XFOIL Version 6.96 Calculated polar for: EPPLER 361 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.5288 0.08355 0.08193 -0.0255 1.0000 0.0117 -10.000 -0.5415 0.07543 0.07383 -0.0319 1.0000 0.0118 -9.750 -0.5819 0.06345 0.06175 -0.0416 1.0000 0.0114 -9.500 -0.6077 0.05842 0.05662 -0.0419 1.0000 0.0114 -9.250 -0.6308 0.05478 0.05288 -0.0391 1.0000 0.0114 -9.000 -0.6461 0.05142 0.04940 -0.0359 1.0000 0.0116 -8.750 -0.6562 0.04767 0.04549 -0.0331 1.0000 0.0117 -8.500 -0.6637 0.04369 0.04132 -0.0299 1.0000 0.0121 -8.250 -0.6817 0.03836 0.03531 -0.0232 1.0000 0.0131 -8.000 -0.6804 0.03207 0.02874 -0.0224 0.9901 0.0136 -7.750 -0.6760 0.02046 0.01581 -0.0196 0.9683 0.0081 -7.500 -0.6358 0.01973 0.01492 -0.0224 0.9364 0.0080 -7.250 -0.6154 0.01726 0.01214 -0.0213 0.8943 0.0076 -7.000 -0.5957 0.01611 0.01073 -0.0197 0.8633 0.0075 -6.750 -0.5750 0.01505 0.00947 -0.0183 0.8395 0.0074 -6.500 -0.5534 0.01426 0.00851 -0.0170 0.8191 0.0074 -6.250 -0.5313 0.01357 0.00768 -0.0159 0.8010 0.0074 -6.000 -0.5092 0.01291 0.00689 -0.0147 0.7843 0.0074 -5.750 -0.4863 0.01238 0.00626 -0.0137 0.7693 0.0074 -5.500 -0.4630 0.01191 0.00569 -0.0128 0.7558 0.0075 -5.250 -0.4392 0.01148 0.00518 -0.0119 0.7432 0.0076 -5.000 -0.4152 0.01111 0.00471 -0.0111 0.7312 0.0078 -4.750 -0.3913 0.01069 0.00421 -0.0102 0.7197 0.0081 -4.500 -0.3672 0.01027 0.00373 -0.0094 0.7094 0.0087 -4.250 -0.3419 0.01003 0.00343 -0.0089 0.6998 0.0099 -4.000 -0.3167 0.00973 0.00310 -0.0083 0.6902 0.0117 -3.750 -0.2911 0.00949 0.00282 -0.0077 0.6815 0.0145 -3.500 -0.2661 0.00918 0.00255 -0.0071 0.6729 0.0269 -3.250 -0.2406 0.00895 0.00237 -0.0066 0.6652 0.0442 -3.000 -0.2148 0.00874 0.00221 -0.0062 0.6574 0.0631 -2.750 -0.1897 0.00846 0.00206 -0.0057 0.6505 0.0967 -2.500 -0.1665 0.00799 0.00188 -0.0049 0.6436 0.1757 -2.250 -0.1467 0.00728 0.00167 -0.0036 0.6371 0.3192 -1.750 -0.1100 0.00581 0.00135 -0.0002 0.6252 0.6445 -1.500 -0.0860 0.00563 0.00133 0.0007 0.6195 0.7050 -1.250 -0.0596 0.00555 0.00131 0.0012 0.6138 0.7365 -1.000 -0.0329 0.00552 0.00130 0.0016 0.6082 0.7590 -0.750 -0.0057 0.00552 0.00130 0.0019 0.6029 0.7776 -0.500 0.0217 0.00550 0.00131 0.0021 0.5976 0.7940 -0.250 0.0484 0.00552 0.00132 0.0025 0.5919 0.8127 0.000 0.0756 0.00553 0.00134 0.0029 0.5859 0.8262 0.250 0.1029 0.00553 0.00136 0.0031 0.5784 0.8377 0.500 0.1301 0.00557 0.00137 0.0034 0.5706 0.8483 0.750 0.1576 0.00559 0.00138 0.0037 0.5619 0.8577 1.000 0.1850 0.00561 0.00139 0.0039 0.5524 0.8659 1.250 0.2123 0.00565 0.00140 0.0041 0.5435 0.8735 1.500 0.2402 0.00567 0.00141 0.0042 0.5367 0.8797 1.750 0.2681 0.00569 0.00144 0.0042 0.5299 0.8852 2.000 0.2958 0.00574 0.00147 0.0044 0.5227 0.8911 2.250 0.3236 0.00577 0.00149 0.0044 0.5140 0.8967 2.500 0.3513 0.00580 0.00153 0.0045 0.5062 0.9023 2.750 0.3786 0.00586 0.00157 0.0047 0.4962 0.9084 3.000 0.4063 0.00591 0.00161 0.0048 0.4848 0.9142 3.250 0.4336 0.00597 0.00166 0.0049 0.4731 0.9203 3.500 0.4602 0.00606 0.00172 0.0052 0.4594 0.9270 3.750 0.4877 0.00617 0.00180 0.0053 0.4399 0.9327 4.000 0.5135 0.00634 0.00189 0.0057 0.4150 0.9398 4.250 0.5399 0.00657 