -0.1005 0.7605 0.9475 2.000 0.6943 0.00810 0.00311 -0.1025 0.7399 1.0000 2.500 0.7502 0.00824 0.00314 -0.1026 0.7174 1.0000 3.000 0.8046 0.00841 0.00323 -0.1023 0.6907 1.0000 3.500 0.8567 0.00862 0.00340 -0.1015 0.6573 1.0000 4.000 0.9070 0.00893 0.00361 -0.1003 0.6137 1.0000 4.500 0.9416 0.00994 0.00386 -0.0960 0.4756 1.0000 5.000 0.9743 0.01140 0.00459 -0.0922 0.3490 1.0000 5.500 1.0139 0.01253 0.00538 -0.0897 0.2797 1.0000 6.000 1.0548 0.01356 0.00618 -0.0875 0.2291 1.0000 6.500 1.0979 0.01440 0.00693 -0.0855 0.1927 1.0000 7.000 1.1328 0.01579 0.00794 -0.0824 0.1213 1.0000 7.500 1.1540 0.01818 0.00970 -0.0774 0.0299 1.0000 8.000 1.1759 0.02013 0.01159 -0.0720 0.0047 1.0000 8.500 1.2037 0.02161 0.01330 -0.0676 0.0042 1.0000 9.000 1.2268 0.02347 0.01544 -0.0629 0.0040 1.0000 9.500 1.2433 0.02582 0.01808 -0.0577 0.0040 1.0000 10.000 1.2530 0.02869 0.02120 -0.0525 0.0040 1.0000 10.500 1.2578 0.03212 0.02485 -0.0475 0.0040 1.0000 11.000 1.2619 0.03599 0.02896 -0.0433 0.0041 1.0000 11.500 1.2650 0.04047 0.03370 -0.0399 0.0042 1.0000 12.000 1.2689 0.04563 0.03916 -0.0371 0.0045 1.0000 12.500 1.2731 0.05168 0.04561 -0.0349 0.0048 1.0000 13.000 1.2721 0.05871 0.05306 -0.0336 0.0052 1.0000 13.500 1.2638 0.06706 0.06181 -0.0336 0.0055 1.0000 15.000 1.0835 0.11357 0.11006 -0.0564 0.0057 1.0000 15.500 1.0385 0.13037 0.12742 -0.0688 0.0060 1.0000 16.000 1.0027 0.14644 0.14384 -0.0806 0.0060 1.0000 16.500 0.9633 0.16536 0.16309 -0.0937 0.0061 1.0000 17.000 0.8921 0.20029 0.19829 -0.1128 0.0069 1.0000 17.500 0.8900 0.21154 0.20955 -0.1183 0.0076 1.0000 19.500 0.8998 0.26390 0.26192 -0.1373 0.0177 1.0000 20.000 0.8980 0.27713 0.27514 -0.1440 0.0163 1.0000 20.500 0.9067 0.28595 0.28399 -0.1475 0.0153 1.0000 21.000 0.9152 0.29525 0.29331 -0.1507 0.0148 1.0000 21.500 0.9197 0.30681 0.30488 -0.1556 0.0135 1.0000 22.000 0.9278 0.31608 0.31417 -0.1590 0.0126 1.0000 22.500 0.9368 0.32510 0.32322 -0.1618 0.0122 1.0000 23.000 0.9411 0.33706 0.33519 -0.1665 0.0116 1.0000 23.500 0.9481 0.34731 0.34546 -0.1701 0.0106 1.0000 24.000 0.9552 0.35669 0.35487 -0.1733 0.0101 1.0000 24.500 0.9623 0.36664 0.36485 -0.1763 0.0098 1.0000 25.000 0.9673 0.37860 0.37681 -0.1805 0.0094 1.0000 25.500 0.9733 0.38937 0.38761 -0.1839 0.0088 1.0000 26.000 0.9789 0.39966 0.39793 -0.1872 0.0083 1.0000 26.500 0.9844 0.40968 0.40799 -0.1904 0.0079 1.0000 27.500 0.9942 0.43111 0.42947 -0.1967 0.0075 1.0000 28.000 0.9986 0.44281 0.44118 -0.2002 0.0073 1.0000 28.500 1.0029 0.45398 