XFOIL Version 6.96 Calculated polar for: MH 121 8.76% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.750 -0.4433 0.14787 0.14536 -0.0274 1.0000 0.0047 -12.500 -0.4393 0.14456 0.14206 -0.0281 1.0000 0.0048 -12.250 -0.4357 0.14116 0.13867 -0.0289 1.0000 0.0050 -7.750 -0.3486 0.06393 0.06172 -0.0749 0.9715 0.0022 -7.500 -0.3390 0.05365 0.05137 -0.0907 0.9599 0.0021 -7.250 -0.3280 0.04613 0.04363 -0.0993 0.9522 0.0020 -7.000 -0.3107 0.03916 0.03636 -0.1055 0.9465 0.0020 -6.750 -0.2868 0.03248 0.02927 -0.1105 0.9427 0.0020 -6.500 -0.2645 0.02663 0.02294 -0.1128 0.9369 0.0020 -6.250 -0.2368 0.02173 0.01747 -0.1148 0.9335 0.0020 -6.000 -0.2057 0.01899 0.01429 -0.1165 0.9311 0.0022 -5.750 -0.1801 0.01627 0.01112 -0.1167 0.9260 0.0024 -5.500 -0.1516 0.01426 0.00880 -0.1175 0.9222 0.0029 -5.250 -0.1207 0.01358 0.00795 -0.1187 0.9193 0.0035 -5.000 -0.0915 0.01320 0.00752 -0.1194 0.9158 0.0046 -4.750 -0.0634 0.01278 0.00701 -0.1197 0.9118 0.0056 -4.500 -0.0349 0.01166 0.00573 -0.1200 0.9080 0.0057 -4.250 -0.0054 0.01070 0.00462 -0.1206 0.9050 0.0057 -4.000 0.0212 0.01001 0.00380 -0.1206 0.9006 0.0058 -3.750 0.0496 0.00948 0.00312 -0.1208 0.8969 0.0060 -3.500 0.0792 0.00907 0.00251 -0.1212 0.8938 0.0070 -3.250 0.1080 0.00850 0.00210 -0.1217 0.8906 0.0625 -3.000 0.1335 0.00725 0.00176 -0.1225 0.8867 0.3239 -2.750 0.1615 0.00701 0.00166 -0.1228 0.8834 0.3920 -2.500 0.1903 0.00687 0.00159 -0.1232 0.8805 0.4382 -2.250 0.2190 0.00680 0.00154 -0.1235 0.8777 0.4683 -2.000 0.2463 0.00674 0.00153 -0.1235 0.8742 0.4994 -1.750 0.2741 0.00668 0.00152 -0.1236 0.8710 0.5272 -1.500 0.3027 0.00666 0.00145 -0.1239 0.8681 0.5438 -1.000 0.3589 0.00663 0.00143 -0.1242 0.8622 0.5643 -0.750 0.3866 0.00663 0.00144 -0.1243 0.8588 0.5733 -0.250 0.4437 0.00663 0.00147 -0.1247 0.8528 0.5926 0.000 0.4706 0.00662 0.00151 -0.1246 0.8484 0.6026 0.250 0.4980 0.00662 0.00154 -0.1246 0.8435 0.6129 0.500 0.5263 0.00662 0.00156 -0.1247 0.8385 0.6240 0.750 0.5526 0.00661 0.00161 -0.1244 0.8314 0.6358 1.000 0.5800 0.00661 0.00167 -0.1243 0.8242 0.6478 1.250 0.6065 0.00660 0.00171 -0.1240 0.8150 0.6609 1.500 0.6326 0.00659 0.00175 -0.1236 0.8039 0.6746 1.750 0.6583 0.00659 0.00179 -0.1231 0.7892 0.6894 2.000 0.6830 0.00660 0.00182 -0.1223 0.7677 0.7052 2.250 0.7071 0.00664 0.00187 -0.1214 0.7391 0.7224 2.500 0.7296 0.00677 0.00199 -0.1201 0.6973 0.7413 2.750 0.7445 0.00728 0.00215 -0.1173 0.6044 0.7617 3.000 0.7491 0.00852 0.00265 -0.1127 0.4357 0.7852 3.250 0.7494 0.01046 0.00341 -0.1080 0.1779 0.8129 3.500 0.7612 0.01157 0.00395 -0.1052 0.0473 0.8489 3.750 0.7778 0.01178 0.00421 -0.1028 0.0262 0.9077 4.000 0.8007 0.01224 0.00459 -0.1019 0.0031 1.0000 4.250 0.8250 0.01260 0.00501 -0.1012 0.0020 1.0000 4.500 0.8489 0.01301 0.00552 -0.1004 0.0018 1.0000 4.750 0.8721 0.01351 0.00619 -0.0995 0.0017 1.0000 5.000 0.8942 0.01414 0.00694 -0.0984 0.0017 1.0000 5.250 0.9153 0.01489 0.00781 -0.0971 0.0016 1.0000 5.500 0.9352 0.01583 0.00888 -0.0955 0.0016 1.0000 5.750 0.9544 0.01696 0.01014 -0.0938 0.0016 1.0000 6.000 0.9742 0.01829 0.01162 -0.0923 0.0016 1.0000 6.250 0.9955 0.01989 0.01340 -0.0909 0.0017 1.0000 6.500 1.0185 0.02192 0.01566 -0.0899 0.0017 1.0000 6.750 1.0416 0.02422 0.01823 -0.0888 0.0017 1.0000 7.000 1.0625 0.02708 0.02146 -0.0874 0.0018 1.0000 7.250 1.0789 0.03045 0.02523 -0.0852 0.0019 1.0000 7.500 1.0893 0.03443 0.02966 -0.0821 0.0019 1.0000 8.000 1.1080 0.04022 0.03600 -0.0767 0.0022 1.0000 8.250 1.1186 0.04238 0.03838 -0.0743 0.0023 1.0000 8.500 1.1267 0.04550 0.04185 -0.0713 0.0025 1.0000 8.750 1.1023 0.05764 0.05460 -0.0634 0.0037 1.0000 9.000 1.0881 0.06213 0.05932 -0.0590 0.0039 1.0000 9.250 1.0694 0.06580 0.06316 -0.0544 0.0041 1.0000 9.500 1.0495 0.06962 0.06714 -0.0509 0.0042 1.0000 9.750 1.0306 0.07368 0.07134 -0.0487 0.0042 1.0000 10.000 1.0104 0.07837 0.07616 -0.0479 0.0043 1.0000 10.250 0.9909 0.08367 0.08158 -0.0486 0.0042 1.0000