XFOIL Version 6.96 Calculated polar for: SD7003-085-88 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 ------ -------- --------- --------- -------- -------- -------- -11.500 -0.9024 0.04286 0.04002 -0.0415 1.0000 0.0052 -11.250 -0.9194 0.03849 0.03542 -0.0428 1.0000 0.0052 -11.000 -0.9227 0.03480 0.03146 -0.0432 1.0000 0.0053 -10.750 -0.9166 0.03203 0.02844 -0.0431 1.0000 0.0054 -10.500 -0.9079 0.02933 0.02545 -0.0427 1.0000 0.0055 -10.250 -0.8941 0.02724 0.02311 -0.0423 1.0000 0.0056 -10.000 -0.8781 0.02540 0.02103 -0.0417 1.0000 0.0058 -9.750 -0.8604 0.02372 0.01912 -0.0412 1.0000 0.0060 -9.500 -0.8413 0.02223 0.01741 -0.0406 1.0000 0.0061 -9.250 -0.8210 0.02094 0.01591 -0.0400 1.0000 0.0063 -9.000 -0.7998 0.01978 0.01457 -0.0394 1.0000 0.0064 -8.750 -0.7777 0.01879 0.01342 -0.0388 1.0000 0.0066 -8.500 -0.7560 0.01769 0.01217 -0.0381 1.0000 0.0068 -8.250 -0.7337 0.01669 0.01106 -0.0375 1.0000 0.0072 -8.000 -0.7104 0.01600 0.01029 -0.0369 1.0000 0.0076 -7.750 -0.6866 0.01541 0.00960 -0.0363 1.0000 0.0081 -7.500 -0.6628 0.01480 0.00891 -0.0357 1.0000 0.0087 -7.250 -0.6389 0.01419 0.00820 -0.0350 1.0000 0.0092 -7.000 -0.6151 0.01357 0.00749 -0.0343 1.0000 0.0097 -6.750 -0.5911 0.01296 0.00685 -0.0337 1.0000 0.0106 -6.500 -0.5668 0.01250 0.00632 -0.0330 1.0000 0.0117 -6.250 -0.5423 0.01208 0.00583 -0.0323 1.0000 0.0130 -6.000 -0.5180 0.01161 0.00535 -0.0317 1.0000 0.0150 -5.750 -0.4934 0.01126 0.00497 -0.0310 1.0000 0.0175 -5.500 -0.4691 0.01090 0.00462 -0.0304 1.0000 0.0207 -5.250 -0.4381 0.01056 0.00426 -0.0311 0.9978 0.0245 -5.000 -0.4029 0.01026 0.00395 -0.0327 0.9940 0.0286 -4.750 -0.3692 0.00995 0.00366 -0.0340 0.9887 0.0347 -4.500 -0.3336 0.00966 0.00340 -0.0357 0.9838 0.0422 -4.250 -0.3010 0.00943 0.00316 -0.0366 0.9758 0.0487 -4.000 -0.2672 0.00916 0.00291 -0.0378 0.9672 0.0562 -3.750 -0.2328 0.00892 0.00268 -0.0391 0.9557 0.0642 -3.500 -0.1984 0.00870 0.00245 -0.0404 0.9400 0.0738 -3.250 -0.1648 0.00848 0.00224 -0.0414 0.9182 0.0864 -3.000 -0.1349 0.00828 0.00204 -0.0417 0.8903 0.1044 -2.750 -0.1078 0.00814 0.00187 -0.0413 0.8598 0.1254 -2.500 -0.0816 0.00801 0.00172 -0.0407 0.8293 0.1520 -2.250 -0.0555 0.00789 0.00159 -0.0402 0.8000 0.1841 -2.000 -0.0292 0.00778 0.00148 -0.0398 0.7713 0.2181 -1.750 -0.0029 0.00765 0.00138 -0.0394 0.7440 0.2618 -1.500 0.0237 0.00755 0.00130 -0.0390 0.7171 0.3044 -1.250 0.0503 0.00745 0.00123 -0.0387 0.6905 0.3479 -1.000 0.0769 0.00732 0.00118 -0.0384 0.6641 0.4048 -0.750 0.1034 0.00715 0.00115 -0.0381 0.6380 0.4747 -0.500 0.1297 0.00701 0.00113 -0.0378 0.6122 0.5455 0.000 0.1822 0.00683 0.00117 -0.0369 0.5606 0.6746 0.250 0.2085 0.00682 0.00120 -0.0364 0.5362 0.7211 0.750 0.2607 0.00687 0.00129 -0.0352 0.4887 0.7951 1.000 0.2863 0.00692 0.00134 -0.0346 0.4659 0.8263 1.250 0.3117 0.00697 0.00140 -0.0338 0.4435 0.8564 1.500 0.3364 0.00704 0.00145 -0.0328 0.4214 0.8869 1.750 0.3612 0.00710 0.00150 -0.0319 0.4000 0.9197 2.000 