0.45239 -0.2034 0.0070 1.0000 29.000 1.0069 0.46488 0.46332 -0.2065 0.0067 1.0000 29.500 1.0104 0.47566 0.47413 -0.2096 0.0063 1.0000 30.000 1.0136 0.48651 0.48501 -0.2126 0.0061 1.0000 30.500 1.0162 0.49692 0.49545 -0.2156 0.0058 1.0000 31.500 1.0207 0.51941 0.51799 -0.2214 0.0056 1.0000 32.000 1.0232 0.53182 0.53042 -0.2243 0.0050 1.0000 32.500 1.0249 0.54303 0.54166 -0.2272 0.0046 1.0000 33.000 1.0261 0.55393 0.55259 -0.2300 0.0044 1.0000 33.500 1.0266 0.56449 0.56318 -0.2328 0.0041 1.0000 34.500 1.0269 0.58719 0.58592 -0.2381 0.0039 1.0000 35.000 1.0271 0.59843 0.59719 -0.2408 0.0038 1.0000 35.500 1.0268 0.60939 0.60818 -0.2434 0.0038 1.0000 36.000 1.0262 0.62028 0.61910 -0.2460 0.0037 1.0000 36.500 1.0253 0.63108 0.62993 -0.2485 0.0035 1.0000 37.000 1.0239 0.64174 0.64061 -0.2510 0.0033 1.0000 37.500 1.0223 0.65228 0.65118 -0.2534 0.0031 1.0000 38.000 1.0199 0.66194 0.66088 -0.2558 0.0031 1.0000 38.500 1.0173 0.67178 0.67075 -0.2582 0.0029 1.0000 39.000 1.0145 0.68140 0.68040 -0.2605 0.0028 1.0000 39.500 1.0112 0.69073 0.68976 -0.2628 0.0028 1.0000 40.000 1.0075 0.69957 0.69863 -0.2651 0.0027 1.0000 40.500 1.0035 0.70830 0.70739 -0.2673 0.0027 1.0000 41.000 0.9990 0.71668 0.71580 -0.2694 0.0026 1.0000 42.500 0.9845 0.74260 0.74179 -0.2757 0.0025 1.0000 43.000 0.9793 0.75032 0.74954 -0.2776 0.0025 1.0000 43.500 0.9742 0.75838 0.75762 -0.2796 0.0024 1.0000 44.000 0.9685 0.76558 0.76485 -0.2814 0.0024 1.0000 44.500 0.9626 0.77287 0.77217 -0.2832 0.0023 1.0000 45.000 0.9565 0.77980 0.77913 -0.2850 0.0022 1.0000 45.500 0.9496 0.78567 0.78502 -0.2867 0.0022 1.0000 46.000 0.9426 0.79118 0.79056 -0.2884 0.0022 1.0000 46.500 0.9353 0.79659 0.79600 -0.2901 0.0021 1.0000 47.000 0.9278 0.80161 0.80104 -0.2916 0.0020 1.0000 47.500 0.9200 0.80629 0.80575 -0.2932 0.0019 1.0000 48.000 0.9119 0.81014 0.80963 -0.2947 0.0019 1.0000 48.500 0.9036 0.81391 0.81343 -0.2962 0.0019 1.0000 49.000 0.8949 0.81683 0.81637 -0.2976 0.0018 1.0000 49.500 0.8862 0.81983 0.81939 -0.2991 0.0018 1.0000 50.000 0.8771 0.82214 0.82173 -0.3003 0.0018 1.0000 50.500 0.8680 0.82419 0.82380 -0.3016 0.0018 1.0000 51.000 0.8585 0.82562 0.82526 -0.3029 0.0017 1.0000 51.500 0.8489 0.82694 0.82660 -0.3041 0.0017 1.0000 52.000 0.8390 0.82740 0.82708 -0.3052 0.0016 1.0000 52.500 0.8291 0.82789 0.82760 -0.3063 0.0015 1.0000 53.000 0.8189 0.82773 0.82745 -0.3074 0.0015 1.0000 53.500 0.8083 0.82693 0.82668 -0.3084 0.0015 1.0000 54.000 0.7976 0.82600 0.82577 -0.3094 0.0014 1.0000