XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY LS(1)-0421MOD AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0472 0.09080 0.08586 -0.0530 1.0000 0.0297 -19.500 -1.0474 0.08726 0.08226 -0.0546 1.0000 0.0299 -19.250 -1.0477 0.08373 0.07867 -0.0562 1.0000 0.0301 -19.000 -1.0477 0.08025 0.07512 -0.0577 1.0000 0.0303 -18.750 -1.0467 0.07695 0.07175 -0.0591 1.0000 0.0305 -18.500 -1.0456 0.07372 0.06844 -0.0603 1.0000 0.0307 -18.250 -1.0439 0.07062 0.06526 -0.0615 1.0000 0.0309 -18.000 -1.0413 0.06768 0.06225 -0.0625 1.0000 0.0312 -17.750 -1.0384 0.06481 0.05929 -0.0635 1.0000 0.0314 -17.500 -1.0347 0.06208 0.05648 -0.0643 1.0000 0.0317 -17.250 -1.0302 0.05951 0.05383 -0.0651 1.0000 0.0321 -17.000 -1.0253 0.05700 0.05123 -0.0658 1.0000 0.0323 -16.750 -1.0194 0.05465 0.04878 -0.0664 1.0000 0.0326 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-0.0644 0.1373 0.8063 12.250 1.5425 0.03896 0.03243 -0.0638 0.1346 0.8092 12.500 1.5466 0.04113 0.03461 -0.0630 0.1319 0.8118 12.750 1.5515 0.04323 0.03676 -0.0624 0.1296 0.8142 13.000 1.5606 0.04493 0.03855 -0.0619 0.1275 0.8167 13.250 1.5676 0.04686 0.04055 -0.0613 0.1253 0.8191 13.500 1.5718 0.04914 0.04288 -0.0609 0.1232 0.8217 13.750 1.5734 0.05172 0.04548 -0.0604 0.1211 0.8244 14.000 1.5751 0.05431 0.04811 -0.0600 0.1191 0.8273 14.250 1.5827 0.05644 0.05033 -0.0599 0.1174 0.8304 14.500 1.5890 0.05869 0.05265 -0.0598 0.1156 0.8331 14.750 1.5922 0.06123 0.05526 -0.0596 0.1138 0.8357 15.000 1.5937 0.06395 0.05802 -0.0595 0.1120 0.8382 15.250 1.5919 0.06704 0.06113 -0.0593 0.1101 0.8409 15.500 1.5956 0.06961 0.06377 -0.0593 0.1086 0.8438 15.750 1.6000 0.07223 0.06649 -0.0595 0.1071 0.8469 16.000 1.6043 0.07488 0.06920 -0.0598 0.1056 0.8498 16.250 1.6056 0.07775 0.07215 -0.0599 0.1042 0.8525 16.500 1.6068 0.08061 0.07506 -0.0601 0.1028 0.8552 16.750 1.6059 0.08372 0.07819 -0.0602 0.1014 0.8581 17.000 1.6077 0.08644 0.08093 -0.0603 0.0999 0.8612