XFOIL Version 6.94 Calculated polar for: MH 117 9.8% 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 0.3158 0.00635 0.00201 -0.0687 0.7228 0.8742 0.500 0.3851 0.00629 0.00192 -0.0707 0.7016 0.9792 1.000 0.4508 0.00640 0.00192 -0.0728 0.6818 1.0000 1.500 0.5034 0.00652 0.00193 -0.0719 0.6606 1.0000 2.000 0.5565 0.00674 0.00204 -0.0712 0.6378 1.0000 2.500 0.6105 0.00687 0.00214 -0.0706 0.6165 1.0000 3.000 0.6635 0.00712 0.00228 -0.0699 0.5883 1.0000 3.500 0.7168 0.00734 0.00244 -0.0691 0.5582 1.0000 4.000 0.7698 0.00763 0.00267 -0.0684 0.5225 1.0000 4.500 0.8208 0.00806 0.00297 -0.0674 0.4699 1.0000 5.000 0.8685 0.00880 0.00336 -0.0659 0.3923 1.0000 5.500 0.9165 0.00961 0.00390 -0.0646 0.3237 1.0000 6.000 0.9631 0.01059 0.00459 -0.0632 0.2537 1.0000 6.500 1.0089 0.01165 0.00537 -0.0617 0.1924 1.0000 7.000 1.0545 0.01272 0.00632 -0.0603 0.1421 1.0000 7.500 1.0988 0.01389 0.00731 -0.0586 0.1015 1.0000 8.000 1.1417 0.01513 0.00846 -0.0568 0.0735 1.0000 8.500 1.1823 0.01653 0.00989 -0.0545 0.0568 1.0000 9.000 1.2207 0.01801 0.01135 -0.0521 0.0421 1.0000 9.500 1.2613 0.01914 0.01264 -0.0500 0.0355 1.0000 10.000 1.2864 0.02142 0.01498 -0.0459 0.0226 1.0000 10.500 1.3254 0.02219 0.01579 -0.0438 0.0169 1.0000 11.000 1.3258 0.02567 0.01959 -0.0368 0.0106 1.0000 11.500 1.3445 0.02799 0.02213 -0.0331 0.0090 1.0000 12.000 1.3478 0.03183 0.02629 -0.0288 0.0076 1.0000 12.500 1.3474 0.03649 0.03128 -0.0257 0.0070 1.0000 13.000 1.3432 0.04197 0.03710 -0.0238 0.0064 1.0000 13.500 1.3334 0.04859 0.04404 -0.0231 0.0057 1.0000 14.000 1.3157 0.05695 0.05278 -0.0240 0.0056 1.0000 14.500 1.2892 0.06734 0.06358 -0.0269 0.0055 1.0000 15.000 1.2617 0.07881 0.07541 -0.0315 0.0055 1.0000 15.500 1.2230 0.09422 0.09123 -0.0395 0.0057 1.0000 16.000 1.1834 0.11158 0.10895 -0.0497 0.0058 1.0000 16.500 1.1399 0.13130 0.12897 -0.0619 0.0058 1.0000 17.000 1.0689 0.15972 0.15771 -0.0795 0.0066 1.0000 17.500 0.9823 0.20250 0.20037 -0.0996 0.0080 1.0000 18.000 0.9749 0.22055 0.21839 -0.1068 0.0082 1.0000 18.500 0.9755 0.23560 0.23341 -0.1124 0.0086 1.0000 19.000 0.9784 0.24961 0.24741 -0.1174 0.0094 1.0000 19.500 0.9766 0.26646 0.26425 -0.1215 0.0108 1.0000 20.000 0.9832 0.27889 0.27669 -0.1256 0.0108 1.0000 21.000 0.9936 0.30372 0.30155 -0.1332 0.0107 1.0000 21.500 0.9961 0.31613 0.31403 -0.1366 0.0107 1.0000 22.000 0.9949 0.32807 0.32600 -0.1396 0.0107 1.0000 22.500 0.9823 0.33871 0.33669 -0.1413 0.0106 1.0000 23.000 0.8820 0.32081 0.31899 -0.1323 0.0106 1.0000 23.500 0.8693 0.32255 0.32078 -0.1331 0.0106 1.0000 24.000 0.8612 0.32466 0.32293 -0.1344 0.0105 1.0000 24.500 0.8550 0.32732 0.32562 -0.1360 0.0104 1.0000 25.000 0.8503 0.33007 0.32840 -0.1377 0.0103 1.0000 25.500 0.8487 0.33361 0.33197 -0.1401 0.0098 1.0000 26.000 0.8476 0.33700 0.33539 -0.1422 0.0091 1.0000 26.500 0.8462 0.34038 0.33880 -0.1441 0.0080 1.0000 27.000 0.8441 0.34346 0.34190 -0.1458 0.0074 1.0000 27.500 0.8432 0.34673 0.34520 -0.1481 0.0068 1.0000 28.000 0.8417 0.34980 0.34830 -0.1498 0.0058 1.0000