XFOIL Version 6.96 Calculated polar for: N-14 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.000 -0.6653 0.09634 0.08838 -0.0327 1.0000 0.0743 -11.750 -0.7008 0.08527 0.07732 -0.0398 1.0000 0.0736 -11.500 -0.7410 0.07631 0.06829 -0.0449 1.0000 0.0727 -11.250 -0.7769 0.06996 0.06182 -0.0465 1.0000 0.0721 -11.000 -0.8069 0.06531 0.05702 -0.0455 1.0000 0.0719 -10.750 -0.8313 0.06170 0.05323 -0.0428 1.0000 0.0720 -10.500 -0.8507 0.05864 0.04998 -0.0390 1.0000 0.0723 -10.250 -0.8636 0.05555 0.04663 -0.0357 1.0000 0.0730 -10.000 -0.8716 0.05262 0.04338 -0.0323 1.0000 0.0739 -9.750 -0.8773 0.04985 0.04025 -0.0289 1.0000 0.0756 -9.500 -0.8801 0.04714 0.03710 -0.0255 1.0000 0.0775 -9.250 -0.8680 0.04560 0.03555 -0.0237 1.0000 0.0797 -9.000 -0.8584 0.04376 0.03352 -0.0214 1.0000 0.0820 -8.750 -0.8477 0.04168 0.03116 -0.0192 1.0000 0.0842 -8.500 -0.8350 0.03963 0.02876 -0.0171 1.0000 0.0867 -8.250 -0.8204 0.03792 0.02683 -0.0152 1.0000 0.0902 -8.000 -0.8048 0.03662 0.02545 -0.0135 1.0000 0.0944 -7.750 -0.7879 0.03514 0.02369 -0.0118 1.0000 0.0995 -7.500 -0.7677 0.03359 0.02203 -0.0106 1.0000 0.1042 -7.250 -0.7478 0.03221 0.02062 -0.0093 1.0000 0.1103 -7.000 -0.7277 0.03088 0.01916 -0.0080 1.0000 0.1186 -6.750 -0.7099 0.02970 0.01793 -0.0064 1.0000 0.1301 -6.500 -0.6935 0.02856 0.01687 -0.0046 1.0000 0.1433 -6.250 -0.6773 0.02755 0.01591 -0.0027 1.0000 0.1584 -6.000 -0.6620 0.02670 0.01512 -0.0007 1.0000 0.1760 -5.750 -0.6475 0.02594 0.01443 0.0014 1.0000 0.1957 -5.500 -0.6327 0.02525 0.01380 0.0035 1.0000 0.2203 -5.250 -0.6197 0.02457 0.01327 0.0058 1.0000 0.2508 -5.000 -0.6072 0.02386 0.01276 0.0083 1.0000 0.2862 -4.750 -0.5942 0.02310 0.01221 0.0107 1.0000 0.3241 -4.500 -0.5805 0.02236 0.01165 0.0132 1.0000 0.3649 -4.250 -0.5668 0.02170 0.01120 0.0157 1.0000 0.4102 -4.000 -0.5530 0.02110 0.01089 0.0183 1.0000 0.4637 -3.750 -0.5387 0.02064 0.01076 0.0212 1.0000 0.5281 -3.500 -0.5207 0.02039 0.01079 0.0238 1.0000 0.5998 -3.250 -0.4973 0.02040 0.01098 0.0255 1.0000 0.6655 -3.000 -0.4722 0.02056 0.01119 0.0269 1.0000 0.7211 -2.750 -0.4469 0.02081 0.01141 0.0283 1.0000 0.7704 -2.500 -0.4157 0.02119 0.01173 0.0286 1.0000 0.8121 -2.250 -0.3814 0.02161 0.01204 0.0282 1.0000 0.8474 -2.000 -0.3380 0.02215 0.01245 0.0261 1.0000 0.8778 -1.750 -0.2833 0.02275 0.01287 0.0217 1.0000 0.9042 -1.500 -0.2304 0.02314 0.01313 0.0172 1.0000 0.9257 -1.250 -0.1850 0.02336 0.01322 0.0135 1.0000 0.9449 -1.000 -0.1381 0.02347 0.01324 0.0093 1.0000 0.9611 -0.750 -0.0841 0.02352 0.01321 0.0035 1.0000 0.9777 -0.500 -0.0261 0.02348 0.01312 -0.0032 1.0000 0.9947 -0.250 -0.0050 0.02343 0.01304 -0.0035 1.0000 1.0000 0.000 -0.0041 0.02343 0.01303 -0.0001 1.0000 1.0000 0.250 0.0039 0.02344 0.01304 0.0021 0.9983 1.0000 0.500 0.0690 0.02344 0.01306 -0.0060 0.9796 1.0000 0.750 0.1240 0.02333 0.01300 -0.0119 0.9620 1.0000 1.000 0.1674 0.02323 0.01296 -0.0156 0.9474 1.0000 1.250 0.2086 0.02310 0.01291 -0.0187 0.9325 1.0000 1.500 0.2500 0.02293 0.01285 -0.0217 0.9171 1.0000 1.750 0.2937 0.02269 0.01273 -0.0249 0.9011 1.0000 2.000 0.3391 0.02240 0.01259 -0.0281 0.8842 1.0000 2.250 0.3741 0.02214 0.01247 -0.0293 0.8625 1.0000 2.500 0.4135 0.02179 0.01226 -0.0309 0.8395 1.0000 2.750 0.4487 0.02138 0.01198 -0.0314 0.8078 1.0000 3.000 0.4768 0.02102 0.01168 -0.0303 0.7652 1.0000 3.250 0.5007 0.02074 0.01142 -0.0285 0.7146 1.0000 3.500 0.5244 0.02056 0.01117 -0.0266 0.6588 1.0000 3.750 0.5475 0.02055 0.01098 -0.0247 0.6007 1.0000 4.000 0.5660 0.02077 0.01099 -0.0223 0.5442 1.0000 4.250 0.5826 0.02117 0.01115 -0.0198 0.4908 1.0000 4.500 0.5971 0.02171 0.01141 -0.0172 0.4414 1.0000 4.750 0.6097 0.02234 0.01177 -0.0144 0.3939 1.0000 5.000 0.6215 0.02302 0.01221 -0.0116 0.3495 1.0000 5.250 0.6337 0.02368 0.01273 -0.0089 0.3093 1.0000 5.500 0.6464 0.02433 0.01329 -0.0064 0.2729 1.0000 5.750 0.6594 0.02501 0.01388 -0.0039 0.2394 1.0000 6.000 0.6716 0.02576 0.01449 -0.0014 0.2075 1.0000 6.250 0.6847 0.02664 0.01525 0.0010 0.1809 1.0000 6.500 0.6982 0.02768 0.01610 0.0032 0.1617 1.0000 6.750 0.7139 0.02875 0.01712 0.0052 0.1457 1.0000 7.000 0.7299 0.02982 0.01817 0.0070 0.1330 1.0000 7.250 0.7487 0.03095 0.01940 0.0086 0.1231 1.0000 7.500 0.7671 0.03221 0.02059 0.0101 0.1167 1.0000 7.750 0.7867 0.03345 0.02209 0.0115 0.1098 1.0000 8.000 0.8035 0.03465 0.02331 0.0131 0.1038 1.0000 8.250 0.8220 0.03615 0.02495 0.0146 0.0993 1.0000 8.500 0.8395 0.03781 0.02688 0.0161 0.0953 1.0000 8.750 0.8545 0.03930 0.02852 0.0179 0.0913 1.0000 9.000 0.8690 0.04087 0.03010 0.0196 0.0877 1.0000 9.250 0.8780 0.04292 0.03258 0.0221 0.0844 1.0000 9.500 0.8864 0.04503 0.03499 0.0245 0.0817 1.0000 9.750 0.8948 0.04683 0.03693 0.0268 0.0788 1.0000 10.000 0.9053 0.04854 0.03860 0.0286 0.0761 1.0000 10.250 0.8987 0.05135 0.04189 0.0323 0.0742 1.0000 10.500 0.8908 0.05428 0.04517 0.0357 0.0729 1.0000 10.750 0.8784 0.05721 0.04839 0.0392 0.0718 1.0000 11.000 0.8608 0.06009 0.05148 0.0429 0.0709 1.0000 11.250 0.8402 0.06337 0.05495 0.0458 0.0702 1.0000 11.500 0.8147 0.06749 0.05926 0.0472 0.0700 1.0000 11.750 0.7809 0.07323 0.06518 0.0464 0.0706 1.0000 12.000 0.7397 0.08149 0.07356 0.0424 0.0719 1.0000 12.250 0.6995 0.09223 0.08434 0.0356 0.0732 1.0000