XFOIL Version 6.96 Calculated polar for: S8038 (13%) 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 ------ -------- --------- --------- -------- -------- -------- -18.500 -0.8777 0.13402 0.13166 -0.0094 1.0000 0.0061 -18.250 -0.9119 0.12256 0.12006 -0.0153 1.0000 0.0060 -18.000 -0.9387 0.11304 0.11043 -0.0202 1.0000 0.0061 -17.750 -0.9678 0.10336 0.10061 -0.0253 1.0000 0.0061 -17.500 -0.9929 0.09472 0.09185 -0.0298 1.0000 0.0061 -17.250 -1.0231 0.08537 0.08235 -0.0348 1.0000 0.0060 -17.000 -1.0418 0.07826 0.07512 -0.0386 1.0000 0.0061 -16.750 -1.0613 0.07119 0.06791 -0.0424 1.0000 0.0061 -16.500 -1.0784 0.06483 0.06141 -0.0458 1.0000 0.0061 -16.250 -1.0918 0.05933 0.05578 -0.0486 1.0000 0.0060 -16.000 -1.1014 0.05468 0.05102 -0.0508 1.0000 0.0061 -15.750 -1.1076 0.05072 0.04695 -0.0524 1.0000 0.0062 -15.500 -1.1184 0.04642 0.04252 -0.0539 1.0000 0.0061 -15.250 -1.1212 0.04329 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0.00108 -0.0221 0.5751 0.5822 -0.250 0.0907 0.00628 0.00108 -0.0218 0.5634 0.5938 0.000 0.1171 0.00631 0.00109 -0.0214 0.5482 0.6056 0.250 0.1434 0.00636 0.00110 -0.0210 0.5294 0.6166 0.500 0.1696 0.00642 0.00112 -0.0206 0.5102 0.6276 0.750 0.1958 0.00650 0.00115 -0.0201 0.4910 0.6368 1.250 0.2484 0.00666 0.00122 -0.0194 0.4543 0.6535 1.500 0.2745 0.00674 0.00126 -0.0189 0.4355 0.6625 1.750 0.3007 0.00685 0.00131 -0.0186 0.4160 0.6713 2.000 0.3263 0.00697 0.00138 -0.0181 0.3938 0.6790 2.250 0.3519 0.00713 0.00146 -0.0176 0.3689 0.6872 2.500 0.3764 0.00732 0.00155 -0.0169 0.3366 0.6956 2.750 0.4013 0.00752 0.00166 -0.0163 0.3090 0.7044 3.000 0.4261 0.00769 0.00177 -0.0157 0.2845 0.7137 3.250 0.4506 0.00791 0.00189 -0.0151 0.2573 0.7221 3.500 0.4755 0.00809 0.00202 -0.0145 0.2358 0.7309 3.750 0.5003 0.00827 0.00215 -0.0139 0.2163 0.7393 4.000 0.5250 0.00847 0.00229 -0.0133 0.1981 0.7487 4.250 0.5495 0.00865 0.00244 -0.0126 0.1812 0.7579 4.500 0.5740 0.00885 0.00259 -0.0120 0.1645 0.7681 4.750 0.5984 0.00903 0.00275 -0.0113 0.1515 0.7790 5.000 0.6228 0.00919 0.00291 -0.0106 0.1409 0.7904 5.250 0.6473 0.00933 0.00307 -0.0100 0.1321 0.8030 5.500 0.6713 0.00950 0.00324 -0.0092 0.1233 0.8171 5.750 0.6952 0.00964 0.00342 -0.0084 0.1157 0.8329 6.000 0.7184 0.00980 0.00360 -0.0075 0.1072 0.8511 6.250 0.7415 0.00995 0.00380 -0.0066 0.1004 0.8727 6.500 0.7656 0.01007 0.00400 -0.0058 0.0950 0.9002 6.750 0.7980 0.01027 0.00426 -0.0069 0.0891 0.9325 7.000 0.8434 0.01060 0.00459 -0.0110 0.0819 