XFOIL Version 6.94 Calculated polar for: FX 78-PK-188/20 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.500 0.2754 0.01791 0.01309 -0.0531 0.7120 0.7684 1.000 0.3256 0.01814 0.01331 -0.0534 0.7075 0.7724 1.500 0.3780 0.01835 0.01349 -0.0540 0.7040 0.7756 2.000 0.4339 0.01834 0.01347 -0.0549 0.7010 0.7784 2.500 0.4904 0.01802 0.01319 -0.0558 0.6985 0.7820 3.000 0.5485 0.01790 0.01309 -0.0568 0.6963 0.7849 3.500 0.6108 0.01768 0.01289 -0.0584 0.6933 0.7873 4.000 0.6542 0.01789 0.01319 -0.0573 0.6861 0.7901 4.500 0.6965 0.01821 0.01364 -0.0562 0.6784 0.7931 5.000 0.7697 0.01682 0.01228 -0.0590 0.6736 0.7958 5.500 0.8592 0.01440 0.00982 -0.0639 0.6670 0.7983 6.000 0.9240 0.01404 0.00950 -0.0661 0.6608 0.8005 6.500 0.9689 0.01345 0.00912 -0.0646 0.6476 0.8029 7.000 1.0335 0.01234 0.00798 -0.0660 0.6291 0.8045 7.500 1.0682 0.01221 0.00801 -0.0629 0.6028 0.8083 8.000 1.0761 0.01281 0.00832 -0.0549 0.5309 0.8123 8.500 1.0316 0.01705 0.01191 -0.0423 0.4148 0.8175 9.000 1.0337 0.01980 0.01451 -0.0368 0.3670 0.8213 9.500 1.0220 0.02347 0.01787 -0.0302 0.2938 0.8260 10.000 0.9990 0.02813 0.02185 -0.0232 0.1857 0.8293 10.500 0.9926 0.03207 0.02523 -0.0183 0.1022 0.8338 11.000 1.0160 0.03419 0.02735 -0.0162 0.0856 0.8378 11.500 1.0379 0.03654 0.02965 -0.0143 0.0664 0.8418 12.000 1.0634 0.03879 0.03204 -0.0128 0.0603 0.8469 12.500 1.0867 0.04130 0.03460 -0.0115 0.0500 0.8507 13.000 1.0935 0.04512 0.03810 -0.0088 0.0147 0.8561 13.500 1.1167 0.04763 0.04068 -0.0076 0.0127 0.8626 14.000 1.1389 0.05035 0.04360 -0.0067 0.0129 0.8697 15.000 1.1530 0.05913 0.05280 -0.0030 0.0066 0.8884 15.500 1.1608 0.06355 0.05749 -0.0019 0.0067 0.9047 16.000 1.1732 0.06832 0.06267 -0.0020 0.0075 0.9422 16.500 1.1801 0.07353 0.06810 -0.0025 0.0076 1.0000 17.000 1.1741 0.08033 0.07515 -0.0025 0.0065 1.0000 17.500 1.1720 0.08664 0.08176 -0.0027 0.0072 1.0000 18.000 1.1512 0.09621 0.09158 -0.0044 0.0053 1.0000 18.500 1.1504 0.10335 0.09896 -0.0066 0.0056 1.0000 19.000 1.1450 0.11132 0.10719 -0.0094 0.0058 1.0000 19.500 1.1130 0.12380 0.12004 -0.0143 0.0053 1.0000 20.000 1.0976 0.13424 0.13081 -0.0197 0.0056 1.0000 20.500 1.0739 0.14650 0.14342 -0.0267 0.0059 1.0000 21.000 1.0251 0.16489 0.16223 -0.0383 0.0059 1.0000 23.000 0.8609 0.28094 0.27870 -0.0833 0.0147 1.0000 23.500 0.8693 0.29224 0.28998 -0.0879 0.0124 1.0000 24.000 0.8804 0.30049 0.29823 -0.0916 0.0111 1.0000 24.500 0.8900 0.30997 0.30771 -0.0956 0.0108 1.0000 25.000 0.8998 0.31875 0.31653 -0.0993 0.0105 1.0000 26.000 0.9070 0.34489 0.34266 -0.1063 0.0096 1.0000 26.500 0.9126 0.35605 0.35383 -0.1100 0.0096 1.0000 27.000 0.9172 0.36678 0.36458 -0.1136 0.0096 1.0000 27.500 0.9203 0.37776 0.37558 -0.1169 0.0095 1.0000 28.000 0.9204 0.38866 0.38650 -0.1200 0.0095 1.0000 28.500 0.9145 0.39944 0.39731 -0.1222 0.0095 1.0000 29.500 0.7593 0.36843 0.36660 -0.1046 0.0095 1.0000 30.000 0.7507 0.36973 0.36793 -0.1061 0.0094 1.0000 30.500 0.7454 0.37089 0.36914 -0.1077 0.0094 1.0000 31.000 0.7410 0.37387 0.37215 -0.1101 0.0091 1.0000 31.500 0.7375 0.37600 0.37431 -0.1121 0.0089 1.0000 32.000 0.7347 0.37822 0.37656 -0.1140 0.0088 1.0000 32.500 0.7333 0.38038 0.37875 -0.1162 0.0078 1.0000 33.000 0.7324 0.38247 0.38087 -0.1184 0.0054 1.0000 33.500 0.7312 0.38435 0.38277 -0.1205 0.0050 1.0000 34.000 0.7284 0.38683 0.38530 -0.1226 0.0055 1.0000