0.00202 0.0059 0.3837 0.9460 4.500 0.5654 0.00691 0.00220 0.0062 0.3425 0.9527 4.750 0.5901 0.00735 0.00243 0.0066 0.2941 0.9595 5.000 0.6179 0.00779 0.00269 0.0063 0.2518 0.9645 5.250 0.6429 0.00817 0.00292 0.0066 0.2202 0.9717 5.500 0.6748 0.00856 0.00319 0.0054 0.1913 0.9742 5.750 0.7069 0.00891 0.00344 0.0042 0.1682 0.9770 6.000 0.7388 0.00924 0.00369 0.0030 0.1516 0.9799 6.250 0.7680 0.00954 0.00393 0.0024 0.1387 0.9840 6.500 0.8023 0.00985 0.00418 0.0007 0.1279 0.9852 6.750 0.8360 0.01015 0.00444 -0.0009 0.1188 0.9868 7.000 0.8695 0.01040 0.00469 -0.0025 0.1126 0.9888 7.250 0.9017 0.01071 0.00496 -0.0038 0.1060 0.9913 7.500 0.9331 0.01098 0.00524 -0.0048 0.1011 0.9939 7.750 0.9667 0.01124 0.00549 -0.0065 0.0963 0.9954 8.000 0.9994 0.01162 0.00585 -0.0080 0.0901 0.9972 8.250 1.0331 0.01183 0.00609 -0.0096 0.0874 0.9989 8.500 1.0623 0.01212 0.00636 -0.0103 0.0831 1.0000 8.750 1.0761 0.01247 0.00671 -0.0079 0.0787 1.0000 9.000 1.0937 0.01267 0.00694 -0.0061 0.0768 1.0000 9.250 1.1111 0.01292 0.00721 -0.0043 0.0743 1.0000 9.500 1.1278 0.01323 0.00751 -0.0025 0.0712 1.0000 9.750 1.1430 0.01364 0.00793 -0.0004 0.0673 1.0000 10.000 1.1619 0.01388 0.00821 0.0011 0.0656 1.0000 10.250 1.1796 0.01419 0.00853 0.0027 0.0630 1.0000 10.500 1.1956 0.01459 0.00891 0.0045 0.0597 1.0000 10.750 1.2113 0.01500 0.00936 0.0064 0.0570 1.0000 11.000 1.2288 0.01531 0.00971 0.0080 0.0549 1.0000 11.250 1.2443 0.01572 0.01012 0.0098 0.0523 1.0000 11.500 1.2557 0.01627 0.01067 0.0123 0.0492 1.0000 11.750 1.2681 0.01664 0.01109 0.0147 0.0479 1.0000 12.000 1.2804 0.01706 0.01155 0.0170 0.0460 1.0000 12.250 1.2912 0.01760 0.01211 0.0193 0.0440 1.0000 12.500 1.2996 0.01833 0.01285 0.0217 0.0418 1.0000 12.750 1.3116 0.01895 0.01353 0.0235 0.0403 1.0000 13.000 1.3240 0.01960 0.01423 0.0250 0.0388 1.0000 13.250 1.3344 0.02042 0.01509 0.0266 0.0372 1.0000 13.500 1.3415 0.02152 0.01621 0.0282 0.0351 1.0000 13.750 1.3512 0.02253 0.01728 0.0295 0.0339 1.0000 14.000 1.3630 0.02345 0.01827 0.0304 0.0326 1.0000 14.250 1.3721 0.02463 0.01949 0.0313 0.0312 1.0000 14.500 1.3783 0.02609 0.02097 0.0323 0.0297 1.0000 14.750 1.3837 0.02769 0.02264 0.0331 0.0284 1.0000 15.000 1.3933 0.02899 0.02402 0.0336 0.0275 1.0000 15.250 1.4005 0.03054 0.02563 0.0341 0.0264 1.0000 15.500 1.4054 0.03234 0.02747 0.0345 0.0251 1.0000 15.750 1.4055 0.03465 0.02984 0.0348 0.0240 1.0000 16.000 1.4099 0.03660 0.03187 0.0350 0.0232 1.0000 16.250 1.4151 0.03853 0.03388 0.0350 0.0224 1.0000 16.500 1.4190 0.04058 0.03599 0.0350 0.0214 1.0000 16.750 1.4172 0.04330 0.03879 0.0349 0.0209 1.0000 17.000 1.4128 0.04638 0.04193 0.0345 0.0200 1.0000 17.250 1.4073 0.04970 0.04535 0.0339 0.0193 1.0000 17.500 1.4091 0.05228 0.04802 0.0334 0.0188 1.0000 17.750 1.4079 0.05528 0.05111 0.0327 0.0182 1.0000 18.000 1.4029 0.05884 0.05476 0.0316 0.0176 1.0000 18.250 1.3964 0.06271 0.05871 0.0304 0.0171 1.0000 18.500 1.3864 0.06718 0.06325 0.0288 0.0165 1.0000 18.750 1.3691 0.07282 0.06900 0.0266 0.0159 1.0000 19.000 1.3637 0.07692 0.07320 0.0250 0.0155 1.0000 19.250 1.3483 0.08266 0.07907 0.0225 0.0155 1.0000