XFOIL Version 6.96 Calculated polar for: CLARK YS AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4875 0.09143 0.08829 -0.0116 1.0000 0.0726 -9.250 -0.4897 0.08713 0.08403 -0.0149 1.0000 0.0749 -9.000 -0.5114 0.08066 0.07761 -0.0231 1.0000 0.0776 -8.750 -0.4307 0.06760 0.06464 -0.0293 0.9129 0.0823 -8.500 -0.5638 0.06716 0.06369 -0.0311 0.9266 0.0805 -8.250 -0.5367 0.06524 0.06188 -0.0306 0.9158 0.0821 -8.000 -0.5273 0.06299 0.05957 -0.0296 0.9045 0.0837 -7.750 -0.5249 0.06038 0.05684 -0.0282 0.8946 0.0858 -7.500 -0.5357 0.05709 0.05317 -0.0263 0.8843 0.0917 -7.250 -0.5503 0.05241 0.04807 -0.0232 0.8765 0.0947 -7.000 -0.5337 0.04974 0.04544 -0.0224 0.8697 0.0961 -6.750 -0.5200 0.04781 0.04343 -0.0209 0.8633 0.0981 -6.500 -0.5421 0.03531 0.02942 -0.0132 0.8570 0.0649 -6.250 -0.5297 0.03195 0.02571 -0.0108 0.8508 0.0624 -6.000 -0.5162 0.02861 0.02176 -0.0080 0.8455 0.0599 -5.750 -0.4957 0.02660 0.01939 -0.0065 0.8392 0.0597 -5.500 -0.4736 0.02542 0.01798 -0.0052 0.8334 0.0608 -5.250 -0.4496 0.02411 0.01642 -0.0043 0.8278 0.0614 -5.000 -0.4240 0.02283 0.01491 -0.0036 0.8218 0.0618 -4.750 -0.3983 0.02182 0.01370 -0.0028 0.8167 0.0626 -4.500 -0.3704 0.02089 0.01264 -0.0027 0.8105 0.0636 -4.250 -0.3434 0.02023 0.01184 -0.0023 0.8048 0.0653 -4.000 -0.3170 0.01982 0.01129 -0.0017 0.7994 0.0669 -3.750 -0.2878 0.01857 0.01009 -0.0019 0.7926 0.0694 -3.500 -0.2625 0.01803 0.00953 -0.0011 0.7868 0.0720 -3.250 -0.2362 0.01750 0.00902 -0.0007 0.7784 0.0754 -3.000 -0.2118 0.01712 0.00853 0.0005 0.7721 0.0794 -2.750 -0.1875 0.01643 0.00797 0.0013 0.7632 0.0877 -2.500 -0.1647 0.01586 0.00743 0.0027 0.7571 0.1033 -2.250 -0.1422 0.01499 0.00696 0.0037 0.7490 0.1641 -2.000 -0.1217 0.01427 0.00673 0.0052 0.7435 0.2754 -1.750 -0.1030 0.01366 0.00656 0.0069 0.7372 0.3794 -1.500 0.0065 0.01406 0.00869 -0.0061 0.7313 0.9160 -1.250 0.1537 0.01494 0.00924 -0.0279 0.7262 0.9767 -1.000 0.2393 0.01397 0.00814 -0.0397 0.7172 1.0000 -0.750 0.2631 0.01383 0.00788 -0.0387 0.7109 1.0000 -0.500 0.2878 0.01372 0.00772 -0.0381 0.7021 1.0000 -0.250 0.3119 0.01358 0.00748 -0.0372 0.6956 1.0000 0.000 0.3367 0.01348 0.00734 -0.0365 0.6868 1.0000 0.250 0.3609 0.01333 0.00710 -0.0356 0.6796 1.0000 0.500 0.3857 0.01323 0.00697 -0.0350 0.6696 1.0000 0.750 0.4101 0.01310 0.00675 -0.0341 0.6611 1.0000 1.000 0.4348 0.01300 0.00660 -0.0333 0.6504 1.0000 1.250 0.4595 0.01292 0.00648 -0.0326 0.6393 1.0000 1.500 0.4840 0.01285 0.00633 -0.0318 0.6286 1.0000 1.750 0.5086 0.01279 0.00620 -0.0310 0.6165 1.0000 2.000 0.5332 0.01275 0.00613 -0.0302 0.6023 1.0000 2.250 0.5577 0.01274 0.00605 -0.0295 0.5869 1.0000 2.500 0.5822 0.01275 0.00600 -0.0287 0.5708 1.0000 2.750 0.6066 0.01279 0.00596 -0.0280 0.5539 1.0000 3.000 0.6310 0.01287 0.00596 -0.0272 0.5360 1.0000 3.250 0.6555 0.01298 0.00602 -0.0266 0.5168 1.0000 3.500 0.6798 0.01312 0.00609 -0.0259 0.4987 1.0000 3.750 0.7041 0.01327 0.00617 -0.0253 0.4811 1.0000 4.000 0.7283 0.01344 0.00628 -0.0246 0.4648 1.0000 4.250 0.7525 0.01364 0.00642 -0.0240 0.4507 1.0000 4.500 0.7766 0.01385 