XFOIL Version 6.94 Calculated polar for: MRC-16 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3224 0.00747 0.00284 -0.0605 0.6959 0.9185 0.500 0.3807 0.00766 0.00294 -0.0605 0.6783 0.9438 1.000 0.4459 0.00788 0.00305 -0.0622 0.6602 0.9617 1.500 0.5258 0.00809 0.00313 -0.0674 0.6408 0.9710 2.000 0.6013 0.00828 0.00320 -0.0718 0.6206 0.9809 2.500 0.6777 0.00847 0.00328 -0.0766 0.5994 0.9902 3.500 0.8137 0.00880 0.00345 -0.0829 0.5556 1.0000 4.000 0.8564 0.00901 0.00360 -0.0807 0.5343 1.0000 4.500 0.8977 0.00926 0.00380 -0.0781 0.5126 1.0000 5.000 0.9378 0.00956 0.00407 -0.0753 0.4902 1.0000 5.500 0.9770 0.00991 0.00436 -0.0722 0.4673 1.0000 6.000 1.0153 0.01033 0.00471 -0.0690 0.4436 1.0000 7.000 1.0931 0.01125 0.00557 -0.0629 0.3925 1.0000 7.500 1.1307 0.01188 0.00611 -0.0598 0.3645 1.0000 8.000 1.1695 0.01251 0.00672 -0.0571 0.3343 1.0000 8.500 1.2042 0.01331 0.00746 -0.0537 0.3027 1.0000 9.000 1.2336 0.01429 0.00832 -0.0496 0.2693 1.0000 9.500 1.2628 0.01543 0.00936 -0.0458 0.2349 1.0000 10.000 1.2904 0.01677 0.01061 -0.0421 0.2012 1.0000 10.500 1.3145 0.01840 0.01216 -0.0384 0.1677 1.0000 11.000 1.3353 0.02037 0.01402 -0.0346 0.1363 1.0000 11.500 1.3513 0.02278 0.01632 -0.0308 0.1059 1.0000 12.000 1.3641 0.02560 0.01904 -0.0273 0.0793 1.0000 12.500 1.3739 0.02886 0.02227 -0.0240 0.0585 1.0000 13.000 1.3802 0.03262 0.02605 -0.0211 0.0436 1.0000 13.500 1.3795 0.03728 0.03079 -0.0184 0.0333 1.0000 14.000 1.3821 0.04196 0.03560 -0.0167 0.0278 1.0000 14.500 1.3708 0.04847 0.04229 -0.0152 0.0233 1.0000 15.000 1.3738 0.05379 0.04781 -0.0148 0.0210 1.0000 15.500 1.3683 0.06039 0.05458 -0.0149 0.0188 1.0000 16.000 1.3497 0.06893 0.06332 -0.0155 0.0171 1.0000 16.500 1.3209 0.07914 0.07379 -0.0169 0.0158 1.0000 17.000 1.3151 0.08663 0.08150 -0.0184 0.0153 1.0000 17.500 1.3055 0.09487 0.08997 -0.0204 0.0146 1.0000 18.000 1.2941 0.10352 0.09883 -0.0228 0.0140 1.0000 18.500 1.2825 0.11232 0.10786 -0.0256 0.0134 1.0000 19.000 1.2710 0.12139 0.11712 -0.0289 0.0129 1.0000 19.500 1.2598 0.13061 0.12654 -0.0326 0.0124 1.0000 20.000 1.2486 0.13996 0.13608 -0.0368 0.0119 1.0000 20.500 1.2373 0.14960 0.14590 -0.0416 0.0115 1.0000 21.000 1.2249 0.15974 0.15623 -0.0470 0.0111 1.0000 21.500 1.2090 0.17096 0.16768 -0.0533 0.0108 1.0000 22.000 1.1863 0.18437 0.18135 -0.0615 0.0105 1.0000 22.500 1.1587 0.20024 0.19751 -0.0715 0.0104 1.0000 23.000 1.1276 0.21921 0.21675 -0.0836 0.0105 1.0000