XFOIL Version 6.96 Calculated polar for: MH 106 13.07% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.8313 0.05284 0.04823 -0.0259 1.0000 0.0243 -10.000 -0.8427 0.04922 0.04442 -0.0234 1.0000 0.0236 -9.750 -0.8494 0.04566 0.04060 -0.0209 1.0000 0.0229 -9.500 -0.8511 0.04240 0.03702 -0.0185 1.0000 0.0226 -9.250 -0.8472 0.03952 0.03383 -0.0162 1.0000 0.0225 -9.000 -0.8393 0.03685 0.03083 -0.0141 1.0000 0.0227 -8.750 -0.8280 0.03442 0.02810 -0.0121 1.0000 0.0230 -8.500 -0.8138 0.03180 0.02516 -0.0103 1.0000 0.0228 -8.250 -0.7965 0.02932 0.02237 -0.0087 1.0000 0.0225 -8.000 -0.7768 0.02721 0.02004 -0.0074 1.0000 0.0224 -7.750 -0.7559 0.02535 0.01802 -0.0061 1.0000 0.0226 -7.500 -0.7348 0.02375 0.01631 -0.0049 1.0000 0.0231 -7.250 -0.7143 0.02233 0.01481 -0.0035 1.0000 0.0238 -7.000 -0.6943 0.02115 0.01355 -0.0020 1.0000 0.0250 -6.750 -0.6794 0.01952 0.01192 0.0001 1.0000 0.0264 -6.500 -0.6633 0.01839 0.01081 0.0020 1.0000 0.0292 -6.250 -0.6447 0.01759 0.00995 0.0036 1.0000 0.0339 -6.000 -0.6302 0.01642 0.00878 0.0059 1.0000 0.0423 -5.750 -0.6224 0.01456 0.00730 0.0093 1.0000 0.0903 -5.500 -0.6159 0.01303 0.00667 0.0123 1.0000 0.2347 -5.250 -0.5883 0.01266 0.00647 0.0118 0.9924 0.2905 -5.000 -0.5424 0.01236 0.00626 0.0078 0.9692 0.3381 -4.750 -0.4987 0.01213 0.00603 0.0046 0.9384 0.3717 -4.500 -0.4597 0.01195 0.00581 0.0026 0.9026 0.4022 -4.250 -0.4308 0.01182 0.00561 0.0028 0.8659 0.4266 -4.000 -0.4069 0.01171 0.00538 0.0041 0.8318 0.4462 -3.750 -0.3835 0.01162 0.00515 0.0053 0.8021 0.4658 -3.500 -0.3600 0.01148 0.00495 0.0066 0.7757 0.4850 -3.250 -0.3360 0.01135 0.00475 0.0076 0.7517 0.5062 -3.000 -0.3118 0.01122 0.00457 0.0086 0.7298 0.5289 -2.750 -0.2875 0.01110 0.00441 0.0096 0.7091 0.5541 -2.500 -0.2634 0.01098 0.00427 0.0106 0.6905 0.5809 -2.250 -0.2390 0.01085 0.00416 0.0116 0.6726 0.6105 -2.000 -0.2145 0.01074 0.00407 0.0125 0.6559 0.6431 -1.750 -0.1900 0.01064 0.00402 0.0135 0.6407 0.6772 -1.500 -0.1652 0.01056 0.00399 0.0145 0.6266 0.7132 -1.250 -0.1400 0.01052 0.00398 0.0155 0.6134 0.7497 -1.000 -0.1137 0.01052 0.00400 0.0163 0.6010 0.7851 -0.750 -0.0860 0.01055 0.00407 0.0169 0.5888 0.8189 -0.500 -0.0562 0.01065 0.00417 0.0170 0.5778 0.8494 -0.250 -0.0226 0.01083 0.00430 0.0164 0.5677 0.8748 0.000 0.0119 0.01103 0.00442 0.0155 0.5576 0.8971 0.250 0.0507 0.01127 0.00460 0.0137 0.5476 0.9137 0.500 0.0901 0.01155 0.00478 0.0118 0.5392 0.9279 0.750 0.1299 0.01179 0.00495 0.0097 0.5302 0.9404 1.000 0.1778 0.01205 0.00514 0.0058 0.5217 0.9475 1.250 0.2200 0.01227 0.00527 0.0031 0.5141 0.9574 1.500 0.2624 0.01247 0.00543 0.0002 0.5061 0.9672 1.750 0.3085 0.01261 0.00549 -0.0036 0.4990 0.9746 2.000 0.3521 0.01274 0.00563 -0.0069 0.4914 0.9836 2.250 0.3978 0.01281 0.00563 -0.0107 0.4843 0.9913 2.500 0.4438 0.01283 0.00566 -0.0147 0.4768 0.9986 2.750 0.4705 0.01286 0.00566 -0.0148 0.4706 1.0000 3.000 0.4924 0.01295 0.00574 -0.0140 0.4652 1.0000 3.250 0.5144 0.01301 0.00583 -0.0132 0.4587 1.0000 3.500 0.5370 0.01313 