0.00657 -0.0234 0.4372 1.0000 4.750 0.8005 0.01405 0.00673 -0.0228 0.4232 1.0000 5.000 0.8242 0.01428 0.00690 -0.0221 0.4103 1.0000 5.250 0.8480 0.01450 0.00712 -0.0215 0.3984 1.0000 5.500 0.8719 0.01474 0.00737 -0.0209 0.3879 1.0000 5.750 0.8953 0.01503 0.00763 -0.0202 0.3785 1.0000 6.000 0.9189 0.01527 0.00792 -0.0196 0.3688 1.0000 6.250 0.9421 0.01556 0.00822 -0.0189 0.3594 1.0000 6.500 0.9649 0.01588 0.00851 -0.0181 0.3495 1.0000 6.750 0.9878 0.01612 0.00886 -0.0174 0.3390 1.0000 7.000 1.0102 0.01645 0.00921 -0.0166 0.3292 1.0000 7.250 1.0322 0.01677 0.00953 -0.0158 0.3185 1.0000 7.500 1.0538 0.01703 0.00991 -0.0149 0.3059 1.0000 7.750 1.0748 0.01731 0.01026 -0.0140 0.2913 1.0000 8.000 1.0950 0.01760 0.01059 -0.0130 0.2741 1.0000 8.250 1.1143 0.01796 0.01096 -0.0119 0.2552 1.0000 8.500 1.1334 0.01833 0.01138 -0.0107 0.2319 1.0000 8.750 1.1498 0.01892 0.01191 -0.0093 0.2070 1.0000 9.000 1.1636 0.01971 0.01260 -0.0076 0.1844 1.0000 9.250 1.1752 0.02062 0.01341 -0.0056 0.1673 1.0000 9.500 1.1857 0.02152 0.01427 -0.0035 0.1543 1.0000 9.750 1.1967 0.02229 0.01508 -0.0013 0.1441 1.0000 10.000 1.2048 0.02314 0.01594 0.0013 0.1361 1.0000 10.250 1.2109 0.02395 0.01678 0.0041 0.1286 1.0000 10.500 1.2150 0.02474 0.01762 0.0073 0.1222 1.0000 10.750 1.2142 0.02551 0.01843 0.0111 0.1158 1.0000 11.000 1.1994 0.02644 0.01936 0.0168 0.1123 1.0000 11.250 1.1958 0.02720 0.02026 0.0207 0.1071 1.0000 11.500 1.1885 0.02826 0.02135 0.0246 0.1025 1.0000 11.750 1.1818 0.02943 0.02255 0.0282 0.0973 1.0000 12.000 1.1785 0.03057 0.02376 0.0312 0.0904 1.0000 12.250 1.1736 0.03198 0.02520 0.0341 0.0834 1.0000 12.500 1.1666 0.03377 0.02698 0.0366 0.0737 1.0000 12.750 1.1607 0.03578 0.02898 0.0386 0.0597 1.0000 13.000 1.1525 0.03816 0.03133 0.0404 0.0519 1.0000 13.250 1.1427 0.04092 0.03403 0.0417 0.0455 1.0000 13.500 1.1375 0.04346 0.03663 0.0427 0.0417 1.0000 13.750 1.1293 0.04646 0.03967 0.0433 0.0391 1.0000 14.000 1.1201 0.04972 0.04297 0.0436 0.0375 1.0000 14.250 1.1149 0.05272 0.04608 0.0437 0.0361 1.0000 14.500 1.1090 0.05601 0.04945 0.0436 0.0346 1.0000 14.750 1.1031 0.05943 0.05295 0.0432 0.0335 1.0000 15.000 1.0965 0.06304 0.05662 0.0427 0.0327 1.0000 15.250 1.0890 0.06680 0.06041 0.0421 0.0319 1.0000 15.500 1.0844 0.07021 0.06386 0.0417 0.0312 1.0000 15.750 1.0826 0.07340 0.06716 0.0412 0.0305 1.0000 16.000 1.0801 0.07676 0.07063 0.0405 0.0297 1.0000 16.250 1.0780 0.08010 0.07405 0.0398 0.0289 1.0000 16.500 1.0770 0.08327 0.07729 0.0392 0.0284 1.0000 16.750 1.0747 0.08671 0.08079 0.0383 0.0276 1.0000 17.000 1.0737 0.08989 0.08400 0.0376 0.0269 1.0000 17.250 1.0764 0.09231 0.08644 0.0377 0.0265 1.0000 17.500 1.0791 0.09467 0.08883 0.0380 0.0259 1.0000 17.750 1.0767 0.09836 0.09266 0.0370 0.0257 1.0000 18.000 1.0740 0.10211 0.09655 0.0359 0.0255 1.0000 18.250 1.0685 0.10650 0.10109 0.0343 0.0253 1.0000 18.500 1.0614 0.11125 0.10600 0.0324 0.0251 1.0000 18.750 1.0538 0.11615 0.11105 0.0303 0.0251 1.0000 19.000 1.0413 0.12217 0.11725 0.0274 0.0250 1.0000 19.250 1.0253 0.12910 0.12436 0.0238 0.0249 1.0000