XFOIL Version 6.96 Calculated polar for: EH 2.5/10 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5013 0.08796 0.08469 -0.0062 1.0000 0.0167 -8.750 -0.5053 0.08323 0.08002 -0.0091 1.0000 0.0166 -8.500 -0.5133 0.07810 0.07495 -0.0129 1.0000 0.0164 -8.250 -0.5247 0.07345 0.07031 -0.0158 1.0000 0.0162 -8.000 -0.5344 0.06862 0.06546 -0.0175 1.0000 0.0161 -7.750 -0.5394 0.06353 0.06030 -0.0189 1.0000 0.0160 -7.500 -0.5414 0.05837 0.05502 -0.0197 1.0000 0.0160 -7.250 -0.5409 0.05300 0.04948 -0.0198 1.0000 0.0162 -7.000 -0.5377 0.04759 0.04383 -0.0192 1.0000 0.0164 -6.750 -0.5327 0.04198 0.03789 -0.0180 1.0000 0.0167 -6.500 -0.5250 0.03670 0.03222 -0.0162 1.0000 0.0175 -6.250 -0.5117 0.03307 0.02817 -0.0145 1.0000 0.0187 -5.750 -0.4538 0.02556 0.01948 -0.0169 0.9072 0.0190 -5.500 -0.4268 0.02326 0.01665 -0.0168 0.8681 0.0192 -5.250 -0.4027 0.02159 0.01454 -0.0158 0.8348 0.0194 -5.000 -0.3801 0.01942 0.01193 -0.0147 0.8071 0.0200 -4.750 -0.3567 0.01801 0.01023 -0.0136 0.7820 0.0209 -4.500 -0.3327 0.01711 0.00913 -0.0127 0.7593 0.0219 -4.250 -0.3086 0.01642 0.00825 -0.0118 0.7391 0.0230 -4.000 -0.2841 0.01581 0.00747 -0.0109 0.7203 0.0242 -3.750 -0.2592 0.01539 0.00690 -0.0102 0.7029 0.0265 -3.500 -0.2344 0.01496 0.00631 -0.0095 0.6866 0.0285 -3.250 -0.2098 0.01447 0.00566 -0.0086 0.6716 0.0294 -3.000 -0.1857 0.01391 0.00499 -0.0078 0.6576 0.0318 -2.750 -0.1608 0.01353 0.00452 -0.0070 0.6440 0.0368 -2.500 -0.1359 0.01317 0.00412 -0.0063 0.6312 0.0500 -2.250 -0.1105 0.01292 0.00383 -0.0058 0.6188 0.0697 -2.000 -0.0852 0.01269 0.00360 -0.0052 0.6071 0.0917 -1.750 -0.0600 0.01247 0.00341 -0.0047 0.5959 0.1208 -1.500 -0.0353 0.01216 0.00322 -0.0042 0.5848 0.1667 -1.250 -0.0140 0.01155 0.00298 -0.0032 0.5659 0.2857 -1.000 -0.0093 0.00974 0.00297 0.0018 0.5431 0.7689 -0.750 0.0184 0.00978 0.00301 0.0027 0.5181 0.8529 -0.250 0.0867 0.01005 0.00309 0.0013 0.4979 0.9171 0.250 0.1666 0.01047 0.00315 -0.0029 0.4587 0.9532 0.500 0.2163 0.01072 0.00322 -0.0072 0.4417 0.9666 0.750 0.2565 0.01078 0.00317 -0.0098 0.4317 0.9713 1.000 0.2884 0.01082 0.00311 -0.0108 0.4228 0.9751 1.250 0.3180 0.01088 0.00309 -0.0113 0.4143 0.9795 1.500 0.3516 0.01091 0.00305 -0.0126 0.4059 0.9823 1.750 0.3846 0.01095 0.00304 -0.0139 0.3982 0.9855 2.000 0.4168 0.01100 0.00304 -0.0150 0.3904 0.9892 2.500 0.4823 0.01111 0.00308 -0.0175 0.3761 0.9962 2.750 0.5155 0.01118 0.00311 -0.0189 0.3694 0.9995 3.000 0.5400 0.01124 0.00322 -0.0184 0.3634 1.0000 3.250 0.5624 0.01134 0.00329 -0.0175 0.3566 1.0000 3.500 0.5847 0.01147 0.00337 -0.0166 0.3430 1.0000 3.750 0.6064 0.01165 0.00345 -0.0156 0.3204 1.0000 4.000 0.6282 0.01185 0.00357 -0.0147 0.3014 1.0000 4.250 0.6506 0.01200 0.00372 -0.0138 0.2931 1.0000 4.500 0.6730 0.01217 0.00393 -0.0129 0.2851 1.0000 4.750 0.6953 0.01238 0.00412 -0.0120 0.2722 1.0000 5.000 0.7170 0.01265 