XFOIL Version 6.96 Calculated polar for: LOCKHEED C-141 BL113.6 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -1.0394 0.10502 0.10220 -0.0438 1.0000 0.0109 -18.750 -1.1208 0.08671 0.08364 -0.0535 1.0000 0.0107 -18.500 -1.1775 0.07273 0.06941 -0.0615 1.0000 0.0106 -18.250 -1.2111 0.06326 0.05974 -0.0671 1.0000 0.0106 -18.000 -1.2327 0.05637 0.05269 -0.0711 1.0000 0.0106 -17.750 -1.2472 0.05101 0.04719 -0.0738 1.0000 0.0107 -17.500 -1.2570 0.04666 0.04271 -0.0757 1.0000 0.0107 -17.250 -1.2634 0.04304 0.03897 -0.0769 1.0000 0.0108 -17.000 -1.2669 0.03997 0.03578 -0.0776 1.0000 0.0108 -16.750 -1.2684 0.03732 0.03303 -0.0778 1.0000 0.0109 -16.500 -1.2677 0.03503 0.03063 -0.0777 1.0000 0.0110 -16.250 -1.2657 0.03302 0.02852 -0.0772 1.0000 0.0111 -16.000 -1.2625 0.03125 0.02665 -0.0764 1.0000 0.0112 -15.750 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0.0262 0.00607 0.00133 -0.0473 0.8478 0.4409 -1.250 0.0507 0.00581 0.00128 -0.0467 0.8431 0.5001 -1.000 0.0758 0.00561 0.00124 -0.0462 0.8376 0.5490 -0.750 0.1017 0.00546 0.00121 -0.0457 0.8322 0.5884 -0.500 0.1276 0.00535 0.00120 -0.0453 0.8255 0.6208 -0.250 0.1529 0.00526 0.00117 -0.0446 0.8125 0.6491 0.250 0.1978 0.00532 0.00110 -0.0420 0.7374 0.6951 0.500 0.2197 0.00543 0.00113 -0.0406 0.7036 0.7213 0.750 0.2421 0.00553 0.00118 -0.0394 0.6729 0.7431 1.000 0.2649 0.00568 0.00124 -0.0382 0.6387 0.7572 1.250 0.2877 0.00584 0.00131 -0.0371 0.6025 0.7675 1.500 0.3099 0.00606 0.00139 -0.0359 0.5588 0.7771 1.750 0.3312 0.00635 0.00150 -0.0346 0.5063 0.7876 2.000 0.3525 0.00666 0.00163 -0.0333 0.4494 0.7986 2.250 0.3727 0.00707 0.00180 -0.0318 0.3799 0.8107 2.500 0.3935 0.00746 0.00197 -0.0305 0.3164 0.8241 2.750 0.4152 0.00781 0.00215 -0.0294 0.2632 0.8379 3.000 0.4382 0.00808 0.00230 -0.0285 0.2254 0.8516 3.250 0.4617 0.00833 0.00246 -0.0277 0.1939 0.8650 3.500 0.4855 0.00856 0.00263 -0.0269 0.1669 0.8787 3.750 0.5094 0.00879 0.00279 -0.0261 0.1456 0.8927 4.000 0.5335 0.00900 0.00296 -0.0254 0.1271 0.9068 4.250 0.5578 0.00922 0.00315 -0.0247 0.1117 0.9202 4.500 0.5825 0.00944 0.00334 -0.0241 0.0998 0.9321 4.750 0.6073 0.00967 0.00353 -0.0235 0.0891 0.9431 5.000 0.6327 0.00991 0.00373 -0.0231 0.0792 0.9529 5.250 0.6596 0.01013 0.00393 -0.0230 0.0724 0.9602 5.500 0.6861 0.01038 0.00414 -0.0229 0.0655 0.9674 5.750 0.7136 0.01065 0.00437 -0.0230 0.0589 0.9728 6.000 0.7427 0.01090 0.00460 -0.0234 0.0541 0.9772 6.250 0.7686 0.01117 0.00483 -0.0232 0.0490 0.9827 6.500 0.7991 0.01145 0.00509 -0.0241 0.0450 0.9852 6.750 0.8294 0.01174 0.00536 -0.0249 0.0417 0.9877 