XFOIL Version 6.94 Calculated polar for: AH 93-W-145 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 0.4380 0.00954 0.00399 -0.0890 0.5642 0.8385 0.500 0.4915 0.00965 0.00415 -0.0882 0.5612 0.8673 1.000 0.5433 0.00980 0.00432 -0.0870 0.5573 0.8949 1.500 0.5858 0.00989 0.00448 -0.0834 0.5529 0.9273 2.000 0.6331 0.00992 0.00451 -0.0813 0.5481 0.9496 2.500 0.6849 0.00991 0.00447 -0.0803 0.5428 0.9708 3.000 0.7532 0.01017 0.00471 -0.0832 0.5369 0.9867 3.500 0.8257 0.01062 0.00519 -0.0874 0.5315 1.0000 4.000 0.8796 0.01074 0.00536 -0.0876 0.5279 1.0000 4.500 0.9378 0.01097 0.00564 -0.0886 0.5234 1.0000 5.000 0.9967 0.01110 0.00586 -0.0897 0.5169 1.0000 5.500 1.0554 0.01115 0.00588 -0.0905 0.5086 1.0000 6.000 1.1128 0.01151 0.00625 -0.0913 0.4983 1.0000 6.500 1.1694 0.01145 0.00636 -0.0917 0.4901 1.0000 7.000 1.2254 0.01139 0.00633 -0.0919 0.4775 1.0000 7.500 1.2799 0.01161 0.00659 -0.0920 0.4640 1.0000 8.000 1.3329 0.01163 0.00669 -0.0917 0.4433 1.0000 8.500 1.3825 0.01195 0.00705 -0.0909 0.4118 1.0000 9.000 1.4172 0.01313 0.00787 -0.0878 0.3351 1.0000 9.500 1.4267 0.01588 0.01001 -0.0815 0.2294 1.0000 10.000 1.4282 0.01856 0.01236 -0.0742 0.1682 1.0000 10.500 1.4270 0.02184 0.01545 -0.0683 0.1246 1.0000 11.000 1.4269 0.02606 0.01961 -0.0650 0.0931 1.0000 11.500 1.4226 0.03148 0.02495 -0.0630 0.0682 1.0000 12.000 1.4180 0.03712 0.03060 -0.0613 0.0497 1.0000 12.500 1.4096 0.04310 0.03663 -0.0595 0.0361 1.0000 13.000 1.3936 0.04999 0.04356 -0.0578 0.0263 1.0000 13.500 1.3934 0.05540 0.04912 -0.0567 0.0221 1.0000 14.000 1.3784 0.06268 0.05653 -0.0557 0.0184 1.0000 14.500 1.3668 0.07005 0.06412 -0.0551 0.0164 1.0000 15.000 1.3693 0.07583 0.07007 -0.0550 0.0152 1.0000 15.500 1.3678 0.08227 0.07668 -0.0552 0.0141 1.0000 16.000 1.3674 0.08849 0.08306 -0.0555 0.0133 1.0000 16.500 1.3632 0.09522 0.08998 -0.0560 0.0127 1.0000 17.000 1.3603 0.10192 0.09688 -0.0568 0.0122 1.0000 17.500 1.3579 0.10880 0.10395 -0.0580 0.0118 1.0000 18.000 1.3539 0.11593 0.11128 -0.0595 0.0115 1.0000 18.500 1.3505 0.12297 0.11852 -0.0612 0.0111 1.0000 19.000 1.3436 0.13076 0.12653 -0.0638 0.0108 1.0000 19.500 1.3355 0.13876 0.13478 -0.0668 0.0105 1.0000 20.000 1.3227 0.14794 0.14424 -0.0710 0.0104 1.0000 20.500 1.3041 0.15809 0.15469 -0.0769 0.0102 1.0000 21.000 1.2717 0.17235 0.16932 -0.0855 0.0099 1.0000 21.500 1.2528 0.18562 0.18285 -0.0936 0.0101 1.0000 22.000 1.2214 0.20377 0.20128 -0.1042 0.0101 1.0000 22.500 1.1765 0.22940 0.22720 -0.1177 0.0102 1.0000 24.500 1.0689 0.34446 0.34231 -0.1518 0.0125 1.0000 25.000 1.0719 0.35511 0.35298 -0.1548 0.0118 1.0000 25.500 1.0739 0.36512 0.36300 -0.1574 0.0112 1.0000 26.000 1.0743 0.37450 0.37243 -0.1594 0.0107 1.0000 26.500 1.0712 0.38356 0.38151 -0.1606 0.0104 1.0000 27.000 1.0582 0.39170 0.38969 -0.1599 0.0100 1.0000 28.500 0.8426 0.35671 0.35489 -0.1280 0.0096 1.0000 29.000 0.8336 0.35798 0.35618 -0.1283 0.0096 1.0000 29.500 0.8256 