XFOIL Version 6.96 Calculated polar for: BOEING-VERTOL VR-13 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.5577 0.12849 0.12622 0.0176 1.0000 0.0059 -11.000 -0.5553 0.12415 0.12188 0.0157 1.0000 0.0058 -9.000 -0.7841 0.02647 0.02228 -0.0235 0.9843 0.0053 -8.750 -0.7662 0.02327 0.01863 -0.0228 0.9747 0.0056 -8.500 -0.7460 0.02132 0.01636 -0.0219 0.9671 0.0059 -8.250 -0.7255 0.01982 0.01459 -0.0208 0.9602 0.0062 -8.000 -0.7047 0.01860 0.01312 -0.0195 0.9525 0.0066 -7.750 -0.6828 0.01767 0.01202 -0.0185 0.9457 0.0069 -7.500 -0.6599 0.01704 0.01131 -0.0175 0.9389 0.0074 -7.250 -0.6364 0.01645 0.01060 -0.0166 0.9330 0.0079 -7.000 -0.6126 0.01577 0.00980 -0.0158 0.9264 0.0087 -6.750 -0.5893 0.01517 0.00908 -0.0148 0.9204 0.0094 -6.500 -0.5635 0.01487 0.00876 -0.0144 0.9137 0.0102 -6.250 -0.5388 0.01454 0.00833 -0.0136 0.9077 0.0113 -6.000 -0.5133 0.01412 0.00783 -0.0131 0.9018 0.0125 -5.750 -0.4867 0.01409 0.00781 -0.0128 0.8957 0.0135 -5.500 -0.4609 0.01388 0.00754 -0.0122 0.8900 0.0146 -5.250 -0.4348 0.01348 0.00701 -0.0118 0.8834 0.0158 -5.000 -0.4086 0.01336 0.00690 -0.0114 0.8776 0.0168 -4.750 -0.3814 0.01328 0.00680 -0.0112 0.8713 0.0182 -4.500 -0.3549 0.01302 0.00645 -0.0108 0.8646 0.0197 -4.250 -0.3286 0.01268 0.00601 -0.0103 0.8582 0.0204 -4.000 -0.3033 0.01206 0.00537 -0.0097 0.8513 0.0216 -3.750 -0.2770 0.01178 0.00505 -0.0093 0.8456 0.0226 -3.500 -0.2499 0.01153 0.00478 -0.0091 0.8391 0.0240 -3.250 -0.2237 0.01126 0.00443 -0.0086 0.8310 0.0253 -3.000 -0.1970 0.01101 0.00412 -0.0081 0.8192 0.0262 -2.750 -0.1715 0.01058 0.00365 -0.0075 0.8070 0.0278 -2.500 -0.1450 0.01035 0.00336 -0.0071 0.7955 0.0291 -2.250 -0.1183 0.01014 0.00309 -0.0067 0.7839 0.0305 -2.000 -0.0914 0.00997 0.00285 -0.0063 0.7718 0.0318 -1.750 -0.0641 0.00983 0.00265 -0.0061 0.7589 0.0333 -1.500 -0.0369 0.00965 0.00242 -0.0058 0.7463 0.0351 -1.250 -0.0097 0.00948 0.00221 -0.0055 0.7335 0.0378 -1.000 0.0178 0.00937 0.00206 -0.0053 0.7206 0.0415 -0.750 0.0454 0.00925 0.00191 -0.0051 0.7067 0.0482 -0.500 0.0725 0.00906 0.00178 -0.0049 0.6912 0.0763 -0.250 0.0976 0.00861 0.00166 -0.0045 0.6721 0.1987 0.000 0.1186 0.00773 0.00153 -0.0035 0.6481 0.4556 0.250 0.1291 0.00639 0.00147 0.0003 0.6196 0.8257 0.500 0.1983 0.00685 0.00186 -0.0082 0.5351 0.9610 0.750 0.2409 0.00750 0.00209 -0.0114 0.4476 0.9790 1.000 0.2892 0.00813 0.00230 -0.0161 0.3612 0.9895 1.250 0.3255 0.00848 0.00240 -0.0182 0.3137 0.9936 1.500 0.3589 0.00870 0.00245 -0.0196 0.2849 0.9952 1.750 0.3924 0.00887 0.00249 -0.0210 0.2658 0.9968 2.000 0.4256 0.00901 0.00254 -0.0223 0.2512 0.9984 2.250 0.4586 0.00916 0.00260 -0.0235 0.2389 0.9999 2.500 0.4854 0.00929 0.00266 -0.0234 0.2288 1.0000 2.750 0.5113 0.00941 0.00272 -0.0231 0.2194 1.0000 3.000 0.5370 0.00953 0.00280 -0.0228 0.2114 1.0000 3.250 0.5626 0.00968 0.00289 -0.0224 0.2026 1.0000 3.500 0.5881 0.00981 0.00299 -0.0220 0.1949 1.0000 3.750 0.6133 0.00998 