0.00433 -0.0111 0.2528 1.0000 5.250 0.7373 0.01312 0.00460 -0.0100 0.2163 1.0000 5.500 0.7578 0.01358 0.00493 -0.0090 0.1864 1.0000 5.750 0.7794 0.01393 0.00525 -0.0081 0.1700 1.0000 6.000 0.8003 0.01439 0.00563 -0.0072 0.1480 1.0000 6.250 0.8072 0.01653 0.00700 -0.0049 0.0206 1.0000 6.500 0.8280 0.01697 0.00752 -0.0039 0.0172 1.0000 6.750 0.8493 0.01736 0.00797 -0.0030 0.0165 1.0000 7.000 0.8704 0.01776 0.00844 -0.0020 0.0162 1.0000 7.250 0.8914 0.01818 0.00894 -0.0011 0.0160 1.0000 7.500 0.9120 0.01864 0.00949 -0.0001 0.0157 1.0000 7.750 0.9323 0.01912 0.01007 0.0009 0.0155 1.0000 8.000 0.9519 0.01968 0.01072 0.0019 0.0148 1.0000 8.250 0.9704 0.02032 0.01151 0.0030 0.0139 1.0000 8.500 0.9881 0.02103 0.01232 0.0042 0.0133 1.0000 8.750 1.0054 0.02175 0.01315 0.0054 0.0130 1.0000 9.000 1.0221 0.02247 0.01400 0.0066 0.0126 1.0000 9.250 1.0375 0.02328 0.01493 0.0079 0.0119 1.0000 9.500 1.0505 0.02421 0.01597 0.0094 0.0111 1.0000 9.750 1.0587 0.02543 0.01728 0.0113 0.0103 1.0000 10.000 1.0701 0.02632 0.01830 0.0129 0.0088 1.0000 10.250 1.0734 0.02749 0.01959 0.0154 0.0084 1.0000 10.500 1.0736 0.02894 0.02114 0.0176 0.0082 1.0000 10.750 1.0724 0.03080 0.02313 0.0191 0.0079 1.0000 11.000 1.0707 0.03306 0.02556 0.0197 0.0076 1.0000 11.250 1.0683 0.03569 0.02832 0.0197 0.0075 1.0000 11.500 1.0654 0.03862 0.03136 0.0193 0.0073 1.0000 11.750 1.0590 0.04210 0.03492 0.0186 0.0070 1.0000 12.000 1.0573 0.04514 0.03808 0.0179 0.0071 1.0000 12.250 1.0501 0.04888 0.04189 0.0170 0.0069 1.0000 12.500 1.0437 0.05257 0.04566 0.0161 0.0068 1.0000 12.750 1.0378 0.05622 0.04941 0.0154 0.0066 1.0000 13.000 1.0361 0.05939 0.05267 0.0147 0.0066 1.0000 13.250 1.0334 0.06269 0.05604 0.0140 0.0064 1.0000 13.500 1.0324 0.06579 0.05922 0.0135 0.0064 1.0000 13.750 1.0318 0.06881 0.06230 0.0130 0.0062 1.0000 14.000 1.0328 0.07172 0.06526 0.0126 0.0061 1.0000 14.250 1.0352 0.07446 0.06804 0.0124 0.0059 1.0000 14.500 1.0416 0.07637 0.06993 0.0132 0.0057 1.0000 14.750 1.0456 0.07901 0.07263 0.0132 0.0056 1.0000 15.000 1.0414 0.08334 0.07717 0.0112 0.0056 1.0000 15.250 1.0331 0.08860 0.08270 0.0086 0.0054 1.0000 15.500 1.0272 0.09347 0.08777 0.0064 0.0053 1.0000 15.750 1.0220 0.09834 0.09281 0.0042 0.0053 1.0000 16.000 1.0178 0.10303 0.09765 0.0021 0.0053 1.0000 16.250 1.0124 0.10812 0.10288 -0.0004 0.0053 1.0000 16.500 1.0040 0.11397 0.10892 -0.0034 0.0053 1.0000 16.750 0.9945 0.12032 0.11544 -0.0069 0.0053 1.0000 17.000 0.9860 0.12652 0.12180 -0.0103 0.0053 1.0000 17.250 0.9813 0.13189 0.12727 -0.0132 0.0054 1.0000 17.500 0.9687 0.13960 0.13516 -0.0177 0.0053 1.0000 17.750 0.9599 0.14646 0.14214 -0.0217 0.0054 1.0000 18.000 0.9529 0.15299 0.14877 -0.0254 0.0054 1.0000 18.250 0.9420 0.16099 0.15690 -0.0302 0.0055 1.0000 18.500 0.9400 0.16633 0.16229 -0.0332 0.0056 1.0000 18.750 0.9352 0.17280 0.16882 -0.0369 0.0056 1.0000