0.9531 7.250 0.8882 0.01098 0.00493 -0.0151 0.0738 0.9653 7.500 0.9249 0.01126 0.00521 -0.0172 0.0702 0.9793 7.750 0.9534 0.01153 0.00548 -0.0176 0.0673 0.9906 8.250 1.0148 0.01216 0.00609 -0.0194 0.0605 0.9999 8.500 1.0361 0.01239 0.00633 -0.0182 0.0589 1.0000 8.750 1.0561 0.01264 0.00660 -0.0168 0.0569 1.0000 9.000 1.0754 0.01292 0.00689 -0.0152 0.0546 1.0000 9.250 1.0944 0.01323 0.00719 -0.0136 0.0521 1.0000 9.500 1.1137 0.01352 0.00750 -0.0121 0.0504 1.0000 9.750 1.1333 0.01379 0.00779 -0.0107 0.0491 1.0000 10.000 1.1521 0.01408 0.00811 -0.0091 0.0471 1.0000 10.250 1.1698 0.01444 0.00846 -0.0074 0.0446 1.0000 10.500 1.1869 0.01481 0.00883 -0.0056 0.0423 1.0000 10.750 1.2048 0.01513 0.00918 -0.0039 0.0408 1.0000 11.000 1.2208 0.01549 0.00955 -0.0019 0.0384 1.0000 11.250 1.2339 0.01589 0.00996 0.0006 0.0363 1.0000 11.500 1.2466 0.01631 0.01039 0.0031 0.0344 1.0000 11.750 1.2610 0.01670 0.01081 0.0052 0.0332 1.0000 12.000 1.2745 0.01716 0.01129 0.0074 0.0310 1.0000 12.250 1.2879 0.01766 0.01182 0.0095 0.0298 1.0000 12.500 1.3003 0.01824 0.01241 0.0116 0.0279 1.0000 12.750 1.3140 0.01877 0.01298 0.0135 0.0270 1.0000 13.000 1.3268 0.01937 0.01363 0.0154 0.0259 1.0000 13.250 1.3386 0.02006 0.01434 0.0172 0.0246 1.0000 13.500 1.3499 0.02081 0.01513 0.0190 0.0238 1.0000 13.750 1.3603 0.02165 0.01601 0.0207 0.0226 1.0000 14.000 1.3719 0.02247 0.01689 0.0222 0.0220 1.0000 14.250 1.3825 0.02339 0.01785 0.0235 0.0211 1.0000 14.500 1.3924 0.02441 0.01893 0.0248 0.0204 1.0000 14.750 1.4006 0.02561 0.02017 0.0261 0.0194 1.0000 15.000 1.4089 0.02688 0.02150 0.0271 0.0188 1.0000 15.250 1.4158 0.02831 0.02299 0.0280 0.0182 1.0000 15.500 1.4244 0.02967 0.02443 0.0287 0.0178 1.0000 15.750 1.4317 0.03121 0.02604 0.0293 0.0172 1.0000 16.000 1.4380 0.03289 0.02778 0.0298 0.0167 1.0000 16.250 1.4428 0.03476 0.02972 0.0301 0.0161 1.0000 16.500 1.4461 0.03685 0.03188 0.0303 0.0155 1.0000 16.750 1.4470 0.03924 0.03433 0.0304 0.0147 1.0000 17.000 1.4489 0.04161 0.03680 0.0303 0.0147 1.0000 17.250 1.4491 0.04423 0.03950 0.0300 0.0140 1.0000 17.500 1.4480 0.04706 0.04242 0.0296 0.0137 1.0000 17.750 1.4456 0.05014 0.04558 0.0289 0.0129 1.0000 18.000 1.4422 0.05346 0.04901 0.0280 0.0129 1.0000 18.250 1.4359 0.05721 0.05284 0.0269 0.0124 1.0000 18.500 1.4255 0.06163 0.05735 0.0254 0.0117 1.0000 18.750 1.4151 0.06621 0.06203 0.0238 0.0113 1.0000 19.000 1.4035 0.07106 0.06699 0.0218 0.0108 1.0000 19.250 1.3876 0.07666 0.07270 0.0195 0.0101 1.0000