XFOIL Version 6.94 Calculated polar for: LOCKHEED L-188 TIP AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3458 0.00755 0.00320 -0.0824 0.8305 0.8103 0.500 0.3979 0.00729 0.00308 -0.0808 0.8204 0.8673 1.000 0.4521 0.00717 0.00311 -0.0800 0.8077 0.9109 1.500 0.5208 0.00702 0.00294 -0.0822 0.7884 0.9543 2.000 0.5974 0.00695 0.00276 -0.0864 0.7605 0.9864 2.500 0.6720 0.00703 0.00273 -0.0906 0.7356 1.0000 3.000 0.7199 0.00718 0.00279 -0.0890 0.7089 1.0000 3.500 0.7674 0.00739 0.00290 -0.0872 0.6770 1.0000 4.000 0.8139 0.00769 0.00308 -0.0851 0.6369 1.0000 4.500 0.8571 0.00817 0.00334 -0.0825 0.5784 1.0000 5.000 0.8908 0.00914 0.00381 -0.0781 0.4672 1.0000 5.500 0.9128 0.01098 0.00478 -0.0722 0.3024 1.0000 6.500 0.9815 0.01357 0.00654 -0.0652 0.1478 1.0000 7.000 1.0185 0.01463 0.00741 -0.0621 0.1138 1.0000 7.500 1.0533 0.01566 0.00835 -0.0586 0.0926 1.0000 8.000 1.0876 0.01678 0.00942 -0.0552 0.0779 1.0000 8.500 1.1224 0.01793 0.01056 -0.0521 0.0671 1.0000 9.000 1.1553 0.01922 0.01185 -0.0488 0.0589 1.0000 9.500 1.1870 0.02063 0.01330 -0.0456 0.0527 1.0000 11.000 1.2699 0.02595 0.01880 -0.0354 0.0399 1.0000 11.500 1.2983 0.02774 0.02073 -0.0325 0.0368 1.0000 12.000 1.3195 0.03017 0.02327 -0.0291 0.0344 1.0000 12.500 1.3432 0.03240 0.02563 -0.0262 0.0320 1.0000 13.000 1.3608 0.03528 0.02864 -0.0231 0.0301 1.0000 13.500 1.3792 0.03811 0.03168 -0.0203 0.0284 1.0000 14.000 1.3922 0.04156 0.03518 -0.0176 0.0270 1.0000 14.500 1.4028 0.04536 0.03928 -0.0150 0.0258 1.0000 15.000 1.4111 0.04950 0.04367 -0.0130 0.0246 1.0000 15.500 1.4176 0.05396 0.04825 -0.0115 0.0236 1.0000 16.000 1.4157 0.05971 0.05426 -0.0103 0.0228 1.0000 16.500 1.4092 0.06639 0.06130 -0.0102 0.0220 1.0000 17.000 1.3988 0.07403 0.06926 -0.0110 0.0214 1.0000 17.500 1.3856 0.08251 0.07801 -0.0129 0.0208 1.0000 18.000 1.3704 0.09179 0.08753 -0.0159 0.0204 1.0000 18.500 1.3527 0.10185 0.09780 -0.0198 0.0200 1.0000 19.000 1.3250 0.11415 0.11038 -0.0254 0.0197 1.0000 19.500 1.2847 0.13029 0.12689 -0.0348 0.0196 1.0000 20.000 1.2362 0.14994 0.14692 -0.0477 0.0196 1.0000