XFOIL Version 6.96 Calculated polar for: Dayton-Wright 6 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 ------ -------- --------- --------- -------- -------- -------- -12.250 -0.5385 0.03634 0.03316 -0.1098 0.9488 0.0243 -12.000 -0.5319 0.03304 0.02958 -0.1106 0.9378 0.0245 -11.750 -0.5114 0.03050 0.02679 -0.1125 0.9306 0.0248 -11.500 -0.4888 0.02812 0.02413 -0.1142 0.9211 0.0252 -11.250 -0.4619 0.02581 0.02149 -0.1164 0.9127 0.0254 -11.000 -0.4337 0.02398 0.01938 -0.1181 0.9021 0.0256 -10.750 -0.4072 0.02257 0.01770 -0.1189 0.8897 0.0259 -10.500 -0.3829 0.02137 0.01626 -0.1190 0.8770 0.0262 -10.250 -0.3602 0.02039 0.01505 -0.1184 0.8664 0.0264 -10.000 -0.3400 0.01952 0.01399 -0.1173 0.8574 0.0266 -9.750 -0.3184 0.01880 0.01308 -0.1163 0.8495 0.0268 -9.500 -0.2973 0.01816 0.01229 -0.1150 0.8415 0.0271 -9.250 -0.2746 0.01769 0.01166 -0.1141 0.8341 0.0273 -9.000 -0.2532 0.01714 0.01097 -0.1128 0.8269 0.0275 -8.750 -0.2308 0.01656 0.01025 -0.1117 0.8204 0.0276 -8.500 -0.2103 0.01576 0.00934 -0.1103 0.8139 0.0279 -8.250 -0.1885 0.01515 0.00865 -0.1091 0.8067 0.0281 -8.000 -0.1660 0.01464 0.00804 -0.1080 0.8000 0.0284 -7.750 -0.1437 0.01420 0.00755 -0.1068 0.7926 0.0287 -7.500 -0.1205 0.01382 0.00709 -0.1058 0.7853 0.0289 -7.250 -0.0980 0.01345 0.00667 -0.1045 0.7766 0.0292 -7.000 -0.0750 0.01313 0.00628 -0.1034 0.7676 0.0295 -6.750 -0.0523 0.01283 0.00592 -0.1022 0.7567 0.0298 -6.500 -0.0301 0.01254 0.00556 -0.1008 0.7430 0.0301 -6.250 -0.0085 0.01229 0.00522 -0.0993 0.7247 0.0305 -6.000 0.0120 0.01209 0.00490 -0.0976 0.6998 0.0308 -5.750 0.0315 0.01196 0.00461 -0.0957 0.6710 0.0312 -5.500 0.0507 0.01189 0.00437 -0.0937 0.6420 0.0317 -5.250 0.0713 0.01181 0.00416 -0.0920 0.6197 0.0321 -5.000 0.0925 0.01174 0.00397 -0.0905 0.6012 0.0326 -4.750 0.1143 0.01166 0.00379 -0.0891 0.5859 0.0329 -4.500 0.1360 0.01153 0.00358 -0.0876 0.5724 0.0334 -4.250 0.1584 0.01142 0.00339 -0.0864 0.5603 0.0341 -4.000 0.1814 0.01131 0.00323 -0.0853 0.5507 0.0350 -3.500 0.2279 0.01118 0.00299 -0.0831 0.5331 0.0368 -3.250 0.2510 0.01114 0.00289 -0.0820 0.5250 0.0381 -3.000 0.2748 0.01107 0.00280 -0.0810 0.5179 0.0401 -2.750 0.2980 0.01100 0.00272 -0.0800 0.5110 0.0442 -2.500 0.3204 0.01086 0.00268 -0.0788 0.5050 0.0679 -2.250 0.3440 0.01080 0.00264 -0.0779 0.4986 0.0839 -2.000 0.3668 0.01078 0.00263 -0.0768 0.4916 0.0948 -1.750 0.3904 0.01074 0.00261 -0.0758 0.4852 0.1068 -1.500 0.4136 0.01072 0.00260 -0.0748 0.4786 0.1205 -1.250 0.4364 0.01072 0.00261 -0.0737 0.4729 0.1335 -1.000 0.4601 0.01069 0.00261 -0.0729 0.4668 0.1493 -0.750 0.4826 0.01068 0.00263 -0.0717 0.4603 0.1670 -0.500 0.5049 0.01066 0.00265 -0.0706 0.4537 0.1922 -0.250 0.5268 0.01060 0.00269 -0.0694 0.4466 0.2282 0.000 0.5472 0.01054 0.00274 -0.0679 0.4400 0.2786 0.250 0.5684 0.01044 0.00279 -0.0666 0.4335 0.3377 0.500 0.5858 0.01024 0.00284 -0.0646 