XFOIL Version 6.96 Calculated polar for: Smoothed ATR airfoil coordinates obtained using 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.3954 0.10016 0.09272 -0.0351 1.0000 0.0702 -10.250 -0.4019 0.09509 0.08772 -0.0375 1.0000 0.0702 -10.000 -0.4120 0.08939 0.08208 -0.0405 1.0000 0.0701 -9.750 -0.4287 0.08243 0.07517 -0.0450 1.0000 0.0701 -9.500 -0.4526 0.07596 0.06873 -0.0487 1.0000 0.0697 -9.250 -0.4805 0.07107 0.06384 -0.0496 1.0000 0.0691 -9.000 -0.5113 0.06750 0.06026 -0.0473 1.0000 0.0690 -8.750 -0.5370 0.06410 0.05679 -0.0446 1.0000 0.0689 -8.500 -0.5587 0.06094 0.05350 -0.0413 1.0000 0.0692 -8.250 -0.5772 0.05788 0.05026 -0.0378 1.0000 0.0696 -8.000 -0.5922 0.05490 0.04704 -0.0340 1.0000 0.0702 -7.750 -0.6032 0.05197 0.04380 -0.0303 1.0000 0.0709 -7.500 -0.6104 0.04910 0.04056 -0.0267 1.0000 0.0716 -7.250 -0.6119 0.04651 0.03765 -0.0234 1.0000 0.0724 -7.000 -0.6042 0.04501 0.03614 -0.0211 1.0000 0.0739 -6.750 -0.5963 0.04362 0.03468 -0.0187 1.0000 0.0758 -6.500 -0.5894 0.04194 0.03279 -0.0162 1.0000 0.0783 -6.250 -0.5823 0.03995 0.03040 -0.0136 1.0000 0.0810 -6.000 -0.5724 0.03808 0.02818 -0.0113 1.0000 0.0833 -5.750 -0.5519 0.03695 0.02708 -0.0109 0.9971 0.0865 -5.500 -0.5165 0.03536 0.02516 -0.0130 0.9881 0.0923 -5.250 -0.4769 0.03389 0.02354 -0.0158 0.9776 0.0981 -5.000 -0.4315 0.03252 0.02187 -0.0192 0.9645 0.1066 -4.750 -0.3830 0.03127 0.02065 -0.0231 0.9491 0.1156 -4.500 -0.3332 0.02999 0.01927 -0.0267 0.9332 0.1261 -4.250 -0.2855 0.02888 0.01805 -0.0299 0.9188 0.1384 -4.000 -0.2367 0.02784 0.01700 -0.0333 0.9073 0.1537 -3.750 -0.1987 0.02693 0.01612 -0.0348 0.8924 0.1698 -3.500 -0.1644 0.02598 0.01527 -0.0357 0.8765 0.1894 -3.250 -0.1329 0.02501 0.01444 -0.0360 0.8596 0.2172 -3.000 -0.1048 0.02391 0.01363 -0.0359 0.8417 0.2599 -2.750 -0.0844 0.02259 0.01304 -0.0343 0.8231 0.3567 -2.500 -0.0657 0.02145 0.01298 -0.0311 0.8044 0.5621 -2.250 -0.0354 0.02122 0.01313 -0.0289 0.7823 0.7092 -2.000 0.0131 0.02137 0.01328 -0.0294 0.7579 0.7936 -1.750 0.0602 0.02162 0.01328 -0.0302 0.7307 0.8462 -1.500 0.1125 0.02195 0.01327 -0.0321 0.6986 0.8906 -1.250 0.1898 0.02228 0.01311 -0.0387 0.6552 0.9308 -1.000 0.2419 0.02232 0.01268 -0.0424 0.6162 0.9549 -0.750 0.2831 0.02227 0.01221 -0.0449 0.5812 0.9685 -0.500 0.3236 0.02224 0.01181 -0.0475 0.5497 