1.0002 -0.00161 0.99043 0.00065 0.97609 0.00427 0.95715 0.00921 0.93617 0.01477 0.91469 0.02055 0.89312 0.02641 0.87154 0.03231 0.84996 0.03824 0.82838 0.04419 0.80681 0.05014 0.78524 0.0561 0.76367 0.06207 0.74209 0.06803 0.72058 0.07398 0.69922 0.07986 0.6781 0.08563 0.6573 0.09122 0.63695 0.09654 0.61707 0.10151 0.59763 0.10606 0.57854 0.11018 0.55967 0.11384 0.54089 0.11704 0.5221 0.11981 0.50324 0.12214 0.48429 0.12404 0.46525 0.12553 0.44616 0.12658 0.42704 0.12722 0.40789 0.12742 0.38868 0.1272 0.36939 0.12657 0.35001 0.12553 0.33058 0.1241 0.31113 0.12228 0.2917 0.12008 0.27233 0.11751 0.25307 0.11457 0.23393 0.11126 0.21496 0.10757 0.19621 0.10353 0.17773 0.09911 0.15956 0.09433 0.14177 0.08917 0.12444 0.08366 0.10769 0.07778 0.09162 0.07157 0.07638 0.06506 0.0622 0.05831 0.04931 0.05144 0.03799 0.0446 0.02846 0.03803 0.0208 0.03198 0.01489 0.02657 0.01041 0.0218 0.00707 0.01758 0.00458 0.01383 0.00276 0.01046 0.00147 0.00741 0.00061 0.00462 0.00013 0.00203 0 -0.00039 0.00025 -0.00278 0.00097 -0.00517 0.00221 -0.00746 0.00399 -0.00958 0.00632 -0.0115 0.00921 -0.01324 0.01273 -0.01487 0.01707 -0.01644 0.02253 -0.018 0.02956 -0.01953 0.03876 -0.02098 0.05086 -0.0222 0.06651 -0.02308 0.08566 -0.02362 0.10687 -0.02393 0.12869 -0.02401 0.15089 -0.02391 0.17339 -0.02368 0.19597 -0.02337 0.21855 -0.02297 0.24109 -0.02251 0.26357 -0.022 0.28601 -0.02144 0.30841 -0.02085 0.33079 -0.02023 0.35315 -0.01959 0.37549 -0.01891 0.39782 -0.01821 0.42015 -0.01749 0.44247 -0.01673 0.46479 -0.01595 0.48711 -0.01513 0.50943 -0.01429 0.53175 -0.01342 0.55407 -0.01251 0.57639 -0.01157 0.59871 -0.0106 0.62103 -0.00962 0.64335 -0.00864 0.66567 -0.00767 0.688 -0.00673 0.71036 -0.00582 0.73279 -0.00494 0.7553 -0.00407 0.77776 -0.0032 0.80018 -0.00229 0.82264 -0.00135 0.84494 -0.00044 0.86681 0.0004 0.88806 0.00108 0.90848 0.00151 0.92796 0.00161 0.94637 0.00129 0.96339 0.00052 0.97834 -0.00064 0.99047 -0.00204 0.9998 -0.00357 XFOIL Version 6.94 Calculated polar for: AH 94-145 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 0.6100 0.01391 0.00862 -0.1270 0.6690 0.9159 0.500 0.6490 0.01394 0.00860 -0.1230 0.6646 0.9628 1.000 0.7172 0.01395 0.00848 -0.1257 0.6608 0.9998 1.500 0.7780 0.01446 0.00884 -0.1274 0.6574 0.9998 2.000 0.8349 0.01499 0.00943 -0.1288 0.6520 0.9998 2.500 0.8934 0.01546 0.00988 -0.1302 0.6468 0.9998 3.000 0.9536 0.01570 0.01010 -0.1315 0.6424 0.9998 3.500 1.0145 0.01594 0.01028 -0.1329 0.6388 0.9998 4.000 1.0701 0.01659 0.01100 -0.1338 0.6334 0.9998 4.500 1.1248 0.01707 0.01156 -0.1344 0.6267 0.9998 5.000 1.1849 0.01703 0.01155 -0.1355 0.6215 0.9998 5.500 1.2476 0.01686 0.01133 -0.1367 0.6162 0.9998 6.000 1.3005 0.01667 0.01130 -0.1366 0.6050 0.9998 6.500 1.3645 0.01586 0.01042 -0.1376 0.5959 0.9998 7.000 1.4175 0.01556 0.01028 -0.1373 0.5833 0.9998 7.500 1.4708 0.01548 0.01032 -0.1371 0.5718 0.9998 8.000 1.5242 0.01521 0.01013 -0.1368 0.5571 0.9998 8.500 1.5688 0.01530 0.01038 -0.1352 0.5354 0.9998 9.000 1.6081 0.01571 0.01088 -0.1328 0.5078 0.9998 9.500 1.6293 0.01674 0.01184 -0.1276 0.4657 0.9998 10.000 1.6216 0.01966 0.01452 -0.1197 0.4031 0.9998 10.500 1.5918 0.02543 0.01994 -0.1122 0.3342 0.9998 11.000 1.5606 0.03219 0.02640 -0.1061 0.2752 0.9998 11.500 1.5362 0.03868 0.03265 -0.1010 0.2255 0.9998 12.000 1.5205 0.04477 0.03856 -0.0969 0.1840 0.9998 12.500 1.5121 0.05056 0.04422 -0.0938 0.1505 0.9998 13.500 1.5065 0.06167 0.05520 -0.0890 0.1042 0.9998 14.000 1.5064 0.06716 0.06068 -0.0870 0.0887 0.9998 15.000 1.5116 0.07799 0.07165 -0.0842 0.0672 0.9998 15.500 1.5110 0.08383 0.07758 -0.0829 0.0600 0.9998 16.000 1.5160 0.08926 0.08315 -0.0822 0.0542 0.9998 16.500 1.5133 0.09539 0.08934 -0.0812 0.0486 0.9998 17.000 1.5202 0.10073 0.09490 -0.0811 0.0449 0.9998 17.500 1.5219 0.10677 0.10109 -0.0812 0.0414 0.9998 18.000 1.5216 0.11244 0.10685 -0.0806 0.0375 0.9998 18.500 1.5249 0.11863 0.11331 -0.0816 0.0352 0.9998 19.000 1.5260 0.12503 0.11990 -0.0828 0.0327 0.9998 19.500 1.5246 0.13178 0.12678 -0.0845 0.0305 0.9998 20.000 1.5227 0.13786 0.13304 -0.0853 0.0280 0.9998 20.500 1.5197 0.14557 0.14104 -0.0884 0.0267 0.9998 21.000 1.5144 0.15375 0.14952 -0.0922 0.0252 0.9998 21.500 1.5084 0.16217 0.15817 -0.0965 0.0238 0.9998 22.000 1.5023 0.17067 0.16685 -0.1013 0.0227 0.9998 22.500 1.4918 0.17998 0.17636 -0.1069 0.0215 0.9998 23.000 1.4605 0.19436 0.19113 -0.1162 0.0207 0.9998 23.500 1.4309 0.21077 0.20794 -0.1281 0.0204 0.9998