XFOIL Version 6.96 Calculated polar for: KENNEDY AND MARSDEN AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.500 -0.1042 0.05345 0.04763 -0.1835 0.4403 0.0415 -13.250 -0.1203 0.04865 0.04271 -0.1869 0.4402 0.0415 -13.000 -0.1267 0.04524 0.03921 -0.1892 0.4402 0.0416 -12.750 -0.1289 0.04248 0.03636 -0.1908 0.4401 0.0417 -12.500 -0.1275 0.04021 0.03403 -0.1920 0.4400 0.0418 -12.250 -0.1245 0.03824 0.03199 -0.1928 0.4398 0.0419 -12.000 -0.1190 0.03658 0.03027 -0.1934 0.4397 0.0420 -11.750 -0.1119 0.03514 0.02878 -0.1937 0.4396 0.0421 -11.500 -0.1041 0.03383 0.02743 -0.1938 0.4394 0.0423 -11.250 -0.0956 0.03263 0.02619 -0.1938 0.4393 0.0424 -11.000 -0.0853 0.03161 0.02513 -0.1936 0.4391 0.0426 -10.750 -0.0748 0.03066 0.02414 -0.1933 0.4389 0.0428 -10.500 -0.0634 0.02977 0.02321 -0.1929 0.4387 0.0430 -10.250 -0.0519 0.02894 0.02234 -0.1924 0.4386 0.0432 -10.000 -0.0397 0.02815 0.02152 -0.1918 0.4384 0.0433 -9.750 -0.0268 0.02743 0.02075 -0.1911 0.4382 0.0435 -9.500 -0.0139 0.02673 0.02002 -0.1903 0.4380 0.0436 -9.250 -0.0001 0.02610 0.01937 -0.1894 0.4378 0.0437 -9.000 0.0141 0.02553 0.01877 -0.1884 0.4376 0.0438 -8.750 0.0280 0.02498 0.01819 -0.1873 0.4374 0.0439 -8.500 0.0419 0.02449 0.01767 -0.1861 0.4372 0.0441 -8.250 0.0560 0.02403 0.01720 -0.1848 0.4370 0.0441 -8.000 0.0689 0.02362 0.01677 -0.1833 0.4368 0.0442 -7.750 0.0796 0.02328 0.01642 -0.1812 0.4366 0.0443 -7.500 0.0886 0.02302 0.01614 -0.1789 0.4364 0.0444 -7.250 0.1019 0.02272 0.01584 -0.1772 0.4362 0.0445 -7.000 0.1180 0.02240 0.01550 -0.1760 0.4359 0.0446 -6.750 0.1356 0.02210 0.01518 -0.1751 0.4356 0.0446 -6.500 0.1518 0.02157 0.01464 -0.1736 0.4352 0.0448 -6.250 0.1684 0.02111 0.01418 -0.1722 0.4349 0.0451 -6.000 0.1866 0.02071 0.01378 -0.1713 0.4347 0.0454 -5.750 0.2070 0.02038 0.01346 -0.1707 0.4344 0.0456 -5.500 0.2292 0.02008 0.01317 -0.1705 0.4341 0.0458 -5.250 0.2532 0.01981 0.01291 -0.1705 0.4338 0.0461 -5.000 0.2786 0.01957 0.01267 -0.1708 0.4336 0.0464 -4.750 0.3053 0.01935 0.01245 -0.1713 0.4333 0.0467 -4.500 0.3331 0.01914 0.01225 -0.1719 0.4330 0.0470 -4.250 0.3620 0.01895 0.01206 -0.1727 0.4327 0.0474 -4.000 0.3918 0.01879 0.01190 -0.1737 0.4324 0.0478 -3.750 0.4223 0.01863 0.01174 -0.1747 0.4321 0.0482 -3.500 0.4534 0.01850 0.01161 -0.1758 0.4318 0.0487 -3.250 0.4845 0.01842 0.01152 -0.1768 0.4314 0.0492 -3.000 0.5155 0.01834 0.01143 -0.1778 0.4311 0.0496 -2.750 0.5468 0.01822 0.01131 -0.1788 0.4307 0.0499 -2.500 0.5819 0.01792 0.01100 -0.1808 0.4302 0.0508 -2.250 0.6157 0.01777 0.01086 -0.1823 0.4298 0.0516 -2.000 0.6488 0.01769 0.01078 -0.1836 0.4293 0.0524 -1.750 0.6822 0.01764 0.01072 -0.1850 0.4290 0.0531 -1.500 0.7157 0.01761 0.01069 -0.1863 0.4286 0.0539 -1.250 0.7491 0.01762 0.01070 -0.1876 0.4282 0.0549 -1.000 0.7835 0.01763 0.01071 -0.1892 0.4279 0.0559 -0.750 0.8196 0.01763 0.01072 -0.1911 0.4276 0.0578 -0.500 0.8539 0.01769 0.01079 -0.1926 0.4272 0.0596 -0.250 0.8879 0.01778 0.01089 -0.1940 