XFOIL Version 6.94 Calculated polar for: FX 84-W-097 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 0.2433 0.00650 0.00209 -0.0447 0.6880 0.9641 0.500 0.3248 0.00648 0.00196 -0.0499 0.6731 0.9930 1.000 0.3894 0.00659 0.00191 -0.0520 0.6575 1.0000 1.500 0.4417 0.00666 0.00191 -0.0514 0.6414 1.0000 2.000 0.4948 0.00685 0.00199 -0.0509 0.6257 1.0000 2.500 0.5491 0.00697 0.00207 -0.0507 0.6084 1.0000 3.000 0.6037 0.00716 0.00224 -0.0505 0.5901 1.0000 3.500 0.6586 0.00736 0.00239 -0.0503 0.5718 1.0000 4.000 0.7136 0.00756 0.00261 -0.0502 0.5511 1.0000 4.500 0.7680 0.00782 0.00281 -0.0499 0.5234 1.0000 5.000 0.8214 0.00813 0.00309 -0.0495 0.4812 1.0000 5.500 0.8740 0.00861 0.00344 -0.0491 0.4371 1.0000 6.000 0.9243 0.00937 0.00395 -0.0486 0.3611 1.0000 6.500 0.9693 0.01082 0.00485 -0.0476 0.2440 1.0000 7.000 1.0050 0.01345 0.00658 -0.0459 0.0820 1.0000 7.500 1.0453 0.01540 0.00826 -0.0443 0.0333 1.0000 8.000 1.0876 0.01696 0.00991 -0.0427 0.0239 1.0000 8.500 1.1156 0.01984 0.01297 -0.0395 0.0170 1.0000 9.000 1.1500 0.02175 0.01506 -0.0371 0.0159 1.0000 9.500 1.1757 0.02420 0.01772 -0.0337 0.0146 1.0000 10.000 1.2040 0.02604 0.01975 -0.0312 0.0130 1.0000 10.500 1.2245 0.02890 0.02279 -0.0283 0.0120 1.0000 11.000 1.2401 0.03272 0.02685 -0.0252 0.0111 1.0000 11.500 1.2529 0.03722 0.03166 -0.0223 0.0106 1.0000 12.000 1.2627 0.04224 0.03708 -0.0199 0.0109 1.0000 12.500 1.2603 0.04828 0.04350 -0.0181 0.0108 1.0000 13.000 1.2324 0.05778 0.05348 -0.0177 0.0100 1.0000 13.500 1.1951 0.06880 0.06498 -0.0198 0.0098 1.0000 14.000 1.1730 0.07862 0.07511 -0.0235 0.0099 1.0000 16.000 0.9427 0.18336 0.18111 -0.0802 0.0144 1.0000 16.500 0.9418 0.19651 0.19423 -0.0870 0.0137 1.0000 17.000 0.9431 0.20977 0.20743 -0.0932 0.0147 1.0000 17.500 0.9498 0.22091 0.21860 -0.0986 0.0143 1.0000 18.000 0.9590 0.23122 0.22890 -0.1037 0.0129 1.0000 18.500 0.9694 0.24083 0.23851 -0.1083 0.0120 1.0000 19.000 0.9809 0.24977 0.24746 -0.1125 0.0113 1.0000 19.500 0.9923 0.25820 0.25590 -0.1160 0.0107 1.0000 20.000 1.0042 0.26629 0.26401 -0.1190 0.0102 1.0000 20.500 1.0067 0.28108 0.27877 -0.1235 0.0096 1.0000 21.000 1.0167 0.29194 0.28965 -0.1277 0.0096 1.0000 21.500 1.0262 0.30352 0.30123 -0.1320 0.0096 1.0000 22.000 1.0348 0.31385 0.31158 -0.1358 0.0095 1.0000 22.500 1.0430 0.32514 0.32288 -0.1398 0.0095 1.0000 23.000 1.0506 0.33615 0.33393 -0.1437 0.0095 1.0000 23.500 1.0574 0.34705 0.34485 -0.1475 0.0094 1.0000 24.000 1.0623 0.35785 0.35568 -0.1509 0.0094 1.0000 24.500 1.0655 0.36940 0.36725 -0.1547 0.0093 1.0000 25.000 1.0673 0.38072 0.37858 -0.1583 0.0090 1.0000 25.500 1.0617 0.39102 0.38893 -0.1598 0.0091 1.0000 27.000 0.8566 0.35326 0.35148 -0.1334 0.0068 1.0000 27.500 0.8468 0.35352 0.35178 -0.1337 0.0078 1.0000 28.000 0.8414 0.35401 0.35232 -0.1349 0.0060 1.0000