XFOIL Version 6.96 Calculated polar for: NACA 66-021 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9528 0.08661 0.08127 -0.0735 0.8693 0.0149 -19.500 -0.9526 0.08341 0.07795 -0.0746 0.8641 0.0150 -19.250 -0.9524 0.08029 0.07470 -0.0756 0.8589 0.0151 -19.000 -0.9510 0.07737 0.07165 -0.0765 0.8538 0.0152 -18.500 -0.9465 0.07190 0.06595 -0.0778 0.8451 0.0154 -18.250 -0.9428 0.06938 0.06332 -0.0784 0.8407 0.0154 -18.000 -0.9400 0.06686 0.06072 -0.0788 0.8365 0.0155 -17.750 -0.9366 0.06447 0.05823 -0.0791 0.8324 0.0156 -17.500 -0.9327 0.06214 0.05581 -0.0793 0.8290 0.0157 -17.250 -0.9284 0.05988 0.05348 -0.0795 0.8254 0.0158 -17.000 -0.9234 0.05774 0.05127 -0.0796 0.8217 0.0160 -16.750 -0.9166 0.05586 0.04931 -0.0796 0.8180 0.0161 -16.500 -0.9103 0.05396 0.04733 -0.0795 0.8145 0.0164 -16.250 -0.9026 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0.7211 3.250 0.3618 0.01036 0.00499 -0.0046 0.6902 0.7218 3.500 0.3916 0.01024 0.00488 -0.0052 0.6869 0.7225 3.750 0.4183 0.01020 0.00488 -0.0052 0.6829 0.7232 4.000 0.4419 0.01012 0.00486 -0.0047 0.6760 0.7240 4.250 0.4708 0.00992 0.00463 -0.0050 0.6682 0.7247 4.500 0.4906 0.00990 0.00470 -0.0037 0.6580 0.7256 4.750 0.5119 0.00982 0.00464 -0.0026 0.6438 0.7264 5.000 0.5277 0.00975 0.00455 -0.0004 0.6128 0.7274 5.250 0.5129 0.00998 0.00445 0.0079 0.5495 0.7288 5.500 0.4883 0.01078 0.00501 0.0173 0.5039 0.7304 5.750 0.4714 0.01183 0.00585 0.0245 0.4589 0.7319 6.000 0.4601 0.01291 0.00673 0.0304 0.4173 0.7334 6.250 0.4550 0.01392 0.00757 0.0351 0.3790 0.7347 6.500 0.4515 0.01497 0.00842 0.0393 0.3376 0.7360 6.750 0.4503 0.01600 0.00924 0.0430 0.2957 0.7371 7.000 0.4535 0.01691 0.00998 0.0460 0.2579 0.7382 7.250 0.4576 0.01780 0.01069 0.0488 0.2179 0.7395 7.500 0.4624 0.01871 0.01141 0.0514 0.1756 0.7408 7.750 0.4703 0.01953 0.01207 0.0535 0.1411 0.7421 8.000 0.4786 0.02037 0.01274 0.0556 0.1050 0.7436 8.250 0.4877 0.02122 0.01343 0.0575 0.0765 0.7451 8.500 0.5016 0.02186 0.01401 0.0587 0.0615 0.7465 8.750 0.5157 0.02252 0.01460 0.0599 0.0488 0.7479 9.000 0.5314 0.02312 0.01516 0.0608 0.0419 0.7493 9.250 0.5475 0.02370 0.01573 0.0617 0.0376 0.7507 9.500 0.5632 0.02432 0.01634 0.0626 0.0345 0.7521 9.750 0.5802 0.02489 0.01692 0.0633 0.0326 0.7535 10.000 0.5965 0.02551 0.01753 0.0641 0.0306 0.7548 10.500 0.6291 0.02675 0.01883 0.0656 0.0280 0.7577 10.750 0.6444 0.02743 0.01954 0.0664 0.0267 0.7593 11.000 0.6590 0.02816 0.02030 0.0673 0.0255 0.7610 11.250 0.6747 0.02885 0.02104 0.0680 0.0249 0.7627 11.500 0.6901 0.02957 0.02180 0.0687 0.0241 0.7645 11.750 0.7047 0.03035 0.02262 0.0694 0.0232 0.7664 12.000 0.7187 0.03119 0.02348 0.0701 0.0224 0.7684 12.250 0.7319 0.03211 0.02442 0.0709 0.0217 0.7703 12.500 0.7458 0.03298 0.02534 0.0716 0.0214 0.7722 12.750 0.7592 0.03392 0.02631 0.0723 0.0210 0.7740 13.000 0.7729 0.03482 0.02728 0.0729 0.0204 0.7761 13.250 0.7859 0.03579 0.02830 0.0736 0.0197 0.7782 13.500 0.7984 0.03680 0.02936 0.0742 0.0192 0.7805 13.750 0.8106 0.03786 0.03047 0.0748 0.0190 0.7829 14.000 0.8206 0.03910 0.03175 0.0755 0.0186 0.7855 14.250 0.8309 0.04035 0.03306 0.0761 0.0184 0.7880 14.500 0.8416 0.04163 0.03440 0.0766 0.0180 0.7905 14.750 0.8518 0.04296 0.03579 0.0771 0.0178 0.7929 15.000 0.8621 0.04427 0.03718 0.0776 0.0176 0.7956 15.250 0.8707 0.04573 0.03873 0.0781 0.0172 0.7985 15.500 0.8803 0.04715 0.04023 0.0785 0.0171 0.8018 15.750 0.8891 0.04868 0.04183 0.0788 0.0169 0.8052 16.000 0.8964 0.05039 0.04361 0.0791 0.0167 0.8084 16.250 0.9049 0.05206 0.04534 0.0792 0.0166 0.8115 16.500 0.9119 0.05385 0.04720 0.0794 0.0162 0.8148 16.750 0.9197 0.05560 0.04904 0.0795 0.0160 0.8183 17.000 0.9244 0.05767 0.05119 0.0795 0.0160 0.8219 17.250 0.9300 0.05974 0.05334 0.0795 0.0159 0.8257 17.500 0.9349 0.06193 0.05560 0.0792 0.0157 0.8293 17.750 0.9384 0.06430 0.05805 0.0790 0.0157 0.8329 18.000 0.9408 0.06680 0.06064 0.0788 0.0155 0.8369 18.250 0.9446 0.06920 0.06314 0.0784 0.0154 0.8412 18.500 0.9479 0.07174 0.06578 0.0778 0.0154 0.8456 19.000 0.9532 0.07715 0.07144 0.0764 0.0152 0.8546 19.250 0.9541 0.08012 0.07453 0.0756 0.0151 0.8597