XFOIL Version 6.96 Calculated polar for: HQ 3.0/13 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.500 -0.6834 0.10018 0.09797 -0.0474 1.0000 0.0052 -15.250 -0.7287 0.08771 0.08541 -0.0541 1.0000 0.0051 -15.000 -0.8635 0.05768 0.05498 -0.0728 1.0000 0.0049 -14.750 -0.8859 0.04987 0.04701 -0.0784 1.0000 0.0049 -14.500 -0.9124 0.04277 0.03973 -0.0833 1.0000 0.0049 -14.250 -0.9230 0.03856 0.03539 -0.0856 1.0000 0.0049 -14.000 -0.9327 0.03493 0.03162 -0.0871 1.0000 0.0049 -13.750 -0.9287 0.03306 0.02968 -0.0873 1.0000 0.0050 -13.500 -0.9398 0.03025 0.02674 -0.0871 1.0000 0.0050 -13.000 -0.9223 0.02672 0.02300 -0.0889 0.9877 0.0050 -12.750 -0.8995 0.02511 0.02125 -0.0912 0.9822 0.0051 -12.500 -0.8788 0.02307 0.01902 -0.0935 0.9746 0.0053 -12.250 -0.8547 0.02153 0.01733 -0.0953 0.9673 0.0055 -12.000 -0.8295 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0.00251 -0.0845 0.3289 0.6777 4.000 0.8315 0.00872 0.00269 -0.0840 0.3056 0.6860 4.250 0.8563 0.00894 0.00286 -0.0835 0.2894 0.6941 4.750 0.9059 0.00937 0.00323 -0.0825 0.2605 0.7119 5.000 0.9307 0.00957 0.00342 -0.0820 0.2486 0.7217 5.250 0.9553 0.00978 0.00361 -0.0815 0.2373 0.7322 5.500 0.9793 0.01000 0.00383 -0.0809 0.2244 0.7427 5.750 1.0029 0.01025 0.00405 -0.0803 0.2102 0.7533 6.000 1.0260 0.01051 0.00428 -0.0795 0.1962 0.7655 6.250 1.0487 0.01079 0.00453 -0.0787 0.1829 0.7783 6.500 1.0705 0.01110 0.00481 -0.0778 0.1672 0.7916 6.750 1.0916 0.01142 0.00510 -0.0767 0.1518 0.8053 7.000 1.1127 0.01173 0.00539 -0.0756 0.1398 0.8204 7.250 1.1329 0.01203 0.00569 -0.0744 0.1275 0.8392 7.500 1.1524 0.01228 0.00598 -0.0729 0.1173 0.8655 7.750 1.1775 0.01254 0.00636 -0.0728 0.1028 1.0000 8.000 1.1957 0.01301 0.00674 -0.0714 0.0887 1.0000 8.250 1.2126 0.01345 0.00712 -0.0696 0.0773 1.0000 8.500 1.2268 0.01397 0.00756 -0.0674 0.0643 1.0000 8.750 1.2419 0.01445 0.00800 -0.0653 0.0551 1.0000 9.000 1.2570 0.01494 0.00846 -0.0634 0.0472 1.0000 9.250 1.2697 0.01558 0.00903 -0.0611 0.0371 1.0000 9.500 1.2843 0.01613 0.00955 -0.0592 0.0314 1.0000 9.750 1.2964 0.01683 0.01021 -0.0570 0.0233 1.0000 10.000 1.3100 0.01746 0.01082 -0.0551 0.0190 1.0000 10.250 1.3222 0.01820 0.01154 -0.0531 0.0139 1.0000 10.500 1.3287 0.01930 0.01260 -0.0505 0.0046 1.0000 10.750 1.3408 0.02010 0.01343 -0.0486 0.0038 1.0000 11.000 1.3543 0.02083 0.01419 -0.0471 0.0034 1.0000 11.250 1.3678 0.02158 0.01499 -0.0456 0.0032 1.0000 11.500 1.3810 0.02237 0.01582 -0.0441 0.0031 1.0000 11.750 1.3934 0.02323 0.01675 -0.0426 0.0030 1.0000 12.000 1.4056 0.02414 0.01770 -0.0412 0.0029 1.0000 12.250 1.4162 0.02517 0.01880 -0.0397 0.0027 1.0000 12.500 1.4263 0.02628 0.01997 -0.0383 0.0026 1.0000 12.750 1.4364 0.02742 0.02117 -0.0369 0.0026 1.0000 13.000 1.4448 0.02871 0.02253 -0.0356 0.0025 1.0000 13.250 1.4523 0.03012 0.02401 -0.0342 0.0024 1.0000 13.500 1.4596 0.03159 0.02555 -0.0330 0.0023 1.0000 13.750 1.4634 0.03340 0.02746 -0.0316 0.0022 1.0000 14.000 1.4713 0.03489 0.02902 -0.0307 0.0021 1.0000 14.250 1.4784 0.03650 0.03069 -0.0298 0.0021 1.0000 14.500 1.4836 0.03835 0.03261 -0.0290 0.0021 1.0000 14.750 1.4872 0.04040 0.03475 -0.0282 0.0020 1.0000 15.000 1.4904 0.04257 0.03701 -0.0275 0.0019 1.0000 15.250 1.4938 0.04480 0.03931 -0.0271 0.0019 1.0000 15.500 1.4960 0.04724 0.04183 -0.0267 0.0019 1.0000 15.750 1.4960 0.05000 0.04469 -0.0265 0.0019 1.0000 16.000 1.4953 0.05297 0.04776 -0.0265 0.0018 1.0000 16.250 1.4944 0.05607 0.05096 -0.0267 0.0018 1.0000 16.500 1.4921 0.05945 0.05444 -0.0271 0.0018 1.0000 16.750 1.4867 0.06338 0.05849 -0.0277 0.0018 1.0000 17.000 1.4833 0.06719 0.06240 -0.0286 0.0017 1.0000 17.250 1.4766 0.07161 0.06693 -0.0298 0.0017 1.0000 17.500 1.4680 0.07646 0.07190 -0.0313 0.0017 1.0000 17.750 1.4583 0.08169 0.07725 -0.0332 0.0017 1.0000 18.000 1.4501 0.08682 0.08250 -0.0352 0.0017 1.0000 18.250 1.4375 0.09285 0.08866 -0.0378 0.0016 1.0000 18.500 1.4249 0.09904 0.09498 -0.0405 0.0017 1.0000 18.750 1.4100 0.10583 0.10190 -0.0437 0.0016 1.0000 19.000 1.3924 0.11331 0.10952 -0.0475 0.0016 1.0000 19.250 1.3764 0.12060 0.11694 -0.0512 0.0016 1.0000