7.000 0.8591 0.01202 0.00562 -0.0256 0.0389 0.9902 7.250 0.8873 0.01234 0.00592 -0.0260 0.0360 0.9929 7.500 0.9172 0.01262 0.00620 -0.0267 0.0337 0.9947 7.750 0.9471 0.01296 0.00652 -0.0276 0.0313 0.9963 8.000 0.9767 0.01327 0.00684 -0.0283 0.0296 0.9981 8.250 1.0058 0.01361 0.00717 -0.0289 0.0279 0.9998 8.500 1.0217 0.01389 0.00745 -0.0267 0.0265 1.0000 8.750 1.0348 0.01413 0.00770 -0.0238 0.0256 1.0000 9.000 1.0477 0.01436 0.00795 -0.0209 0.0246 1.0000 9.250 1.0624 0.01464 0.00824 -0.0185 0.0235 1.0000 9.500 1.0786 0.01498 0.00857 -0.0164 0.0223 1.0000 9.750 1.0963 0.01531 0.00893 -0.0147 0.0215 1.0000 10.000 1.1149 0.01565 0.00930 -0.0132 0.0207 1.0000 10.250 1.1334 0.01603 0.00969 -0.0117 0.0199 1.0000 10.500 1.1517 0.01645 0.01012 -0.0102 0.0191 1.0000 10.750 1.1695 0.01692 0.01061 -0.0088 0.0183 1.0000 11.000 1.1882 0.01734 0.01106 -0.0074 0.0179 1.0000 11.250 1.2065 0.01778 0.01155 -0.0061 0.0174 1.0000 11.500 1.2244 0.01826 0.01206 -0.0047 0.0168 1.0000 11.750 1.2419 0.01878 0.01260 -0.0034 0.0163 1.0000 12.000 1.2589 0.01933 0.01318 -0.0020 0.0159 1.0000 12.250 1.2749 0.01994 0.01383 -0.0005 0.0154 1.0000 12.500 1.2909 0.02056 0.01449 0.0010 0.0150 1.0000 12.750 1.3072 0.02116 0.01514 0.0024 0.0147 1.0000 13.000 1.3228 0.02179 0.01583 0.0038 0.0144 1.0000 13.250 1.3379 0.02247 0.01656 0.0053 0.0141 1.0000 13.500 1.3522 0.02320 0.01734 0.0067 0.0138 1.0000 13.750 1.3660 0.02398 0.01817 0.0082 0.0135 1.0000 14.000 1.3789 0.02481 0.01905 0.0097 0.0133 1.0000 14.250 1.3912 0.02572 0.02001 0.0112 0.0130 1.0000 14.500 1.4022 0.02671 0.02106 0.0128 0.0128 1.0000 14.750 1.4116 0.02783 0.02224 0.0145 0.0125 1.0000 15.000 1.4199 0.02907 0.02354 0.0161 0.0123 1.0000 15.250 1.4297 0.03020 0.02476 0.0175 0.0122 1.0000 15.500 1.4384 0.03144 0.02608 0.0189 0.0121 1.0000 15.750 1.4462 0.03279 0.02751 0.0202 0.0120 1.0000 16.000 1.4531 0.03424 0.02905 0.0215 0.0119 1.0000 16.250 1.4588 0.03583 0.03072 0.0227 0.0118 1.0000 16.500 1.4634 0.03756 0.03254 0.0238 0.0116 1.0000 16.750 1.4670 0.03946 0.03453 0.0248 0.0115 1.0000 17.000 1.4696 0.04154 0.03671 0.0255 0.0114 1.0000 17.250 1.4708 0.04384 0.03911 0.0261 0.0113 1.0000 17.500 1.4712 0.04636 0.04173 0.0265 0.0112 1.0000 17.750 1.4701 0.04917 0.04464 0.0266 0.0111 1.0000 18.000 1.4673 0.05230 0.04787 0.0264 0.0110 1.0000 18.250 1.4626 0.05580 0.05148 0.0259 0.0109 1.0000 18.500 1.4560 0.05973 0.05553 0.0250 0.0108 1.0000 18.750 1.4471 0.06418 0.06009 0.0237 0.0108 1.0000 19.000 1.4350 0.06927 0.06532 0.0219 0.0107 1.0000 19.250 1.4195 0.07510 0.07128 0.0195 0.0107 1.0000