XFOIL Version 6.94 Calculated polar for: FX 74-080 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 0.5443 0.01007 0.00509 -0.1327 0.8329 1.0000 0.500 0.5910 0.01043 0.00538 -0.1313 0.8256 1.0000 1.000 0.6377 0.01070 0.00562 -0.1300 0.8171 1.0000 1.500 0.6911 0.01088 0.00576 -0.1298 0.8105 1.0000 2.000 0.7474 0.01123 0.00611 -0.1303 0.8041 1.0000 2.500 0.7913 0.01148 0.00650 -0.1284 0.7939 1.0000 3.000 0.8464 0.01144 0.00668 -0.1281 0.7846 1.0000 3.500 0.9045 0.00936 0.00450 -0.1260 0.7402 1.0000 4.000 0.8900 0.01078 0.00392 -0.1100 0.3728 1.0000 4.500 0.8704 0.01515 0.00650 -0.0968 0.0115 1.0000 5.000 0.8887 0.01731 0.00898 -0.0895 0.0081 1.0000 5.500 0.9112 0.01944 0.01124 -0.0838 0.0081 1.0000 6.000 0.9651 0.02421 0.01626 -0.0832 0.0099 1.0000 6.500 1.0769 0.03206 0.02500 -0.0868 0.0310 1.0000 7.000 1.1121 0.03884 0.03228 -0.0839 0.0252 1.0000 7.500 1.1403 0.04334 0.03741 -0.0779 0.0205 1.0000 8.000 1.1597 0.04998 0.04434 -0.0739 0.0183 1.0000 8.500 1.1507 0.06154 0.05650 -0.0675 0.0170 1.0000 9.000 1.1397 0.06733 0.06281 -0.0591 0.0168 1.0000 9.500 1.1215 0.06947 0.06545 -0.0494 0.0160 1.0000 10.000 1.0917 0.07475 0.07112 -0.0420 0.0154 1.0000 10.500 1.0552 0.08205 0.07871 -0.0379 0.0151 1.0000 11.000 1.0183 0.09058 0.08747 -0.0373 0.0156 1.0000 11.500 0.9773 0.10226 0.09928 -0.0401 0.0163 1.0000 12.000 0.9482 0.11376 0.11097 -0.0463 0.0163 1.0000 12.500 0.9242 0.12863 0.12591 -0.0548 0.0167 1.0000 13.000 0.9184 0.14411 0.14135 -0.0643 0.0166 1.0000 13.500 0.9190 0.15705 0.15427 -0.0718 0.0162 1.0000 14.000 0.9215 0.16876 0.16593 -0.0782 0.0155 1.0000 14.500 0.9263 0.17873 0.17594 -0.0835 0.0144 1.0000 15.000 0.9320 0.18815 0.18535 -0.0882 0.0138 1.0000 15.500 0.9399 0.19651 0.19369 -0.0927 0.0129 1.0000 16.000 0.9484 0.20467 0.20186 -0.0969 0.0121 1.0000 16.500 0.9579 0.21266 0.20985 -0.1009 0.0114 1.0000 17.000 0.9674 0.22131 0.21849 -0.1047 0.0109 1.0000 17.500 0.9787 0.22976 0.22696 -0.1071 0.0102 1.0000 18.000 0.9848 0.24202 0.23915 -0.1098 0.0096 1.0000 18.500 0.9956 0.25005 0.24724 -0.1141 0.0096 1.0000 19.000 1.0061 0.25987 0.25704 -0.1181 0.0095 1.0000 19.500 1.0165 0.26946 0.26666 -0.1221 0.0095 1.0000 20.000 1.0260 0.27835 0.27553 -0.1270 0.0094 1.0000 20.500 1.0353 0.28715 0.28434 -0.1317 0.0093 1.0000 21.000 1.0451 0.29641 0.29364 -0.1361 0.0091 1.0000 21.500 1.0565 0.30590 0.30311 -0.1408 0.0083 1.0000 22.000 1.0656 0.31529 0.31259 -0.1445 0.0081 1.0000 22.500 1.0746 0.32532 0.32263 -0.1482 0.0075 1.0000 23.000 1.0827 0.33521 0.33255 -0.1517 0.0073 1.0000 23.500 1.0899 0.34592 0.34327 -0.1551 0.0066 1.0000 24.000 1.0962 0.35625 0.35363 -0.1585 0.0066 1.0000 24.500 1.1015 0.36636 0.36378 -0.1617 0.0062 1.0000 25.000 1.1051 0.37714 0.37460 -0.1647 0.0061 1.0000 25.500 1.1071 0.38761 0.38512 -0.1675 0.0057 1.0000 26.000 1.1050 0.39849 0.39605 -0.1697 0.0056 1.0000 26.500 1.0928 0.40850 0.40611 -0.1704 0.0052 1.0000