0.9803 -0.250 0.3641 0.02222 0.01144 -0.0503 0.5234 0.9916 0.000 0.3987 0.02224 0.01119 -0.0523 0.5012 1.0000 0.250 0.4158 0.02237 0.01111 -0.0508 0.4856 1.0000 0.500 0.4337 0.02252 0.01104 -0.0495 0.4724 1.0000 0.750 0.4520 0.02270 0.01105 -0.0482 0.4602 1.0000 1.000 0.4706 0.02291 0.01111 -0.0469 0.4495 1.0000 1.250 0.4897 0.02315 0.01114 -0.0456 0.4404 1.0000 1.500 0.5086 0.02343 0.01134 -0.0444 0.4307 1.0000 1.750 0.5285 0.02373 0.01143 -0.0432 0.4234 1.0000 2.000 0.5477 0.02407 0.01174 -0.0419 0.4153 1.0000 2.250 0.5678 0.02443 0.01195 -0.0407 0.4085 1.0000 2.500 0.5877 0.02483 0.01227 -0.0395 0.4019 1.0000 2.750 0.6070 0.02525 0.01264 -0.0383 0.3951 1.0000 3.000 0.6280 0.02567 0.01291 -0.0371 0.3896 1.0000 3.250 0.6472 0.02619 0.01343 -0.0359 0.3838 1.0000 3.500 0.6665 0.02671 0.01394 -0.0346 0.3782 1.0000 3.750 0.6873 0.02721 0.01434 -0.0335 0.3734 1.0000 4.000 0.7071 0.02779 0.01488 -0.0322 0.3686 1.0000 4.250 0.7246 0.02844 0.01559 -0.0308 0.3631 1.0000 4.500 0.7441 0.02904 0.01617 -0.0295 0.3584 1.0000 4.750 0.7658 0.02963 0.01666 -0.0285 0.3545 1.0000 5.000 0.7827 0.03042 0.01753 -0.0270 0.3502 1.0000 5.250 0.7988 0.03124 0.01844 -0.0254 0.3455 1.0000 5.500 0.8174 0.03197 0.01917 -0.0241 0.3412 1.0000 5.750 0.8387 0.03262 0.01976 -0.0231 0.3376 1.0000 6.000 0.8546 0.03355 0.02076 -0.0216 0.3337 1.0000 6.250 0.8667 0.03465 0.02203 -0.0196 0.3296 1.0000 6.500 0.8818 0.03564 0.02311 -0.0181 0.3257 1.0000 6.750 0.9008 0.03646 0.02392 -0.0169 0.3222 1.0000 7.000 0.9240 0.03716 0.02455 -0.0162 0.3191 1.0000 7.250 0.9276 0.03875 0.02639 -0.0136 0.3149 1.0000 7.500 0.9347 0.04022 0.02803 -0.0114 0.3110 1.0000 7.750 0.9467 0.04148 0.02940 -0.0097 0.3075 1.0000 8.000 0.9644 0.04247 0.03040 -0.0086 0.3045 1.0000 8.250 0.9876 0.04326 0.03114 -0.0081 0.3017 1.0000 8.500 0.9685 0.04615 0.03438 -0.0039 0.2975 1.0000 8.750 0.9573 0.04870 0.03713 -0.0008 0.2936 1.0000 9.000 0.9571 0.05068 0.03922 0.0013 0.2903 1.0000 9.250 0.9684 0.05208 0.04067 0.0026 0.2876 1.0000 9.500 0.9967 0.05263 0.04119 0.0028 0.2852 1.0000 9.750 0.7697 0.07512 0.06406 0.0042 0.2734 1.0000 10.000 0.7852 0.07635 0.06531 0.0048 0.2707 1.0000 10.250 0.8126 0.07597 0.06494 0.0063 0.2692 1.0000 10.750 0.7299 0.09492 0.08399 -0.0014 0.2552 1.0000 11.000 0.7515 0.09554 0.08463 -0.0005 0.2531 1.0000