XFOIL Version 6.96 Calculated polar for: BOEING-VERTOL VR-14 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.4588 0.11632 0.11482 0.0099 1.0000 0.0045 -10.250 -0.5921 0.11842 0.11684 0.0236 1.0000 0.0046 -10.000 -0.5890 0.11469 0.11312 0.0220 1.0000 0.0044 -9.500 -0.5849 0.10637 0.10482 0.0181 1.0000 0.0041 -8.000 -0.7373 0.02054 0.01669 -0.0143 0.9614 0.0026 -7.750 -0.7197 0.01820 0.01397 -0.0127 0.9542 0.0027 -7.500 -0.6987 0.01671 0.01220 -0.0115 0.9475 0.0027 -7.250 -0.6767 0.01556 0.01084 -0.0104 0.9416 0.0027 -7.000 -0.6530 0.01461 0.00972 -0.0097 0.9350 0.0028 -6.750 -0.6295 0.01385 0.00880 -0.0088 0.9289 0.0028 -6.500 -0.6044 0.01318 0.00801 -0.0082 0.9227 0.0029 -6.250 -0.5795 0.01262 0.00734 -0.0075 0.9164 0.0029 -6.000 -0.5550 0.01178 0.00635 -0.0068 0.9100 0.0033 -5.750 -0.5296 0.01128 0.00575 -0.0062 0.9032 0.0036 -5.500 -0.5037 0.01087 0.00527 -0.0058 0.8969 0.0039 -5.250 -0.4775 0.01050 0.00484 -0.0054 0.8902 0.0042 -5.000 -0.4512 0.01018 0.00445 -0.0049 0.8839 0.0045 -4.750 -0.4246 0.00987 0.00408 -0.0046 0.8763 0.0048 -4.500 -0.3982 0.00955 0.00370 -0.0042 0.8688 0.0056 -4.250 -0.3715 0.00928 0.00339 -0.0039 0.8604 0.0067 -4.000 -0.3445 0.00904 0.00312 -0.0036 0.8531 0.0083 -3.750 -0.3173 0.00884 0.00289 -0.0034 0.8451 0.0103 -3.500 -0.2899 0.00868 0.00275 -0.0032 0.8361 0.0129 -3.250 -0.2626 0.00856 0.00259 -0.0030 0.8222 0.0151 -3.000 -0.2353 0.00849 0.00248 -0.0028 0.8052 0.0172 -2.750 -0.2077 0.00841 0.00235 -0.0027 0.7901 0.0190 -2.500 -0.1800 0.00837 0.00226 -0.0026 0.7755 0.0201 -2.250 -0.1528 0.00818 0.00199 -0.0023 0.7597 0.0226 -2.000 -0.1251 0.00809 0.00185 -0.0022 0.7439 0.0243 -1.750 -0.0973 0.00801 0.00171 -0.0021 0.7283 0.0257 -1.500 -0.0694 0.00792 0.00157 -0.0020 0.7120 0.0266 -1.250 -0.0414 0.00786 0.00144 -0.0020 0.6947 0.0274 -1.000 -0.0136 0.00778 0.00130 -0.0019 0.6754 0.0297 -0.750 0.0143 0.00774 0.00119 -0.0019 0.6525 0.0335 -0.500 0.0420 0.00777 0.00111 -0.0018 0.6146 0.0380 -0.250 0.0695 0.00785 0.00105 -0.0018 0.5640 0.0515 0.000 0.0959 0.00788 0.00102 -0.0017 0.4946 0.1173 0.250 0.1211 0.00772 0.00102 -0.0015 0.4329 0.2515 0.500 0.1443 0.00732 0.00101 -0.0011 0.3646 0.4647 0.750 0.1585 0.00623 0.00100 0.0015 0.3255 0.8267 1.000 0.2061 0.00625 0.00124 -0.0026 0.2854 0.9650 1.250 0.2431 0.00646 0.00133 -0.0046 0.2643 0.9780 1.500 0.2850 0.00669 0.00146 -0.0077 0.2463 0.9882 1.750 0.3248 0.00688 0.00156 -0.0104 0.2315 0.9939 2.000 0.3589 0.00700 0.00161 -0.0119 0.2196 0.9952 2.250 0.3917 0.00712 0.00166 -0.0131 0.2084 0.9963 2.500 0.4241 0.00726 0.00171 -0.0142 0.1950 0.9974 2.750 0.4561 0.00741 0.00179 -0.0152 0.1814 0.9985 3.000 0.4875 0.00754 0.00186 -0.0161 0.1706 0.9994 3.250 0.5181 0.00766 0.00193 -0.0168 0.1633 1.0000 3.500 0.5441 0.00778 0.00202 -0.0165 0.1559 1.0000 3.750 0.5701 0.00789 