XFOIL Version 6.96 Calculated polar for: EPPLER 360 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 ------ -------- --------- --------- -------- -------- -------- -12.500 -0.5054 0.12662 0.12485 -0.0094 1.0000 0.0097 -12.250 -0.5042 0.12233 0.12057 -0.0111 1.0000 0.0095 -8.250 -0.7475 0.02474 0.02047 -0.0162 0.9973 0.0084 -8.000 -0.7198 0.02189 0.01743 -0.0174 0.9940 0.0081 -7.750 -0.6926 0.01957 0.01485 -0.0180 0.9889 0.0079 -7.250 -0.6311 0.01657 0.01149 -0.0200 0.9750 0.0079 -7.000 -0.5971 0.01568 0.01049 -0.0215 0.9627 0.0081 -6.750 -0.5587 0.01449 0.00917 -0.0240 0.9455 0.0081 -6.500 -0.5248 0.01351 0.00804 -0.0254 0.9148 0.0081 -6.250 -0.5022 0.01289 0.00724 -0.0243 0.8804 0.0080 -6.000 -0.4810 0.01237 0.00656 -0.0229 0.8530 0.0081 -5.750 -0.4593 0.01190 0.00597 -0.0217 0.8314 0.0082 -5.500 -0.4369 0.01150 0.00545 -0.0205 0.8118 0.0082 -5.250 -0.4146 0.01106 0.00491 -0.0194 0.7943 0.0084 -5.000 -0.3926 0.01056 0.00430 -0.0182 0.7786 0.0087 -4.750 -0.3690 0.01022 0.00389 -0.0173 0.7646 0.0092 -4.500 -0.3444 0.00997 0.00358 -0.0166 0.7513 0.0102 -4.000 -0.2952 0.00942 0.00292 -0.0152 0.7263 0.0152 -3.750 -0.2707 0.00912 0.00265 -0.0144 0.7154 0.0270 -3.500 -0.2461 0.00888 0.00245 -0.0138 0.7047 0.0452 -3.250 -0.2207 0.00866 0.00229 -0.0133 0.6944 0.0644 -3.000 -0.1959 0.00840 0.00213 -0.0128 0.6852 0.0970 -2.750 -0.1731 0.00796 0.00194 -0.0119 0.6760 0.1695 -2.500 -0.1527 0.00731 0.00173 -0.0108 0.6678 0.2942 -2.250 -0.1357 0.00643 0.00149 -0.0090 0.6598 0.4756 -2.000 -0.1180 0.00573 0.00136 -0.0071 0.6525 0.6369 -1.750 -0.0940 0.00555 0.00133 -0.0062 0.6450 0.6973 -1.500 -0.0675 0.00550 0.00132 -0.0057 0.6382 0.7259 -1.250 -0.0405 0.00548 0.00131 -0.0054 0.6311 0.7463 -1.000 -0.0134 0.00549 0.00131 -0.0051 0.6246 0.7636 -0.750 0.0141 0.00549 0.00132 -0.0049 0.6180 0.7787 -0.500 0.0410 0.00553 0.00134 -0.0046 0.6114 0.7945 -0.250 0.0684 0.00554 0.00137 -0.0043 0.6044 0.8071 0.000 0.0957 0.00560 0.00137 -0.0040 0.5958 0.8174 0.250 0.1232 0.00562 0.00140 -0.0038 0.5868 0.8262 0.500 0.1504 0.00568 0.00141 -0.0036 0.5771 0.8343 0.750 0.1779 0.00571 0.00143 -0.0034 0.5664 0.8412 1.000 0.2055 0.00576 0.00144 -0.0032 0.5570 0.8474 1.250 0.2333 0.00579 0.00145 -0.0032 0.5489 0.8521 1.500 0.2612 0.00581 0.00148 -0.0031 0.5411 0.8565 1.750 0.2889 0.00587 0.00150 -0.0030 0.5324 0.8610 2.000 0.3170 0.00591 0.00152 -0.0030 0.5242 0.8652 2.250 0.3444 0.00595 0.00155 -0.0029 0.5144 0.8694 2.500 0.3721 0.00600 0.00159 -0.0028 0.5036 0.8737 2.750 0.3997 0.00606 0.00163 -0.0028 0.4933 0.8782 3.000 0.4270 0.00613 0.00167 -0.0026 0.4803 0.8825 3.250 0.4539 0.00621 0.00172 -0.0024 0.4635 0.8869 3.500 0.4806 0.00632 0.00179 -0.0022 0.4446 0.8916 3.750 0.5067 0.00648 0.00187 -0.0019 0.4222 0.8963 4.000 0.5321 0.00667 0.00197 -0.0015 0.3917 0.9011 4.250 0.5561 0.00697 0.00212 -0.0008 0.3497 0.9065 4.500 0.5792 0.00736 0.00231 -0.0001 0.3032 0.9122 4.750 0.6024 0.00770 0.00252 0.0007 0.2645 0.9178 5.000 