0.4269 0.4367 1.000 0.7715 0.00994 0.00378 -0.0936 0.4020 0.9848 1.500 0.8581 0.01033 0.00403 -0.1008 0.3849 0.9967 2.000 0.9195 0.01063 0.00421 -0.1026 0.3705 1.0000 2.250 0.9380 0.01079 0.00432 -0.1009 0.3633 1.0000 2.500 0.9571 0.01094 0.00444 -0.0992 0.3579 1.0000 2.750 0.9763 0.01108 0.00455 -0.0976 0.3522 1.0000 3.000 0.9945 0.01126 0.00470 -0.0958 0.3470 1.0000 3.250 1.0133 0.01142 0.00484 -0.0942 0.3424 1.0000 3.500 1.0320 0.01158 0.00498 -0.0925 0.3369 1.0000 3.750 1.0497 0.01177 0.00515 -0.0906 0.3322 1.0000 4.000 1.0671 0.01196 0.00532 -0.0887 0.3280 1.0000 4.250 1.0844 0.01211 0.00547 -0.0867 0.3240 1.0000 4.500 1.1001 0.01228 0.00564 -0.0845 0.3197 1.0000 4.750 1.1151 0.01247 0.00582 -0.0821 0.3157 1.0000 5.000 1.1311 0.01267 0.00601 -0.0800 0.3121 1.0000 5.250 1.1486 0.01283 0.00620 -0.0781 0.3085 1.0000 5.500 1.1648 0.01305 0.00641 -0.0761 0.3031 1.0000 5.750 1.1795 0.01333 0.00665 -0.0738 0.2974 1.0000 6.000 1.1978 0.01351 0.00687 -0.0723 0.2932 1.0000 6.250 1.2144 0.01376 0.00712 -0.0705 0.2872 1.0000 6.500 1.2294 0.01408 0.00741 -0.0684 0.2815 1.0000 6.750 1.2478 0.01430 0.00766 -0.0670 0.2768 1.0000 7.000 1.2638 0.01460 0.00796 -0.0652 0.2702 1.0000 7.250 1.2796 0.01493 0.00829 -0.0634 0.2638 1.0000 7.500 1.2965 0.01524 0.00862 -0.0618 0.2575 1.0000 7.750 1.3109 0.01564 0.00901 -0.0599 0.2510 1.0000 8.000 1.3280 0.01597 0.00936 -0.0585 0.2446 1.0000 8.250 1.3410 0.01648 0.00983 -0.0565 0.2333 1.0000 8.500 1.3532 0.01704 0.01035 -0.0544 0.2214 1.0000 8.750 1.3648 0.01767 0.01094 -0.0524 0.2082 1.0000 9.000 1.3737 0.01846 0.01166 -0.0501 0.1913 1.0000 9.250 1.3762 0.01963 0.01269 -0.0470 0.1669 1.0000 9.500 1.3749 0.02109 0.01400 -0.0438 0.1404 1.0000 9.750 1.3692 0.02292 0.01565 -0.0402 0.1117 1.0000 10.000 1.3518 0.02565 0.01815 -0.0359 0.0733 1.0000 10.250 1.3275 0.02913 0.02142 -0.0316 0.0319 1.0000 10.500 1.3206 0.03157 0.02385 -0.0292 0.0194 1.0000 10.750 1.3235 0.03337 0.02570 -0.0278 0.0170 1.0000 11.000 1.3285 0.03507 0.02747 -0.0267 0.0161 1.0000 11.250 1.3321 0.03696 0.02943 -0.0257 0.0154 1.0000 11.500 1.3351 0.03898 0.03154 -0.0249 0.0149 1.0000 11.750 1.3353 0.04139 0.03403 -0.0241 0.0142 1.0000 12.000 1.3361 0.04384 0.03657 -0.0235 0.0137 1.0000 12.250 1.3378 0.04627 0.03910 -0.0232 0.0133 1.0000 12.500 1.3385 0.04891 0.04182 -0.0229 0.0129 1.0000 12.750 1.3377 0.05181 0.04482 -0.0228 0.0125 1.0000 13.000 1.3353 0.05495 0.04806 -0.0228 0.0122 1.0000 13.250 1.3321 0.05824 0.05145 -0.0229 0.0120 1.0000 13.500 1.3276 0.06177 0.05506 -0.0231 0.0116 1.0000 13.750 1.3219 0.06549 0.05888 -0.0233 0.0115 1.0000 14.000 1.3148 0.06943 0.06292 -0.0237 0.0113 1.0000 14.250 1.3053 0.07377 0.06738 -0.0242 0.0111 1.0000 14.500 1.2978 0.07792 0.07163 -0.0248 0.0111 1.0000 14.750 1.2867 0.08265 0.07645 -0.0256 0.0108 1.0000 15.000 1.2792 0.08693 0.08083 -0.0264 0.0108 1.0000