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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.000 -0.8795 0.07562 0.07209 -0.0497 1.0000 0.0165 -15.750 -0.9288 0.06229 0.05847 -0.0590 1.0000 0.0164 -15.500 -0.9551 0.05407 0.05004 -0.0650 1.0000 0.0164 -15.250 -0.9690 0.04855 0.04437 -0.0687 1.0000 0.0165 -15.000 -0.9823 0.04382 0.03947 -0.0712 1.0000 0.0165 -14.750 -0.9892 0.04038 0.03590 -0.0724 1.0000 0.0166 -14.500 -0.9940 0.03752 0.03291 -0.0728 1.0000 0.0167 -14.250 -0.9952 0.03528 0.03056 -0.0725 1.0000 0.0168 -14.000 -0.9966 0.03324 0.02840 -0.0716 1.0000 0.0170 -13.750 -0.9961 0.03154 0.02658 -0.0702 1.0000 0.0171 -13.500 -0.9939 0.03009 0.02502 -0.0684 1.0000 0.0173 -13.250 -0.9904 0.02883 0.02365 -0.0663 1.0000 0.0174 -13.000 -0.9869 0.02766 0.02239 -0.0639 1.0000 0.0175 -12.750 -0.9821 0.02667 0.02130 -0.0612 1.0000 0.0177 -12.500 -0.9786 0.02576 0.02030 -0.0580 1.0000 0.0178 -12.250 -0.9749 0.02502 0.01947 -0.0545 1.0000 0.0179 -12.000 -0.9710 0.02431 0.01869 -0.0508 1.0000 0.0180 -11.750 -0.9663 0.02353 0.01786 -0.0474 1.0000 0.0182 -11.500 -0.9541 0.02271 0.01698 -0.0453 0.9982 0.0184 -11.250 -0.9288 0.02179 0.01601 -0.0457 0.9908 0.0187 -11.000 -0.9017 0.02099 0.01516 -0.0463 0.9856 0.0190 -10.500 -0.8431 0.01954 0.01359 -0.0480 0.9764 0.0197 -10.250 -0.8129 0.01886 0.01284 -0.0489 0.9718 0.0201 -10.000 -0.7826 0.01822 0.01214 -0.0497 0.9671 0.0206 -9.750 -0.7544 0.01763 0.01148 -0.0501 0.9613 0.0210 -9.500 -0.7242 0.01705 0.01083 -0.0508 0.9563 0.0214 -9.250 -0.6975 0.01647 0.01021 -0.0508 0.9476 0.0220 -9.000 -0.6702 0.01597 0.00968 -0.0508 0.9374 0.0227 -8.750 -0.6460 0.01557 0.00922 -0.0501 0.9267 0.0234 -8.500 -0.6226 0.01519 0.00879 -0.0492 0.9170 0.0242 -8.250 -0.5989 0.01482 0.00835 -0.0483 0.9077 0.0249 -8.000 -0.5764 0.01446 0.00793 -0.0471 0.8967 0.0257 -7.750 -0.5534 0.01409 0.00753 -0.0461 0.8862 0.0267 -7.500 -0.5299 0.01377 0.00717 -0.0451 0.8748 0.0278 -7.250 -0.5061 0.01348 0.00683 -0.0442 0.8632 0.0291 -7.000 -0.4822 0.01317 0.00648 -0.0432 0.8506 0.0305 -6.750 -0.4583 0.01291 0.00617 -0.0422 0.8344 0.0323 -6.500 -0.4341 0.01268 0.00586 -0.0413 0.8156 0.0344 -6.250 -0.4103 0.01246 0.00558 -0.0403 0.7924 0.0367 -6.000 -0.3862 0.01229 0.00531 -0.0393 0.7674 0.0393 -5.750 -0.3623 0.01215 0.00505 -0.0383 0.7404 0.0417 -5.500 -0.3382 0.01202 0.00483 -0.0374 0.7145 0.0444 -5.250 -0.3139 0.01194 0.00461 -0.0365 0.6861 0.0469 -5.000 -0.2897 0.01182 0.00440 -0.0356 0.6597 0.0495 -4.750 -0.2652 0.01174 0.00421 -0.0347 0.6326 0.0525 -4.500 -0.2406 0.01168 0.00403 -0.0339 0.6067 0.0553 -4.250 -0.2162 0.01160 0.00386 -0.0331 0.5816 0.0587 -4.000 -0.1913 0.01155 0.00371 -0.0324 0.5583 0.0620 -3.750 -0.1664 0.01147 0.00356 -0.0317 0.5332 0.0661 -3.500 -0.1415 0.01143 0.00343 -0.0310 0.5036 0.0710 -3.250 -0.1174 0.01143 0.00330 -0.0301 0.4625 0.0771 -3.000 -0.0933 0.01148 0.00319 -0.0293 0.4249 0.0836 -2.750 -0.0686 0.01147 0.00310 -0.0286 0.3998 0.0921 -2.500 -0.0435 0.01144 0.00303 -0.0280 0.3819 0.1030 -2.250 -0.0181 0.01139 0.00295 -0.0274 0.3687 0.1166 -2.000 0.0076 0.01132 0.00289 -0.0269 0.3582 0.1318 -1.750 0.0334 0.01124 0.00283 -0.0264 0.3498 0.1502 -1.500 0.0590 0.01115 0.00277 -0.0259 0.3418 0.1728 -1.250 0.0843 0.01105 0.00272 -0.0253 0.3345 0.2012 -1.000 0.1093 0.01087 0.00266 -0.0247 0.3279 0.2428 -0.750 0.1315 0.01047 0.00258 -0.0237 0.3215 0.3451 -0.500 0.1543 0.01015 0.00255 -0.0228 0.3166 0.4403 -0.250 0.1776 0.00990 0.00253 -0.0218 0.3119 0.5137 0.000 0.1997 0.00965 0.00255 -0.0206 0.3073 0.5964 0.250 0.2226 0.00952 0.00260 -0.0194 0.3028 0.6641 0.500 0.2464 0.00940 0.00264 -0.0184 0.2990 0.7164 0.750 0.2704 0.00931 0.00270 -0.0173 0.2947 0.7598 1.000 0.2949 0.00929 0.00278 -0.0163 0.2902 0.7988 1.250 0.3199 0.00934 0.00290 -0.0154 0.2863 0.8354 1.500 0.3460 0.00941 0.00302 -0.0147 0.2832 0.8663 1.750 0.3721 0.00951 0.00315 -0.0140 0.2801 0.8933 2.000 0.3985 0.00963 0.00327 -0.0134 0.2767 0.9125 2.250 0.4243 0.00975 0.00336 -0.0127 0.2731 0.9236 2.500 0.4528 0.00991 0.00346 -0.0127 0.2694 0.9305 2.750 0.4784 0.01001 0.00354 -0.0121 0.2666 0.9390 3.000 0.5097 0.01013 0.00365 -0.0127 0.2637 0.9441 3.250 0.5379 0.01026 0.00376 -0.0126 0.2608 0.9521 3.500 0.5708 0.01043 0.00390 -0.0136 0.2576 0.9584 3.750 0.6035 0.01062 0.00404 -0.0146 0.2546 0.9644 4.000 0.6337 0.01079 0.00417 -0.0150 0.2518 0.9695 4.250 0.6685 0.01092 0.00430 -0.0165 0.2491 0.9716 4.500 0.7025 0.01107 0.00443 -0.0178 0.2461 0.9737 4.750 0.7351 0.01123 0.00458 -0.0189 0.2434 0.9761 5.000 0.7659 0.01141 0.00472 -0.0196 0.2407 0.9793 5.250 0.7960 0.01161 0.00488 -0.0202 0.2379 0.9822 5.500 0.8294 0.01177 0.00505 -0.0214 0.2356 0.9837 5.750 0.8624 0.01192 0.00520 -0.0226 0.2330 0.9856 6.000 0.8944 0.01209 0.00537 -0.0236 0.2304 0.9879 6.250 0.9252 0.01227 0.00555 -0.0244 0.2280 0.9905 6.500 0.9546 0.01247 0.00574 -0.0249 0.2255 0.9931 6.750 0.9860 0.01270 0.00594 -0.0259 0.2228 0.9953 7.000 1.0175 0.01289 0.00615 -0.0268 0.2205 