0.3907 0.00721 0.00155 -0.0320 0.3770 0.9543 2.250 0.4276 0.00735 0.00160 -0.0339 0.3526 0.9908 2.500 0.4562 0.00753 0.00169 -0.0341 0.3318 1.0000 2.750 0.4831 0.00773 0.00178 -0.0339 0.3109 1.0000 3.000 0.5101 0.00793 0.00190 -0.0337 0.2915 1.0000 3.250 0.5371 0.00813 0.00202 -0.0335 0.2723 1.0000 3.500 0.5642 0.00834 0.00216 -0.0333 0.2553 1.0000 3.750 0.5911 0.00856 0.00231 -0.0331 0.2370 1.0000 4.000 0.6180 0.00879 0.00248 -0.0329 0.2206 1.0000 4.250 0.6449 0.00904 0.00265 -0.0327 0.2043 1.0000 4.500 0.6717 0.00928 0.00285 -0.0325 0.1888 1.0000 4.750 0.6984 0.00954 0.00305 -0.0323 0.1739 1.0000 5.000 0.7251 0.00980 0.00327 -0.0321 0.1599 1.0000 5.250 0.7517 0.01008 0.00350 -0.0319 0.1463 1.0000 5.500 0.7782 0.01037 0.00376 -0.0317 0.1339 1.0000 5.750 0.8047 0.01065 0.00402 -0.0315 0.1234 1.0000 6.000 0.8311 0.01095 0.00429 -0.0312 0.1127 1.0000 6.250 0.8572 0.01128 0.00459 -0.0310 0.1014 1.0000 6.500 0.8830 0.01166 0.00493 -0.0307 0.0882 1.0000 6.750 0.9087 0.01205 0.00527 -0.0304 0.0763 1.0000 7.000 0.9343 0.01243 0.00563 -0.0301 0.0672 1.0000 7.250 0.9597 0.01284 0.00601 -0.0298 0.0591 1.0000 7.500 0.9853 0.01321 0.00642 -0.0295 0.0526 1.0000 7.750 1.0103 0.01366 0.00685 -0.0291 0.0460 1.0000 8.000 1.0352 0.01412 0.00731 -0.0287 0.0396 1.0000 8.250 1.0599 0.01460 0.00780 -0.0283 0.0337 1.0000 8.500 1.0840 0.01515 0.00835 -0.0279 0.0280 1.0000 8.750 1.1079 0.01571 0.00894 -0.0274 0.0236 1.0000 9.000 1.1316 0.01628 0.00955 -0.0269 0.0205 1.0000 9.250 1.1548 0.01690 0.01022 -0.0263 0.0182 1.0000 9.500 1.1774 0.01760 0.01097 -0.0257 0.0165 1.0000 9.750 1.2002 0.01822 0.01168 -0.0251 0.0155 1.0000 10.000 1.2224 0.01889 0.01244 -0.0244 0.0144 1.0000 10.250 1.2438 0.01965 0.01326 -0.0237 0.0135 1.0000 10.500 1.2634 0.02059 0.01429 -0.0228 0.0127 1.0000 10.750 1.2831 0.02146 0.01526 -0.0219 0.0122 1.0000 11.000 1.3029 0.02227 0.01618 -0.0211 0.0117 1.0000 11.250 1.3215 0.02314 0.01717 -0.0201 0.0113 1.0000 11.500 1.3393 0.02406 0.01820 -0.0191 0.0108 1.0000 11.750 1.3561 0.02500 0.01924 -0.0180 0.0103 1.0000 12.000 1.3706 0.02609 0.02043 -0.0167 0.0099 1.0000 12.250 1.3820 0.02736 0.02180 -0.0152 0.0095 1.0000 12.500 1.3866 0.02896 0.02352 -0.0129 0.0092 1.0000 12.750 1.3899 0.03030 0.02498 -0.0104 0.0090 1.0000 13.000 1.3936 0.03165 0.02646 -0.0083 0.0088 1.0000 13.250 1.3952 0.03327 0.02822 -0.0065 0.0086 1.0000 13.500 1.3955 0.03521 0.03029 -0.0054 0.0083 1.0000 13.750 1.3934 0.03766 0.03288 -0.0048 0.0081 1.0000 14.000 1.3885 0.04075 0.03614 -0.0051 0.0080 1.0000 14.250 1.3825 0.04444 0.03998 -0.0063 0.0079 1.0000 14.500 1.3741 0.04888 0.04457 -0.0083 0.0077 1.0000 14.750 1.3639 0.05403 0.04988 -0.0110 0.0077 1.0000 15.000 1.3506 0.06003 0.05604 -0.0145 0.0076 1.0000 15.250 1.3357 0.06658 0.06274 -0.0183 0.0075 1.0000 15.500 1.3177 0.07386 0.07017 -0.0225 0.0075 1.0000 15.750 1.2957 0.08202 0.07848 -0.0272 0.0076 1.0000 16.000 1.2734 0.09044 0.08705 -0.0320 0.0076 1.0000