XFOIL Version 6.96 Calculated polar for: LOCKHEED C-141 BL426.57 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 ------ -------- --------- --------- -------- -------- -------- -17.000 -1.0058 0.09309 0.09071 -0.0384 1.0000 0.0092 -16.750 -1.1587 0.05864 0.05571 -0.0599 1.0000 0.0089 -16.500 -1.1881 0.04954 0.04639 -0.0667 1.0000 0.0088 -16.250 -1.2041 0.04388 0.04056 -0.0701 1.0000 0.0089 -16.000 -1.2134 0.03983 0.03637 -0.0718 1.0000 0.0089 -15.750 -1.2190 0.03668 0.03309 -0.0724 1.0000 0.0090 -15.500 -1.2212 0.03419 0.03047 -0.0722 1.0000 0.0090 -15.250 -1.2211 0.03214 0.02831 -0.0713 1.0000 0.0091 -15.000 -1.2193 0.03043 0.02649 -0.0700 1.0000 0.0092 -14.750 -1.2158 0.02900 0.02496 -0.0683 1.0000 0.0093 -14.500 -1.2113 0.02780 0.02366 -0.0662 1.0000 0.0094 -14.250 -1.2072 0.02680 0.02257 -0.0636 1.0000 0.0095 -14.000 -1.2085 0.02601 0.02170 -0.0594 1.0000 0.0096 -13.750 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-0.0433 0.7189 0.7567 0.750 0.2602 0.00510 0.00103 -0.0423 0.6889 0.7978 1.000 0.2836 0.00518 0.00109 -0.0412 0.6556 0.8281 1.250 0.3078 0.00533 0.00116 -0.0404 0.6200 0.8448 1.500 0.3315 0.00554 0.00125 -0.0395 0.5761 0.8595 1.750 0.3550 0.00579 0.00135 -0.0386 0.5279 0.8742 2.000 0.3777 0.00612 0.00149 -0.0375 0.4688 0.8884 2.250 0.3989 0.00658 0.00167 -0.0363 0.3910 0.9023 2.500 0.4210 0.00700 0.00186 -0.0352 0.3252 0.9159 2.750 0.4438 0.00739 0.00204 -0.0342 0.2686 0.9290 3.000 0.4673 0.00771 0.00221 -0.0334 0.2256 0.9407 3.250 0.4921 0.00805 0.00239 -0.0329 0.1867 0.9487 3.500 0.5168 0.00835 0.00256 -0.0323 0.1559 0.9565 3.750 0.5441 0.00862 0.00273 -0.0323 0.1324 0.9623 4.000 0.5700 0.00887 0.00290 -0.0320 0.1135 0.9688 4.250 0.5985 0.00912 0.00307 -0.0324 0.0978 0.9730 4.500 0.6276 0.00937 0.00326 -0.0328 0.0851 0.9771 4.750 0.6548 0.00962 0.00345 -0.0328 0.0732 0.9820 5.000 0.6844 0.00989 0.00366 -0.0334 0.0624 0.9848 5.250 0.7149 0.01016 0.00388 -0.0343 0.0538 0.9871 5.500 0.7456 0.01041 0.00410 -0.0351 0.0480 0.9894 5.750 0.7754 0.01068 0.00433 -0.0358 0.0428 0.9919 6.000 0.8051 0.01094 0.00457 -0.0364 0.0389 0.9942 6.250 0.8365 0.01122 0.00483 -0.0375 0.0349 0.9957 6.500 0.8675 0.01151 0.00510 -0.0384 0.0314 0.9975 6.750 0.8979 0.01181 0.00538 -0.0393 0.0285 0.9993 7.000 0.9225 0.01207 0.00565 -0.0388 0.0265 1.0000 7.250 0.9412 0.01234 0.00590 -0.0371 0.0246 1.0000 7.500 0.9604 0.01260 0.00617 -0.0355 0.0231 1.0000 7.750 