0.6256 0.00804 0.00273 0.0014 0.2315 0.9240 5.250 0.6489 0.00837 0.00294 0.0021 0.2024 0.9304 5.500 0.6723 0.00866 0.00316 0.0029 0.1802 0.9372 5.750 0.6961 0.00892 0.00335 0.0036 0.1636 0.9446 6.000 0.7206 0.00918 0.00357 0.0041 0.1493 0.9517 6.250 0.7450 0.00945 0.00380 0.0046 0.1371 0.9598 6.500 0.7731 0.00970 0.00403 0.0043 0.1280 0.9660 6.750 0.8006 0.00995 0.00426 0.0042 0.1203 0.9732 7.000 0.8325 0.01025 0.00453 0.0030 0.1128 0.9771 7.250 0.8633 0.01051 0.00480 0.0021 0.1076 0.9821 7.500 0.8953 0.01080 0.00507 0.0008 0.1019 0.9855 7.750 0.9287 0.01114 0.00540 -0.0008 0.0961 0.9875 8.000 0.9622 0.01138 0.00566 -0.0023 0.0927 0.9900 8.250 0.9939 0.01172 0.00597 -0.0036 0.0876 0.9932 8.500 1.0264 0.01206 0.00633 -0.0051 0.0833 0.9958 8.750 1.0599 0.01233 0.00661 -0.0067 0.0800 0.9982 9.000 1.0903 0.01269 0.00695 -0.0078 0.0756 1.0000 9.250 1.1010 0.01301 0.00728 -0.0047 0.0724 1.0000 9.500 1.1184 0.01321 0.00751 -0.0029 0.0707 1.0000 9.750 1.1360 0.01347 0.00779 -0.0012 0.0679 1.0000 10.000 1.1526 0.01383 0.00814 0.0006 0.0647 1.0000 10.250 1.1689 0.01424 0.00856 0.0025 0.0616 1.0000 10.500 1.1885 0.01450 0.00886 0.0037 0.0596 1.0000 10.750 1.2065 0.01485 0.00921 0.0052 0.0567 1.0000 11.000 1.2215 0.01536 0.00971 0.0070 0.0530 1.0000 11.250 1.2392 0.01570 0.01010 0.0085 0.0514 1.0000 11.500 1.2543 0.01606 0.01050 0.0105 0.0495 1.0000 11.750 1.2669 0.01651 0.01096 0.0127 0.0473 1.0000 12.000 1.2775 0.01710 0.01155 0.0152 0.0450 1.0000 12.250 1.2901 0.01763 0.01214 0.0172 0.0434 1.0000 12.500 1.3049 0.01809 0.01264 0.0188 0.0418 1.0000 12.750 1.3172 0.01870 0.01329 0.0206 0.0401 1.0000 13.000 1.3270 0.01949 0.01409 0.0226 0.0381 1.0000 13.250 1.3355 0.02040 0.01504 0.0245 0.0364 1.0000 13.500 1.3489 0.02107 0.01578 0.0257 0.0353 1.0000 13.750 1.3614 0.02183 0.01655 0.0268 0.0327 1.0000 14.000 1.3694 0.02294 0.01771 0.0283 0.0319 1.0000 14.250 1.3738 0.02438 0.01920 0.0298 0.0302 1.0000 14.500 1.3887 0.02512 0.01999 0.0304 0.0286 1.0000 14.750 1.3963 0.02644 0.02139 0.0313 0.0278 1.0000 15.000 1.4031 0.02789 0.02287 0.0321 0.0266 1.0000 15.250 1.4067 0.02967 0.02471 0.0329 0.0255 1.0000 15.500 1.4162 0.03100 0.02609 0.0333 0.0237 1.0000 15.750 1.4220 0.03270 0.02785 0.0338 0.0227 1.0000 16.000 1.4258 0.03464 0.02985 0.0341 0.0218 1.0000 16.250 1.4262 0.03697 0.03223 0.0343 0.0207 1.0000 16.500 1.4282 0.03919 0.03454 0.0344 0.0198 1.0000 16.750 1.4315 0.04134 0.03677 0.0343 0.0190 1.0000 17.000 1.4316 0.04389 0.03939 0.0341 0.0183 1.0000 17.250 1.4303 0.04665 0.04223 0.0338 0.0176 1.0000 17.500 1.4255 0.04994 0.04560 0.0332 0.0170 1.0000 17.750 1.4165 0.05385 0.04960 0.0322 0.0164 1.0000 18.000 1.4149 0.05698 0.05282 0.0313 0.0159 1.0000 18.250 1.4123 0.06033 0.05626 0.0302 0.0152 1.0000 18.500 1.4048 0.06445 0.06050 0.0288 0.0151 1.0000 18.750 1.3946 0.06907 0.06522 0.0270 0.0147 1.0000 19.000 1.3832 0.07403 0.07028 0.0249 0.0142 1.0000 19.250 1.3667 0.07994 0.07629 0.0223 0.0138 1.0000