XFOIL Version 6.96 Calculated polar for: BOEING-VERTOL VR-11X 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 ------ -------- --------- --------- -------- -------- -------- -8.250 -0.4973 0.06488 0.06217 -0.0428 0.8687 0.0105 -8.000 -0.4968 0.06085 0.05804 -0.0438 0.8678 0.0103 -7.750 -0.4942 0.05669 0.05375 -0.0443 0.8669 0.0102 -7.500 -0.4903 0.05215 0.04904 -0.0443 0.8661 0.0101 -7.250 -0.4849 0.04711 0.04375 -0.0437 0.8652 0.0102 -7.000 -0.4769 0.04242 0.03880 -0.0424 0.8644 0.0103 -6.750 -0.4653 0.03888 0.03502 -0.0413 0.8638 0.0102 -6.500 -0.4519 0.03544 0.03133 -0.0400 0.8631 0.0099 -6.250 -0.4377 0.03172 0.02728 -0.0383 0.8622 0.0096 -6.000 -0.4233 0.02754 0.02267 -0.0361 0.8611 0.0093 -5.750 -0.4072 0.02331 0.01791 -0.0337 0.8603 0.0090 -5.500 -0.3865 0.02046 0.01463 -0.0322 0.8594 0.0090 -5.250 -0.3626 0.01874 0.01263 -0.0313 0.8584 0.0092 -5.000 -0.3376 0.01745 0.01112 -0.0306 0.8573 0.0093 -4.750 -0.3119 0.01640 0.00990 -0.0301 0.8563 0.0096 -4.500 -0.2859 0.01553 0.00889 -0.0296 0.8555 0.0099 -4.250 -0.2597 0.01482 0.00807 -0.0292 0.8549 0.0102 -4.000 -0.2333 0.01425 0.00741 -0.0289 0.8543 0.0105 -3.750 -0.2082 0.01368 0.00677 -0.0282 0.8527 0.0108 -3.500 -0.1844 0.01315 0.00619 -0.0272 0.8499 0.0111 -3.250 -0.1578 0.01273 0.00578 -0.0270 0.8464 0.0115 -3.000 -0.1313 0.01241 0.00545 -0.0266 0.8433 0.0122 -2.750 -0.1053 0.01209 0.00509 -0.0261 0.8403 0.0131 -2.500 -0.0799 0.01177 0.00471 -0.0254 0.8372 0.0136 -2.250 -0.0540 0.01135 0.00429 -0.0249 0.8331 0.0142 -2.000 -0.0274 0.01102 0.00396 -0.0245 0.8277 0.0151 -1.750 -0.0016 0.01072 0.00362 -0.0238 0.8227 0.0163 -1.500 0.0259 0.01044 0.00334 -0.0236 0.8166 0.0178 -1.250 0.0530 0.01017 0.00307 -0.0233 0.8101 0.0206 -1.000 0.0803 0.00991 0.00285 -0.0230 0.8039 0.0275 -0.750 0.1072 0.00959 0.00263 -0.0228 0.7945 0.0556 -0.500 0.1299 0.00874 0.00242 -0.0220 0.7829 0.2441 -0.250 0.1451 0.00745 0.00223 -0.0198 0.7697 0.5690 0.000 0.1586 0.00629 0.00207 -0.0162 0.7403 0.8411 0.500 0.2889 0.00795 0.00272 -0.0323 0.4953 0.9756 0.750 0.3230 0.00844 0.00284 -0.0341 0.4255 0.9785 1.000 0.3547 0.00887 0.00296 -0.0353 0.3666 0.9819 1.500 0.4177 0.00954 0.00317 -0.0375 0.2900 0.9877 1.750 0.4504 0.00980 0.00326 -0.0388 0.2582 0.9899 2.000 0.4824 0.01008 0.00336 -0.0400 0.2289 0.9924 2.500 0.5470 0.01052 0.00357 -0.0425 0.1984 0.9961 2.750 0.5800 0.01069 0.00367 -0.0438 0.1904 0.9978 3.000 0.6130 0.01087 0.00378 -0.0452 0.1840 0.9993 3.250 0.6421 0.01106 0.00391 -0.0457 0.1784 1.0000 3.500 0.6666 0.01118 0.00403 -0.0452 0.1749 1.0000 3.750 0.6908 0.01134 0.00415 -0.0446 0.1714 1.0000 4.000 