0.00311 -0.0216 0.1872 1.0000 4.000 0.6387 0.01011 0.00322 -0.0212 0.1813 1.0000 4.250 0.6639 0.01028 0.00336 -0.0208 0.1750 1.0000 4.500 0.6890 0.01045 0.00350 -0.0203 0.1695 1.0000 4.750 0.7139 0.01062 0.00366 -0.0198 0.1628 1.0000 5.000 0.7387 0.01083 0.00382 -0.0193 0.1566 1.0000 5.250 0.7636 0.01100 0.00399 -0.0188 0.1518 1.0000 5.500 0.7882 0.01120 0.00419 -0.0183 0.1471 1.0000 5.750 0.8127 0.01142 0.00440 -0.0178 0.1430 1.0000 6.000 0.8373 0.01161 0.00460 -0.0172 0.1392 1.0000 6.250 0.8615 0.01183 0.00482 -0.0167 0.1339 1.0000 6.500 0.8856 0.01209 0.00506 -0.0161 0.1294 1.0000 6.750 0.9098 0.01229 0.00530 -0.0155 0.1260 1.0000 7.000 0.9339 0.01253 0.00555 -0.0149 0.1225 1.0000 7.250 0.9575 0.01280 0.00583 -0.0142 0.1190 1.0000 7.500 0.9811 0.01307 0.00613 -0.0136 0.1157 1.0000 7.750 1.0049 0.01331 0.00640 -0.0129 0.1119 1.0000 8.000 1.0282 0.01359 0.00669 -0.0123 0.1074 1.0000 8.250 1.0511 0.01392 0.00702 -0.0115 0.1030 1.0000 8.500 1.0745 0.01417 0.00733 -0.0109 0.0990 1.0000 8.750 1.0972 0.01449 0.00766 -0.0101 0.0941 1.0000 9.000 1.1196 0.01483 0.00802 -0.0094 0.0892 1.0000 9.250 1.1421 0.01516 0.00838 -0.0086 0.0834 1.0000 9.500 1.1638 0.01556 0.00878 -0.0078 0.0773 1.0000 9.750 1.1852 0.01598 0.00920 -0.0069 0.0695 1.0000 10.000 1.2057 0.01647 0.00968 -0.0059 0.0622 1.0000 10.250 1.2254 0.01703 0.01023 -0.0049 0.0560 1.0000 10.500 1.2454 0.01753 0.01078 -0.0038 0.0524 1.0000 10.750 1.2642 0.01812 0.01139 -0.0026 0.0487 1.0000 11.000 1.2831 0.01869 0.01201 -0.0015 0.0456 1.0000 11.250 1.3022 0.01921 0.01261 -0.0003 0.0425 1.0000 11.500 1.3194 0.01988 0.01330 0.0010 0.0388 1.0000 11.750 1.3365 0.02054 0.01403 0.0023 0.0358 1.0000 12.000 1.3532 0.02119 0.01473 0.0036 0.0326 1.0000 12.250 1.3677 0.02200 0.01556 0.0052 0.0294 1.0000 12.500 1.3822 0.02273 0.01636 0.0067 0.0273 1.0000 12.750 1.3935 0.02354 0.01722 0.0087 0.0254 1.0000 13.000 1.4025 0.02446 0.01819 0.0109 0.0237 1.0000 13.250 1.4109 0.02548 0.01928 0.0130 0.0224 1.0000 13.500 1.4212 0.02642 0.02035 0.0146 0.0217 1.0000 13.750 1.4305 0.02749 0.02153 0.0162 0.0208 1.0000 14.000 1.4384 0.02871 0.02285 0.0177 0.0198 1.0000 14.250 1.4448 0.03012 0.02435 0.0190 0.0189 1.0000 14.500 1.4490 0.03179 0.02610 0.0203 0.0179 1.0000 14.750 1.4510 0.03374 0.02815 0.0214 0.0171 1.0000 15.000 1.4561 0.03549 0.03003 0.0221 0.0165 1.0000 15.250 1.4592 0.03754 0.03220 0.0226 0.0158 1.0000 15.500 1.4598 0.03992 0.03470 0.0229 0.0151 1.0000 15.750 1.4578 0.04275 0.03765 0.0228 0.0145 1.0000 16.000 1.4528 0.04610 0.04114 0.0223 0.0140 1.0000 16.250 1.4444 0.05014 0.04531 0.0212 0.0136 1.0000 16.500 1.4320 0.05508 0.05040 0.0194 0.0133 1.0000 16.750 1.4149 0.06118 0.05667 0.0165 0.0131 1.0000 17.000 1.3918 0.06888 0.06456 0.0125 0.0131 1.0000 17.250 1.3621 0.07812 0.07401 0.0075 0.0132 1.0000 17.500 1.3271 0.08837 0.08444 0.0024 0.0135 1.0000 17.750 1.2903 0.09871 0.09496 -0.0026 0.0139 1.0000