0.9802 0.01286 0.00644 -0.0340 0.0219 1.0000 8.000 0.9998 0.01315 0.00674 -0.0325 0.0206 1.0000 8.250 1.0195 0.01349 0.00708 -0.0310 0.0192 1.0000 8.500 1.0405 0.01379 0.00739 -0.0298 0.0184 1.0000 8.750 1.0616 0.01410 0.00773 -0.0287 0.0175 1.0000 9.000 1.0826 0.01446 0.00810 -0.0276 0.0166 1.0000 9.250 1.1033 0.01485 0.00850 -0.0264 0.0158 1.0000 9.500 1.1237 0.01528 0.00895 -0.0252 0.0152 1.0000 9.750 1.1447 0.01566 0.00936 -0.0242 0.0148 1.0000 10.000 1.1653 0.01606 0.00981 -0.0231 0.0144 1.0000 10.250 1.1853 0.01648 0.01027 -0.0219 0.0140 1.0000 10.500 1.2043 0.01691 0.01073 -0.0205 0.0136 1.0000 10.750 1.2225 0.01737 0.01123 -0.0190 0.0133 1.0000 11.000 1.2403 0.01787 0.01177 -0.0175 0.0129 1.0000 11.250 1.2572 0.01843 0.01236 -0.0159 0.0125 1.0000 11.500 1.2727 0.01911 0.01309 -0.0141 0.0121 1.0000 11.750 1.2900 0.01964 0.01367 -0.0127 0.0119 1.0000 12.000 1.3069 0.02020 0.01429 -0.0112 0.0117 1.0000 12.250 1.3229 0.02081 0.01497 -0.0097 0.0115 1.0000 12.500 1.3384 0.02147 0.01569 -0.0081 0.0113 1.0000 12.750 1.3531 0.02216 0.01646 -0.0065 0.0111 1.0000 13.000 1.3675 0.02290 0.01726 -0.0048 0.0109 1.0000 13.250 1.3811 0.02368 0.01810 -0.0032 0.0108 1.0000 13.500 1.3940 0.02451 0.01900 -0.0016 0.0106 1.0000 13.750 1.4063 0.02540 0.01996 0.0001 0.0104 1.0000 14.000 1.4176 0.02635 0.02099 0.0017 0.0102 1.0000 14.250 1.4280 0.02740 0.02210 0.0034 0.0101 1.0000 14.500 1.4370 0.02856 0.02334 0.0051 0.0099 1.0000 14.750 1.4446 0.02985 0.02472 0.0068 0.0098 1.0000 15.000 1.4500 0.03135 0.02630 0.0086 0.0096 1.0000 15.250 1.4519 0.03317 0.02823 0.0104 0.0094 1.0000 15.500 1.4559 0.03489 0.03005 0.0119 0.0093 1.0000 15.750 1.4617 0.03651 0.03176 0.0130 0.0092 1.0000 16.000 1.4661 0.03830 0.03367 0.0141 0.0092 1.0000 16.250 1.4684 0.04037 0.03584 0.0150 0.0091 1.0000 16.500 1.4695 0.04265 0.03824 0.0158 0.0090 1.0000 16.750 1.4684 0.04525 0.04095 0.0163 0.0089 1.0000 17.000 1.4659 0.04815 0.04398 0.0165 0.0089 1.0000 17.250 1.4618 0.05144 0.04738 0.0163 0.0088 1.0000 17.500 1.4554 0.05519 0.05126 0.0157 0.0087 1.0000 17.750 1.4466 0.05950 0.05571 0.0146 0.0087 1.0000 18.000 1.4357 0.06442 0.06076 0.0130 0.0086 1.0000 18.250 1.4208 0.07022 0.06672 0.0106 0.0086 1.0000 18.500 1.4012 0.07715 0.07380 0.0073 0.0086 1.0000 18.750 1.3763 0.08543 0.08226 0.0030 0.0086 1.0000 19.000 1.3427 0.09568 0.09269 -0.0024 0.0086 1.0000 19.250 1.2999 0.10805 0.10526 -0.0090 0.0086 1.0000