XFOIL Version 6.96 Calculated polar for: YS-900 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.750 -0.4855 0.04559 0.04314 -0.0725 0.9618 0.0021 -7.500 -0.4950 0.04175 0.03909 -0.0677 0.9598 0.0022 -7.250 -0.4958 0.03878 0.03595 -0.0638 0.9583 0.0024 -7.000 -0.4893 0.03617 0.03315 -0.0604 0.9572 0.0024 -6.750 -0.4844 0.03368 0.03046 -0.0568 0.9561 0.0025 -6.500 -0.4781 0.03157 0.02818 -0.0531 0.9550 0.0026 -6.250 -0.4711 0.02977 0.02620 -0.0495 0.9537 0.0028 -6.000 -0.4619 0.02784 0.02405 -0.0459 0.9525 0.0029 -5.750 -0.4516 0.02611 0.02214 -0.0425 0.9512 0.0031 -5.500 -0.4390 0.02438 0.02021 -0.0394 0.9500 0.0034 -2.250 -0.1302 0.00939 0.00339 -0.0264 0.9437 0.0046 -2.000 -0.1049 0.00920 0.00310 -0.0260 0.9432 0.0037 -1.750 -0.1036 0.00934 0.00320 -0.0200 0.9393 0.0034 -1.500 -0.0856 0.00930 0.00313 -0.0180 0.9372 0.0032 -1.250 -0.0623 0.00921 0.00298 -0.0171 0.9359 0.0033 -1.000 -0.0368 0.00912 0.00294 -0.0169 0.9349 0.0069 -0.750 -0.0467 0.00695 0.00258 -0.0095 0.9322 0.5682 -0.500 -0.0776 0.00617 0.00246 0.0040 0.9244 0.7420 -0.250 -0.0396 0.00692 0.00387 0.0029 0.9246 0.9223 0.000 0.0000 0.00697 0.00392 0.0000 0.9237 0.9237 0.250 0.0396 0.00691 0.00386 -0.0029 0.9223 0.9246 0.500 0.0802 0.00613 0.00245 -0.0046 0.7504 0.9241 0.750 0.0484 0.00690 0.00257 0.0091 0.5804 0.9321 1.000 0.0400 0.00888 0.00292 0.0162 0.0934 0.9347 1.250 0.0624 0.00921 0.00298 0.0171 0.0033 0.9359 1.500 0.0856 0.00929 0.00312 0.0180 0.0031 0.9372 1.750 0.1035 0.00934 0.00320 0.0201 0.0034 0.9393 2.000 0.1049 0.00920 0.00310 0.0259 0.0036 0.9432 2.250 0.1302 0.00939 0.00338 0.0264 0.0045 0.9437 4.500 0.3500 0.00715 0.00250 0.0313 0.0057 0.9464 4.750 0.3726 0.00770 0.00318 0.0325 0.0049 0.9470 5.000 0.3933 0.00865 0.00431 0.0341 0.0041 0.9477 5.250 0.4101 0.00996 0.00583 0.0364 0.0038 0.9486 5.500 0.4241 0.01141 0.00749 0.0392 0.0034 0.9495 5.750 0.4361 0.01305 0.00933 0.0423 0.0033 0.9506 6.000 0.4459 0.01481 0.01129 0.0456 0.0030 0.9521 6.250 0.4539 0.01678 0.01345 0.0491 0.0029 0.9534 6.500 0.4611 0.01881 0.01569 0.0525 0.0028 0.9546 6.750 0.4661 0.02101 0.01805 0.0560 0.0026 0.9557 7.000 0.4708 0.02350 0.02072 0.0594 0.0026 0.9567 7.250 0.4735 0.02619 0.02358 0.0628 0.0025 0.9577 7.500 0.4728 0.02910 0.02664 0.0664 0.0024 0.9590 7.750 0.4712 0.03210 0.02979 0.0700 0.0023 0.9606