0.4269 0.0619 0.000 0.9240 0.01786 0.01100 -0.1960 0.4265 0.0661 0.250 0.9600 0.01798 0.01116 -0.1979 0.4261 0.0729 0.500 0.9993 0.01812 0.01139 -0.2006 0.4256 0.0937 0.750 1.0499 0.01823 0.01178 -0.2059 0.4250 0.1713 1.000 1.0882 0.01984 0.01372 -0.2095 0.4231 0.2450 1.250 1.1399 0.01967 0.01380 -0.2149 0.4229 0.3321 1.500 1.2117 0.01939 0.01394 -0.2245 0.4228 0.4980 1.750 1.2503 0.01947 0.01416 -0.2268 0.4226 0.5593 2.000 1.2802 0.01964 0.01437 -0.2273 0.4224 0.5808 2.250 1.3085 0.01983 0.01459 -0.2275 0.4223 0.5944 2.500 1.3357 0.02003 0.01480 -0.2274 0.4221 0.6071 2.750 1.3620 0.02024 0.01504 -0.2272 0.4219 0.6162 3.000 1.3862 0.02049 0.01531 -0.2266 0.4217 0.6256 3.250 1.4108 0.02078 0.01560 -0.2260 0.4214 0.6330 3.500 1.4341 0.02099 0.01586 -0.2252 0.4211 0.6399 3.750 1.4572 0.02123 0.01613 -0.2245 0.4209 0.6433 4.000 1.4805 0.02147 0.01639 -0.2238 0.4205 0.6465 4.250 1.5037 0.02173 0.01666 -0.2231 0.4202 0.6498 4.500 1.5264 0.02200 0.01694 -0.2223 0.4198 0.6534 4.750 1.5482 0.02229 0.01725 -0.2214 0.4195 0.6563 5.000 1.5704 0.02251 0.01749 -0.2206 0.4191 0.6604 5.250 1.5887 0.02274 0.01776 -0.2190 0.4186 0.6631 5.500 1.6084 0.02301 0.01806 -0.2178 0.4182 0.6651 5.750 1.6292 0.02328 0.01835 -0.2168 0.4178 0.6667 6.000 1.6504 0.02356 0.01865 -0.2160 0.4173 0.6682 6.250 1.6716 0.02385 0.01895 -0.2151 0.4169 0.6697 6.500 1.6915 0.02414 0.01927 -0.2141 0.4164 0.6713 6.750 1.7104 0.02445 0.01960 -0.2129 0.4159 0.6729 7.000 1.7291 0.02477 0.01994 -0.2117 0.4155 0.6746 7.250 1.7479 0.02508 0.02027 -0.2105 0.4150 0.6762 7.500 1.7665 0.02539 0.02060 -0.2094 0.4145 0.6776 7.750 1.7848 0.02568 0.02090 -0.2082 0.4141 0.6788 8.000 1.8037 0.02592 0.02116 -0.2072 0.4136 0.6798 8.250 1.8227 0.02620 0.02144 -0.2061 0.4132 0.6806 8.500 1.8419 0.02649 0.02175 -0.2052 0.4127 0.6815 8.750 1.8632 0.02678 0.02205 -0.2047 0.4123 0.6838 9.000 1.8827 0.02709 0.02238 -0.2039 0.4119 0.6854 9.250 1.9014 0.02741 0.02273 -0.2030 0.4115 0.6870 9.500 1.9203 0.02775 0.02308 -0.2021 0.4112 0.6886 9.750 1.9400 0.02807 0.02342 -0.2013 0.4107 0.6900 10.000 1.9592 0.02845 0.02381 -0.2006 0.4103 0.6913 10.250 1.9790 0.02885 0.02422 -0.2000 0.4099 0.6926 10.500 1.9970 0.02938 0.02477 -0.1991 0.4093 0.6940 10.750 1.9787 0.03212 0.02762 -0.1943 0.4074 0.6951 11.000 1.9819 0.03305 0.02862 -0.1919 0.4070 0.6964 11.250 1.9806 0.03429 0.02994 -0.1893 0.4065 0.6977 11.500 1.9740 0.03595 0.03168 -0.1865 0.4058 0.6988 11.750 1.9530 0.03872 0.03457 -0.1830 0.4044 0.6999 12.000 1.8008 0.05362 0.04985 -0.1763 0.3983 0.7000 12.250 1.8155 0.05482 0.05106 -0.1765 0.3975 0.7011 12.500 1.8355 0.05545 0.05169 -0.1766 0.3969 0.7022 12.750 1.8573 0.05588 0.05211 -0.1767 0.3964 0.7032 13.000 1.8806 0.05613 0.05235 -0.1769 0.3960 0.7041 13.250 1.9064 0.05622 0.05244 -0.1772 0.3956 0.7057 13.500 1.9336 0.05615 0.05237 -0.1776 0.3952 0.7076 13.750 1.9572 0.05635 0.05257 -0.1778 0.3946 0.7092 14.000 1.4221 0.11821 0.11494 -0.1702 0.3444 0.7032