XFOIL Version 6.94 Calculated polar for: Eif385mod 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.005 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0732 0.06180 0.03499 -0.0233 0.9993 1.0007 -2.750 -0.0506 0.06173 0.03405 -0.0249 0.9993 1.0007 -2.500 -0.0270 0.06191 0.03342 -0.0260 0.9993 1.0007 -2.250 -0.0040 0.06224 0.03300 -0.0266 0.9993 1.0007 -2.000 0.0183 0.06268 0.03279 -0.0268 0.9993 1.0007 -1.750 0.0398 0.06318 0.03274 -0.0268 0.9993 1.0007 -1.500 0.0605 0.06375 0.03282 -0.0265 0.9993 1.0007 -1.250 0.0805 0.06438 0.03300 -0.0262 0.9993 1.0007 -1.000 0.0999 0.06508 0.03333 -0.0257 0.9993 1.0007 -0.750 0.1186 0.06583 0.03376 -0.0253 0.9993 1.0007 -0.500 0.1367 0.06666 0.03432 -0.0247 0.9993 1.0007 -0.250 0.1542 0.06756 0.03498 -0.0242 0.9993 1.0007 0.000 0.1711 0.06854 0.03577 -0.0237 0.9993 1.0007 0.250 0.1873 0.06961 0.03669 -0.0233 0.9993 1.0007 0.500 0.2028 0.07078 0.03774 -0.0228 0.9993 1.0007 0.750 0.2175 0.07206 0.03893 -0.0225 0.9993 1.0007 1.000 0.2314 0.07346 0.04027 -0.0221 0.9993 1.0007 1.250 0.2445 0.07499 0.04177 -0.0219 0.9993 1.0007 1.500 0.2566 0.07666 0.04342 -0.0218 0.9993 1.0007 1.750 0.2678 0.07850 0.04525 -0.0217 0.9993 1.0007 2.000 0.2780 0.08048 0.04723 -0.0218 0.9993 1.0007 2.250 0.2874 0.08262 0.04939 -0.0220 0.9993 1.0007 2.500 0.2961 0.08489 0.05166 -0.0223 0.9993 1.0007 2.750 0.3043 0.08728 0.05404 -0.0227 0.9993 1.0007 3.000 0.3122 0.08976 0.05651 -0.0232 0.9993 1.0007 3.250 0.3201 0.09231 0.05904 -0.0238 0.9993 1.0007 3.500 0.3282 0.09490 0.06162 -0.0245 0.9993 1.0007 3.750 0.3365 0.09751 0.06421 -0.0253 0.9993 1.0007 4.000 0.3450 0.10014 0.06683 -0.0261 0.9993 1.0007 4.250 0.3539 0.10276 0.06943 -0.0269 0.9993 1.0007 4.500 0.3630 0.10539 0.07204 -0.0277 0.9993 1.0007 4.750 0.3724 0.10801 0.07464 -0.0286 0.9993 1.0007 5.000 0.3821 0.11062 0.07725 -0.0295 0.9993 1.0007