XFOIL Version 6.94 Calculated polar for: PSU 94-097 (AIAA 2001-2478) 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 0.4860 0.00854 0.00376 -0.1078 0.7747 1.0000 0.500 0.5447 0.00861 0.00366 -0.1084 0.7622 1.0000 1.000 0.6023 0.00889 0.00370 -0.1087 0.7451 1.0000 1.500 0.6602 0.00891 0.00369 -0.1091 0.7342 1.0000 2.000 0.7175 0.00894 0.00365 -0.1093 0.7186 1.0000 2.500 0.7745 0.00921 0.00379 -0.1094 0.6999 1.0000 3.000 0.8313 0.00922 0.00388 -0.1095 0.6857 1.0000 3.500 0.8876 0.00929 0.00390 -0.1094 0.6650 1.0000 4.000 0.9436 0.00947 0.00414 -0.1094 0.6437 1.0000 4.500 0.9984 0.00961 0.00422 -0.1090 0.6126 1.0000 5.000 1.0526 0.00985 0.00453 -0.1087 0.5754 1.0000 5.500 1.1032 0.01037 0.00484 -0.1076 0.5156 1.0000 6.000 1.1507 0.01124 0.00546 -0.1063 0.4382 1.0000 6.500 1.1941 0.01252 0.00637 -0.1046 0.3557 1.0000 7.000 1.2348 0.01401 0.00751 -0.1026 0.2829 1.0000 7.500 1.2769 0.01532 0.00867 -0.1008 0.2289 1.0000 8.000 1.3152 0.01683 0.00995 -0.0985 0.1759 1.0000 8.500 1.3498 0.01853 0.01145 -0.0958 0.1290 1.0000 9.000 1.3819 0.02027 0.01331 -0.0926 0.0901 1.0000 9.500 1.3938 0.02307 0.01589 -0.0865 0.0504 1.0000 10.000 1.3994 0.02648 0.01939 -0.0801 0.0331 1.0000 10.500 1.4149 0.02929 0.02247 -0.0758 0.0262 1.0000 11.000 1.4217 0.03312 0.02651 -0.0713 0.0214 1.0000 11.500 1.4163 0.03828 0.03199 -0.0665 0.0166 1.0000 12.000 1.4309 0.04163 0.03549 -0.0646 0.0109 1.0000 12.500 1.4127 0.04888 0.04308 -0.0607 0.0088 1.0000 13.000 1.3807 0.05832 0.05309 -0.0565 0.0078 1.0000 13.500 1.3511 0.06808 0.06336 -0.0547 0.0074 1.0000 14.000 1.3342 0.07695 0.07264 -0.0557 0.0073 1.0000 14.500 1.3091 0.08791 0.08402 -0.0586 0.0072 1.0000 15.000 1.2790 0.10080 0.09731 -0.0641 0.0071 1.0000 15.500 1.2442 0.11577 0.11265 -0.0722 0.0072 1.0000 16.000 1.2047 0.13281 0.13004 -0.0830 0.0073 1.0000 18.000 1.1037 0.20949 0.20730 -0.1232 0.0088 1.0000 18.500 1.0704 0.24131 0.23898 -0.1327 0.0112 1.0000 19.000 1.0652 0.25822 0.25584 -0.1376 0.0127 1.0000 19.500 1.0627 0.27240 0.27001 -0.1409 0.0154 1.0000 21.000 1.0483 0.31190 0.30951 -0.1464 0.0173 1.0000 21.500 1.0394 0.32233 0.31996 -0.1475 0.0172 1.0000 23.000 0.9150 0.31776 0.31551 -0.1343 0.0148 1.0000 23.500 0.9008 0.31971 0.31749 -0.1338 0.0119 1.0000 24.000 0.8891 0.32148 0.31929 -0.1334 0.0106 1.0000 24.500 0.8800 0.32334 0.32118 -0.1333 0.0097 1.0000 25.000 0.8727 0.32503 0.32290 -0.1332 0.0090 1.0000 25.500 0.8669 0.32625 0.32416 -0.1329 0.0083 1.0000