0.00211 -0.0162 0.1503 1.0000 4.000 0.5960 0.00802 0.00221 -0.0158 0.1440 1.0000 4.250 0.6219 0.00815 0.00232 -0.0155 0.1388 1.0000 4.500 0.6477 0.00830 0.00245 -0.0151 0.1321 1.0000 4.750 0.6735 0.00845 0.00257 -0.0148 0.1265 1.0000 5.000 0.6992 0.00859 0.00271 -0.0144 0.1219 1.0000 5.250 0.7248 0.00877 0.00286 -0.0140 0.1160 1.0000 5.500 0.7503 0.00894 0.00302 -0.0137 0.1101 1.0000 5.750 0.7757 0.00913 0.00319 -0.0133 0.1041 1.0000 6.000 0.8010 0.00932 0.00337 -0.0129 0.0985 1.0000 6.250 0.8263 0.00952 0.00356 -0.0125 0.0924 1.0000 6.500 0.8514 0.00975 0.00378 -0.0121 0.0854 1.0000 6.750 0.8761 0.01004 0.00401 -0.0116 0.0750 1.0000 7.000 0.9004 0.01037 0.00428 -0.0111 0.0633 1.0000 7.250 0.9247 0.01070 0.00458 -0.0106 0.0550 1.0000 7.500 0.9491 0.01101 0.00489 -0.0101 0.0491 1.0000 7.750 0.9732 0.01135 0.00522 -0.0096 0.0442 1.0000 8.000 0.9975 0.01165 0.00554 -0.0091 0.0406 1.0000 8.250 1.0219 0.01193 0.00584 -0.0086 0.0377 1.0000 8.500 1.0451 0.01237 0.00625 -0.0080 0.0308 1.0000 8.750 1.0682 0.01282 0.00668 -0.0074 0.0257 1.0000 9.000 1.0916 0.01322 0.00709 -0.0068 0.0223 1.0000 9.250 1.1147 0.01362 0.00751 -0.0062 0.0198 1.0000 9.500 1.1375 0.01407 0.00796 -0.0055 0.0177 1.0000 9.750 1.1604 0.01449 0.00842 -0.0049 0.0162 1.0000 10.000 1.1833 0.01488 0.00888 -0.0042 0.0153 1.0000 10.250 1.2057 0.01532 0.00935 -0.0036 0.0141 1.0000 10.500 1.2276 0.01582 0.00988 -0.0028 0.0128 1.0000 10.750 1.2492 0.01636 0.01045 -0.0021 0.0114 1.0000 11.000 1.2712 0.01681 0.01096 -0.0014 0.0108 1.0000 11.250 1.2927 0.01732 0.01152 -0.0007 0.0100 1.0000 11.500 1.3136 0.01788 0.01213 0.0000 0.0091 1.0000 11.750 1.3338 0.01850 0.01279 0.0009 0.0081 1.0000 12.000 1.3540 0.01909 0.01344 0.0017 0.0075 1.0000 12.250 1.3738 0.01972 0.01412 0.0025 0.0066 1.0000 12.500 1.3920 0.02046 0.01491 0.0035 0.0055 1.0000 12.750 1.4099 0.02121 0.01572 0.0045 0.0047 1.0000 13.000 1.4258 0.02211 0.01667 0.0057 0.0034 1.0000 13.250 1.4381 0.02329 0.01792 0.0072 0.0018 1.0000 13.500 1.4483 0.02456 0.01929 0.0090 0.0010 1.0000 13.750 1.4577 0.02567 0.02051 0.0109 0.0008 1.0000 14.000 1.4631 0.02687 0.02183 0.0132 0.0007 1.0000 14.250 1.4680 0.02820 0.02326 0.0153 0.0007 1.0000 14.500 1.4713 0.02975 0.02493 0.0171 0.0006 1.0000 14.750 1.4735 0.03152 0.02682 0.0185 0.0006 1.0000 15.000 1.4743 0.03354 0.02897 0.0196 0.0006 1.0000 15.250 1.4730 0.03595 0.03152 0.0203 0.0005 1.0000 15.500 1.4696 0.03879 0.03449 0.0204 0.0005 1.0000 15.750 1.4637 0.04219 0.03804 0.0200 0.0005 1.0000 16.000 1.4544 0.04637 0.04237 0.0187 0.0005 1.0000 16.250 1.4399 0.05179 0.04796 0.0162 0.0005 1.0000 16.500 1.4193 0.05904 0.05540 0.0119 0.0005 1.0000 16.750 1.3876 0.06938 0.06595 0.0054 0.0005 1.0000 17.000 1.3406 0.08289 0.07968 -0.0022 0.0005 1.0000 17.250 1.2877 0.09655 0.09352 -0.0091 0.0006 1.0000