XFOIL Version 6.94 Calculated polar for: LOCKHEED L-188 ROOT 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 0.2631 0.00793 0.00311 -0.0615 0.7769 0.7597 0.500 0.3186 0.00798 0.00320 -0.0611 0.7653 0.7834 1.000 0.3760 0.00801 0.00319 -0.0613 0.7542 0.7979 1.500 0.4309 0.00791 0.00309 -0.0607 0.7334 0.8128 2.000 0.4853 0.00786 0.00301 -0.0601 0.7099 0.8286 2.500 0.5398 0.00786 0.00305 -0.0596 0.6908 0.8471 3.000 0.5936 0.00788 0.00313 -0.0589 0.6707 0.8680 3.500 0.6457 0.00793 0.00324 -0.0578 0.6477 0.8949 4.000 0.6981 0.00805 0.00339 -0.0567 0.6198 0.9311 4.500 0.7619 0.00833 0.00362 -0.0583 0.5766 0.9689 5.500 0.8524 0.01082 0.00484 -0.0561 0.3134 1.0000 6.000 0.8823 0.01215 0.00567 -0.0518 0.2226 1.0000 6.500 0.9178 0.01324 0.00646 -0.0486 0.1689 1.0000 7.000 0.9545 0.01425 0.00727 -0.0456 0.1349 1.0000 7.500 0.9890 0.01522 0.00813 -0.0422 0.1129 1.0000 8.000 1.0226 0.01628 0.00910 -0.0387 0.0970 1.0000 8.500 1.0550 0.01750 0.01026 -0.0354 0.0851 1.0000 9.000 1.0886 0.01873 0.01148 -0.0325 0.0758 1.0000 10.000 1.1535 0.02150 0.01430 -0.0269 0.0623 1.0000 10.500 1.1837 0.02310 0.01598 -0.0241 0.0573 1.0000 11.000 1.2104 0.02500 0.01792 -0.0211 0.0532 1.0000 11.500 1.2381 0.02688 0.01985 -0.0185 0.0494 1.0000 12.500 1.2860 0.03140 0.02454 -0.0133 0.0438 1.0000 13.000 1.3075 0.03397 0.02725 -0.0108 0.0413 1.0000 13.500 1.3283 0.03664 0.03002 -0.0087 0.0391 1.0000 14.000 1.3432 0.03992 0.03341 -0.0062 0.0374 1.0000 14.500 1.3598 0.04315 0.03685 -0.0044 0.0357 1.0000 15.000 1.3736 0.04673 0.04053 -0.0029 0.0342 1.0000 15.500 1.3825 0.05097 0.04491 -0.0013 0.0329 1.0000 16.000 1.3898 0.05561 0.04982 -0.0004 0.0316 1.0000 16.500 1.3954 0.06063 0.05502 0.0000 0.0305 1.0000 17.000 1.3991 0.06595 0.06046 0.0001 0.0296 1.0000 17.500 1.3953 0.07236 0.06707 0.0001 0.0288 1.0000 18.000 1.3849 0.08030 0.07535 -0.0017 0.0281 1.0000 18.500 1.3709 0.08915 0.08451 -0.0044 0.0274 1.0000 19.000 1.3555 0.09868 0.09431 -0.0081 0.0267 1.0000 19.500 1.3404 0.10850 0.10434 -0.0125 0.0262 1.0000 20.000 1.3265 0.11834 0.11434 -0.0174 0.0256 1.0000 21.000 1.2589 0.14737 0.14399 -0.0347 0.0250 1.0000