XFOIL Version 6.94 Calculated polar for: EPPLER STE 87(-3)-914 AIRFOIL 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 ------- -------- --------- --------- -------- ------- ------- 0.000 0.5760 0.01407 0.00978 -0.1465 0.8485 0.7794 1.500 0.7214 0.01301 0.00881 -0.1407 0.8172 0.8150 2.500 0.8210 0.01216 0.00805 -0.1374 0.7846 0.8356 3.000 0.8798 0.01125 0.00712 -0.1366 0.7596 0.8559 3.500 0.9470 0.01069 0.00634 -0.1382 0.7126 0.8662 4.000 0.9885 0.01115 0.00646 -0.1355 0.6454 0.8713 4.500 1.0016 0.01244 0.00725 -0.1277 0.5534 0.8764 5.000 1.0137 0.01407 0.00837 -0.1203 0.4561 0.8814 5.500 1.0453 0.01521 0.00923 -0.1168 0.4001 0.8847 6.000 1.0725 0.01666 0.01029 -0.1127 0.3276 0.8884 6.500 1.1095 0.01763 0.01109 -0.1103 0.2903 0.8912 7.000 1.1473 0.01851 0.01191 -0.1081 0.2643 0.8944 7.500 1.1824 0.01958 0.01286 -0.1054 0.2321 0.8979 8.000 1.2198 0.02056 0.01380 -0.1032 0.2110 0.9022 8.500 1.2545 0.02175 0.01488 -0.1008 0.1807 0.9062 9.000 1.2832 0.02331 0.01622 -0.0975 0.1372 0.9101 9.500 1.2877 0.02635 0.01867 -0.0910 0.0483 0.9156 10.000 1.2954 0.02940 0.02149 -0.0852 0.0048 0.9221 11.000 1.3430 0.03321 0.02563 -0.0782 0.0035 0.9433 11.500 1.3619 0.03537 0.02801 -0.0746 0.0034 0.9981 12.000 1.3823 0.03820 0.03103 -0.0719 0.0032 0.9981 12.500 1.3977 0.04152 0.03455 -0.0690 0.0032 0.9981 13.000 1.4074 0.04546 0.03870 -0.0661 0.0031 0.9981 13.500 1.4113 0.05015 0.04361 -0.0633 0.0031 0.9981 14.000 1.4097 0.05571 0.04941 -0.0610 0.0031 0.9981 14.500 1.4021 0.06228 0.05622 -0.0593 0.0031 0.9981 15.000 1.3896 0.06994 0.06414 -0.0585 0.0031 0.9981 15.500 1.3730 0.07861 0.07307 -0.0588 0.0031 0.9981 16.000 1.3528 0.08827 0.08298 -0.0602 0.0031 0.9981 16.500 1.3318 0.09845 0.09342 -0.0625 0.0031 0.9981 17.000 1.3115 0.10876 0.10395 -0.0654 0.0031 0.9981 17.500 1.2938 0.11884 0.11425 -0.0688 0.0032 0.9981 18.000 1.2806 0.12827 0.12387 -0.0723 0.0032 0.9981 18.500 1.2707 0.13715 0.13293 -0.0760 0.0032 0.9981 19.000 1.2645 0.14551 0.14145 -0.0798 0.0033 0.9981 19.500 1.2602 0.15362 0.14974 -0.0838 0.0033 0.9981 20.000 1.2558 0.16185 0.15815 -0.0883 0.0033 0.9981 20.500 1.2511 0.17037 0.16687 -0.0933 0.0034 0.9981 21.000 1.2449 0.17949 0.17620 -0.0990 0.0034 0.9981 21.500 1.2374 0.18927 0.18619 -0.1056 0.0035 0.9981 22.000 1.2282 0.19974 0.19688 -0.1129 0.0035 0.9981 22.500 1.2224 0.21061 0.20796 -0.1209 0.0036 0.9981 23.000 1.2077 0.22503 0.22268 -0.1314 0.0037 0.9981