0.35953 0.35776 -0.1289 0.0095 1.0000 30.000 0.8190 0.36129 0.35955 -0.1297 0.0095 1.0000 30.500 0.8136 0.36330 0.36158 -0.1309 0.0095 1.0000 31.000 0.8086 0.36548 0.36380 -0.1322 0.0094 1.0000 31.500 0.8042 0.36814 0.36648 -0.1337 0.0093 1.0000 32.000 0.8029 0.37292 0.37130 -0.1361 0.0083 1.0000 32.500 0.8003 0.37540 0.37380 -0.1376 0.0059 1.0000 33.000 0.7980 0.37687 0.37529 -0.1390 0.0051 1.0000 33.500 0.7956 0.37795 0.37641 -0.1403 0.0047 1.0000 34.500 0.7838 0.38120 0.37968 -0.1415 0.0042 1.0000 35.000 0.7809 0.38393 0.38244 -0.1431 0.0042 1.0000 35.500 0.7782 0.38673 0.38527 -0.1447 0.0042 1.0000 36.000 0.7757 0.38948 0.38804 -0.1464 0.0042 1.0000 36.500 0.7732 0.39230 0.39089 -0.1482 0.0042 1.0000 37.000 0.7709 0.39527 0.39388 -0.1500 0.0042 1.0000 37.500 0.7687 0.39818 0.39681 -0.1519 0.0041 1.0000 38.000 0.7664 0.40118 0.39984 -0.1538 0.0041 1.0000 38.500 0.7643 0.40416 0.40284 -0.1558 0.0041 1.0000 39.000 0.7621 0.40714 0.40585 -0.1577 0.0041 1.0000 39.500 0.7601 0.41028 0.40902 -0.1597 0.0041 1.0000 40.000 0.7579 0.41326 0.41203 -0.1618 0.0041 1.0000 40.500 0.7557 0.41641 0.41520 -0.1638 0.0040 1.0000 41.000 0.7537 0.41973 0.41854 -0.1659 0.0040 1.0000 41.500 0.7518 0.42310 0.42194 -0.1681 0.0039 1.0000 42.000 0.7496 0.42629 0.42516 -0.1702 0.0038 1.0000 42.500 0.7478 0.42972 0.42862 -0.1722 0.0034 1.0000 43.000 0.7453 0.43289 0.43181 -0.1743 0.0024 1.0000 43.500 0.7425 0.43569 0.43463 -0.1764 0.0017 1.0000 44.000 0.7395 0.43821 0.43718 -0.1787 0.0014 1.0000 44.500 0.7359 0.43986 0.43886 -0.1808 0.0012 1.0000 45.500 0.7263 0.44480 0.44383 -0.1838 0.0010 1.0000 46.000 0.7229 0.44830 0.44735 -0.1860 0.0010 1.0000 46.500 0.7194 0.45197 0.45104 -0.1881 0.0010 1.0000 47.000 0.7157 0.45555 0.45464 -0.1903 0.0010 1.0000 47.500 0.7120 0.45899 0.45811 -0.1925 0.0010 1.0000 48.000 0.7083 0.46253 0.46167 -0.1946 0.0010 1.0000 48.500 0.7043 0.46583 0.46499 -0.1969 0.0010 1.0000 49.000 0.7003 0.46924 0.46843 -0.1991 0.0010 1.0000 49.500 0.6962 0.47264 0.47185 -0.2013 0.0010 1.0000 50.000 0.6920 0.47597 0.47521 -0.2036 0.0010 1.0000 50.500 0.6876 0.47942 0.47868 -0.2058 0.0010 1.0000 51.000 0.6832 0.48278 0.48205 -0.2080 0.0010 1.0000 51.500 0.6787 0.48617 0.48547 -0.2103 0.0010 1.0000 52.000 0.6740 0.48952 0.48884 -0.2126 0.0009 1.0000 52.500 0.6692 0.49288 0.49223 -0.2149 0.0009 1.0000 53.000 0.6644 0.49635 0.49572 -0.2171 0.0009 1.0000 53.500 0.6594 0.49975 0.49914 -0.2193 0.0009 1.0000 54.000 0.6545 0.50347 0.50287 -0.2214 0.0008 1.0000 54.500 0.6495 0.50718 0.50660 -0.2234 0.0006 1.0000 55.000 0.6440 0.51053 0.50998 -0.2256 0.0004 1.0000 55.500 0.6384 0.51388 0.51335 -0.2278 0.0002 1.0000 56.000 0.6326 0.51709 0.51658 -0.2301 0.0001 1.0000 56.500 0.6266 0.52020 0.51971 -0.2324 0.0001 1.0000 57.000 0.6206 0.52325 0.52277 -0.2348 0.0000 1.0000 57.500 0.6143 0.52617 0.52572 -0.2372 0.0000 1.0000 58.000 0.6075 0.52853 0.52810 -0.2396 0.0000 1.0000