0.9975 7.250 1.0493 0.01307 0.00635 -0.0279 0.2183 0.9995 7.500 1.0713 0.01325 0.00655 -0.0269 0.2162 1.0000 7.750 1.0889 0.01342 0.00674 -0.0250 0.2142 1.0000 8.000 1.1061 0.01361 0.00694 -0.0231 0.2120 1.0000 8.250 1.1229 0.01382 0.00714 -0.0211 0.2097 1.0000 8.500 1.1395 0.01407 0.00738 -0.0191 0.2074 1.0000 8.750 1.1583 0.01426 0.00761 -0.0175 0.2059 1.0000 9.000 1.1774 0.01445 0.00784 -0.0159 0.2040 1.0000 9.250 1.1961 0.01466 0.00808 -0.0144 0.2018 1.0000 9.500 1.2145 0.01488 0.00833 -0.0128 0.1994 1.0000 9.750 1.2324 0.01514 0.00860 -0.0111 0.1973 1.0000 10.000 1.2491 0.01542 0.00889 -0.0093 0.1950 1.0000 10.250 1.2639 0.01572 0.00920 -0.0071 0.1928 1.0000 10.500 1.2815 0.01596 0.00949 -0.0054 0.1910 1.0000 10.750 1.2988 0.01622 0.00981 -0.0038 0.1889 1.0000 11.000 1.3157 0.01652 0.01015 -0.0021 0.1866 1.0000 11.250 1.3321 0.01685 0.01051 -0.0005 0.1840 1.0000 11.500 1.3477 0.01723 0.01091 0.0012 0.1817 1.0000 11.750 1.3622 0.01769 0.01137 0.0030 0.1793 1.0000 12.000 1.3801 0.01803 0.01179 0.0042 0.1773 1.0000 12.250 1.3971 0.01843 0.01225 0.0055 0.1750 1.0000 12.500 1.4131 0.01887 0.01275 0.0069 0.1725 1.0000 12.750 1.4278 0.01938 0.01329 0.0084 0.1697 1.0000 13.000 1.4410 0.01998 0.01391 0.0099 0.1671 1.0000 13.250 1.4551 0.02057 0.01456 0.0113 0.1649 1.0000 13.500 1.4707 0.02111 0.01518 0.0124 0.1625 1.0000 13.750 1.4845 0.02175 0.01588 0.0137 0.1592 1.0000 14.000 1.4964 0.02252 0.01668 0.0150 0.1563 1.0000 14.250 1.5056 0.02347 0.01765 0.0164 0.1531 1.0000 14.500 1.5189 0.02423 0.01849 0.0175 0.1494 1.0000 14.750 1.5288 0.02523 0.01953 0.0186 0.1448 1.0000 15.000 1.5340 0.02658 0.02089 0.0199 0.1398 1.0000 15.250 1.5424 0.02780 0.02216 0.0208 0.1339 1.0000 15.500 1.5450 0.02950 0.02389 0.0218 0.1290 1.0000 15.750 1.5508 0.03106 0.02552 0.0225 0.1254 1.0000 16.000 1.5537 0.03293 0.02744 0.0231 0.1207 1.0000 16.250 1.5525 0.03526 0.02982 0.0235 0.1171 1.0000 16.500 1.5526 0.03760 0.03224 0.0237 0.1130 1.0000 16.750 1.5494 0.04038 0.03509 0.0237 0.1090 1.0000 17.000 1.5393 0.04406 0.03883 0.0232 0.1051 1.0000 17.250 1.5350 0.04725 0.04212 0.0226 0.1025 1.0000 17.500 1.5213 0.05164 0.04659 0.0216 0.0982 1.0000 17.750 1.5054 0.05648 0.05153 0.0202 0.0959 1.0000 18.000 1.4867 0.06189 0.05704 0.0185 0.0935 1.0000 18.250 1.4676 0.06752 0.06279 0.0165 0.0907 1.0000 18.500 1.4457 0.07364 0.06903 0.0143 0.0885 1.0000 18.750 1.4188 0.08056 0.07605 0.0116 0.0863 1.0000 19.000 1.3907 0.08778 0.08336 0.0087 0.0841 1.0000