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 = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3236 0.01002 0.00539 -0.0789 0.8482 0.8848 0.500 0.3891 0.00977 0.00520 -0.0797 0.8415 0.9374 1.000 0.4636 0.00981 0.00525 -0.0837 0.8302 0.9692 1.500 0.5507 0.00955 0.00494 -0.0902 0.8214 0.9894 2.000 0.6199 0.00891 0.00419 -0.0926 0.7964 1.0000 2.500 0.6664 0.00876 0.00395 -0.0906 0.7736 1.0000 3.000 0.7149 0.00876 0.00389 -0.0888 0.7492 1.0000 3.500 0.7640 0.00884 0.00390 -0.0871 0.7213 1.0000 4.000 0.8130 0.00901 0.00398 -0.0853 0.6885 1.0000 4.500 0.8592 0.00929 0.00415 -0.0831 0.6449 1.0000 5.000 0.9010 0.00977 0.00442 -0.0800 0.5783 1.0000 5.500 0.9284 0.01096 0.00497 -0.0744 0.4440 1.0000 6.000 0.9434 0.01307 0.00615 -0.0673 0.2809 1.0000 6.500 0.9705 0.01472 0.00730 -0.0627 0.1894 1.0000 7.000 1.0005 0.01611 0.00840 -0.0585 0.1409 1.0000 7.500 1.0308 0.01745 0.00959 -0.0544 0.1129 1.0000 8.000 1.0622 0.01883 0.01091 -0.0507 0.0944 1.0000 8.500 1.0926 0.02034 0.01238 -0.0471 0.0813 1.0000 9.000 1.1210 0.02208 0.01408 -0.0434 0.0716 1.0000 9.500 1.1508 0.02379 0.01581 -0.0401 0.0638 1.0000 10.000 1.1808 0.02555 0.01763 -0.0370 0.0577 1.0000 11.000 1.2388 0.02954 0.02184 -0.0309 0.0481 1.0000 11.500 1.2666 0.03184 0.02419 -0.0280 0.0446 1.0000 12.000 1.2929 0.03405 0.02656 -0.0252 0.0412 1.0000 12.500 1.3188 0.03679 0.02949 -0.0223 0.0386 1.0000 13.000 1.3411 0.03946 0.03231 -0.0196 0.0362 1.0000 13.500 1.3594 0.04283 0.03594 -0.0167 0.0341 1.0000 14.000 1.3715 0.04642 0.03981 -0.0138 0.0323 1.0000 14.500 1.3913 0.05016 0.04360 -0.0116 0.0309 1.0000 15.000 1.3803 0.05594 0.04995 -0.0086 0.0299 1.0000 15.500 1.3674 0.06251 0.05698 -0.0067 0.0290 1.0000 16.000 1.3552 0.06935 0.06414 -0.0061 0.0282 1.0000 16.500 1.3435 0.07656 0.07160 -0.0066 0.0275 1.0000 17.000 1.3290 0.08486 0.08009 -0.0077 0.0268 1.0000 17.500 1.2822 0.09886 0.09461 -0.0135 0.0267 1.0000 18.000 1.2314 0.11587 0.11208 -0.0229 0.0267 1.0000