XFOIL Version 6.94 Calculated polar for: S4022 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 0.6718 0.00945 0.00409 -0.1641 0.8283 0.7304 0.500 0.7281 0.00948 0.00408 -0.1639 0.8118 0.7498 1.000 0.7824 0.00953 0.00412 -0.1634 0.7942 0.7688 1.500 0.8350 0.00960 0.00420 -0.1626 0.7752 0.7891 2.000 0.8864 0.00965 0.00429 -0.1614 0.7551 0.8099 2.500 0.9372 0.00972 0.00439 -0.1601 0.7339 0.8340 3.000 0.9845 0.00979 0.00452 -0.1580 0.7111 0.8630 3.500 1.0255 0.00979 0.00463 -0.1545 0.6858 0.9064 4.000 1.0733 0.00982 0.00468 -0.1528 0.6568 1.0000 4.500 1.1259 0.01019 0.00496 -0.1523 0.6246 1.0000 5.000 1.1735 0.01066 0.00535 -0.1507 0.5873 1.0000 5.500 1.2178 0.01120 0.00582 -0.1485 0.5462 1.0000 6.000 1.2582 0.01189 0.00638 -0.1455 0.4990 1.0000 6.500 1.2943 0.01274 0.00708 -0.1418 0.4450 1.0000 7.000 1.3219 0.01387 0.00800 -0.1366 0.3784 1.0000 7.500 1.3406 0.01543 0.00917 -0.1301 0.2967 1.0000 8.000 1.3585 0.01732 0.01068 -0.1239 0.2179 1.0000 8.500 1.3737 0.01959 0.01253 -0.1178 0.1445 1.0000 9.000 1.3922 0.02178 0.01452 -0.1126 0.0977 1.0000 9.500 1.4128 0.02391 0.01660 -0.1079 0.0697 1.0000 10.000 1.4254 0.02677 0.01931 -0.1027 0.0373 1.0000 10.500 1.4294 0.03057 0.02317 -0.0967 0.0205 1.0000 11.000 1.4277 0.03513 0.02794 -0.0911 0.0165 1.0000 11.500 1.4390 0.03885 0.03192 -0.0876 0.0145 1.0000 12.000 1.4430 0.04357 0.03693 -0.0842 0.0133 1.0000 12.500 1.4442 0.04897 0.04257 -0.0814 0.0124 1.0000 13.000 1.4414 0.05540 0.04927 -0.0791 0.0116 1.0000 13.500 1.4374 0.06297 0.05721 -0.0770 0.0111 1.0000 14.000 1.4325 0.07136 0.06606 -0.0758 0.0107 1.0000 14.500 1.4264 0.07935 0.07446 -0.0763 0.0104 1.0000 15.000 1.4144 0.08874 0.08427 -0.0782 0.0101 1.0000 15.500 1.3957 0.09985 0.09581 -0.0817 0.0098 1.0000 16.000 1.3713 0.11284 0.10922 -0.0872 0.0097 1.0000 16.500 1.3432 0.12753 0.12432 -0.0951 0.0096 1.0000 17.000 1.3099 0.14471 0.14190 -0.1056 0.0098 1.0000 17.500 1.2736 0.16463 0.16217 -0.1190 0.0100 1.0000 18.000 1.2212 0.19207 0.18988 -0.1373 0.0108 1.0000