0.00589 -0.0123 0.4535 1.0000 3.750 0.5592 0.01322 0.00607 -0.0115 0.4467 1.0000 4.000 0.5818 0.01333 0.00615 -0.0106 0.4406 1.0000 4.250 0.6044 0.01348 0.00635 -0.0098 0.4341 1.0000 4.500 0.6271 0.01359 0.00647 -0.0089 0.4271 1.0000 4.750 0.6499 0.01375 0.00665 -0.0080 0.4205 1.0000 5.000 0.6727 0.01386 0.00680 -0.0071 0.4131 1.0000 5.250 0.6955 0.01401 0.00699 -0.0062 0.4058 1.0000 5.500 0.7184 0.01413 0.00714 -0.0053 0.3979 1.0000 5.750 0.7412 0.01428 0.00735 -0.0044 0.3900 1.0000 6.000 0.7643 0.01439 0.00745 -0.0035 0.3816 1.0000 6.250 0.7868 0.01452 0.00770 -0.0025 0.3723 1.0000 6.500 0.8096 0.01464 0.00783 -0.0015 0.3632 1.0000 6.750 0.8322 0.01472 0.00798 -0.0005 0.3528 1.0000 7.000 0.8544 0.01482 0.00817 0.0005 0.3410 1.0000 7.250 0.8766 0.01491 0.00835 0.0015 0.3285 1.0000 7.500 0.8985 0.01502 0.00854 0.0026 0.3143 1.0000 7.750 0.9202 0.01515 0.00873 0.0037 0.2982 1.0000 8.000 0.9410 0.01535 0.00893 0.0048 0.2796 1.0000 8.250 0.9613 0.01565 0.00927 0.0060 0.2565 1.0000 8.500 0.9797 0.01615 0.00971 0.0074 0.2324 1.0000 8.750 0.9961 0.01684 0.01032 0.0090 0.2085 1.0000 9.000 1.0121 0.01760 0.01103 0.0105 0.1858 1.0000 9.250 1.0260 0.01850 0.01184 0.0123 0.1663 1.0000 9.500 1.0402 0.01936 0.01270 0.0141 0.1487 1.0000 9.750 1.0529 0.02030 0.01362 0.0159 0.1334 1.0000 10.000 1.0641 0.02130 0.01461 0.0179 0.1203 1.0000 10.250 1.0736 0.02237 0.01567 0.0201 0.1088 1.0000 10.500 1.0802 0.02354 0.01680 0.0224 0.0988 1.0000 10.750 1.0870 0.02462 0.01795 0.0247 0.0895 1.0000 11.000 1.0890 0.02577 0.01917 0.0276 0.0820 1.0000 11.250 1.0859 0.02722 0.02060 0.0305 0.0760 1.0000 11.500 1.0868 0.02877 0.02225 0.0323 0.0699 1.0000 11.750 1.0852 0.03074 0.02424 0.0334 0.0648 1.0000 12.000 1.0839 0.03299 0.02657 0.0341 0.0597 1.0000 12.250 1.0842 0.03530 0.02896 0.0342 0.0551 1.0000 12.500 1.0786 0.03822 0.03183 0.0345 0.0512 1.0000 12.750 1.0800 0.04075 0.03454 0.0340 0.0471 1.0000 13.000 1.0776 0.04369 0.03752 0.0334 0.0436 1.0000 13.250 1.0725 0.04681 0.04063 0.0334 0.0404 1.0000 13.500 1.0713 0.04984 0.04383 0.0326 0.0375 1.0000 13.750 1.0684 0.05304 0.04710 0.0316 0.0349 1.0000 14.000 1.0638 0.05628 0.05031 0.0312 0.0327 1.0000 14.250 1.0610 0.05945 0.05362 0.0309 0.0308 1.0000 14.500 1.0567 0.06311 0.05743 0.0296 0.0288 1.0000 14.750 1.0530 0.06667 0.06108 0.0282 0.0271 1.0000 15.000 1.0492 0.07032 0.06475 0.0269 0.0257 1.0000 15.250 1.0442 0.07392 0.06838 0.0265 0.0239 1.0000 15.500 1.0396 0.07805 0.07269 0.0250 0.0232 1.0000 15.750 1.0335 0.08251 0.07732 0.0232 0.0223 1.0000 16.000 1.0266 0.08719 0.08214 0.0212 0.0214 1.0000 16.250 1.0203 0.09185 0.08695 0.0192 0.0210 1.0000 16.500 1.0142 0.09661 0.09177 0.0167 0.0199 1.0000 16.750 1.0103 0.10087 0.09604 0.0146 0.0189 1.0000 17.000 0.9981 0.10652 0.10178 0.0125 0.0181 1.0000 17.250 0.9871 0.11254 0.10796 0.0095 0.0181 1.0000 17.500 0.9711 0.12009 0.11569 0.0048 0.0176 1.0000 17.750 0.9570 0.12692 0.12267 0.0017 0.0180 1.0000 18.000 0.9396 0.13538 0.13130 -0.0037 0.0177 1.0000