0.7148 0.01151 0.00429 -0.0440 0.1684 1.0000 4.250 0.7385 0.01170 0.00445 -0.0433 0.1654 1.0000 4.500 0.7620 0.01191 0.00465 -0.0426 0.1627 1.0000 4.750 0.7858 0.01206 0.00481 -0.0420 0.1611 1.0000 5.000 0.8094 0.01222 0.00498 -0.0413 0.1583 1.0000 5.250 0.8327 0.01240 0.00515 -0.0405 0.1545 1.0000 5.500 0.8555 0.01263 0.00535 -0.0397 0.1501 1.0000 5.750 0.8781 0.01288 0.00557 -0.0389 0.1470 1.0000 6.000 0.9014 0.01303 0.00576 -0.0381 0.1448 1.0000 6.250 0.9245 0.01321 0.00595 -0.0374 0.1415 1.0000 6.500 0.9471 0.01342 0.00616 -0.0365 0.1385 1.0000 6.750 0.9693 0.01365 0.00639 -0.0356 0.1357 1.0000 7.000 0.9909 0.01393 0.00666 -0.0346 0.1328 1.0000 7.250 1.0135 0.01410 0.00689 -0.0338 0.1302 1.0000 7.500 1.0357 0.01431 0.00712 -0.0329 0.1267 1.0000 7.750 1.0574 0.01455 0.00736 -0.0319 0.1230 1.0000 8.000 1.0783 0.01483 0.00763 -0.0308 0.1190 1.0000 8.250 1.0999 0.01505 0.00791 -0.0298 0.1161 1.0000 8.500 1.1209 0.01531 0.00818 -0.0287 0.1119 1.0000 8.750 1.1411 0.01561 0.00847 -0.0276 0.1069 1.0000 9.000 1.1614 0.01589 0.00879 -0.0264 0.1018 1.0000 9.250 1.1808 0.01624 0.00912 -0.0251 0.0951 1.0000 9.500 1.1996 0.01662 0.00948 -0.0237 0.0871 1.0000 9.750 1.2175 0.01705 0.00990 -0.0223 0.0800 1.0000 10.000 1.2346 0.01753 0.01036 -0.0207 0.0733 1.0000 10.250 1.2501 0.01797 0.01082 -0.0188 0.0683 1.0000 10.500 1.2635 0.01849 0.01133 -0.0165 0.0631 1.0000 10.750 1.2778 0.01895 0.01183 -0.0144 0.0593 1.0000 11.000 1.2916 0.01950 0.01240 -0.0124 0.0548 1.0000 11.250 1.3056 0.02008 0.01300 -0.0104 0.0498 1.0000 11.500 1.3187 0.02077 0.01369 -0.0084 0.0440 1.0000 11.750 1.3318 0.02148 0.01440 -0.0065 0.0370 1.0000 12.000 1.3427 0.02237 0.01528 -0.0044 0.0293 1.0000 12.500 1.3661 0.02404 0.01702 -0.0005 0.0241 1.0000 12.750 1.3779 0.02489 0.01793 0.0013 0.0231 1.0000 13.000 1.3889 0.02580 0.01891 0.0031 0.0223 1.0000 13.250 1.3991 0.02678 0.01997 0.0049 0.0215 1.0000 13.500 1.4082 0.02784 0.02112 0.0068 0.0208 1.0000 13.750 1.4175 0.02890 0.02227 0.0085 0.0204 1.0000 14.000 1.4264 0.03001 0.02348 0.0102 0.0201 1.0000 14.250 1.4340 0.03123 0.02480 0.0119 0.0197 1.0000 14.500 1.4404 0.03257 0.02625 0.0136 0.0194 1.0000 14.750 1.4456 0.03403 0.02783 0.0153 0.0191 1.0000 15.000 1.4492 0.03566 0.02956 0.0169 0.0188 1.0000 15.250 1.4511 0.03750 0.03152 0.0184 0.0184 1.0000 15.500 1.4508 0.03960 0.03374 0.0198 0.0181 1.0000 15.750 1.4483 0.04203 0.03628 0.0210 0.0177 1.0000 16.000 1.4436 0.04483 0.03921 0.0218 0.0175 1.0000 16.250 1.4364 0.04815 0.04266 0.0222 0.0172 1.0000 16.500 1.4267 0.05215 0.04680 0.0219 0.0170 1.0000 16.750 1.4140 0.05697 0.05178 0.0207 0.0168 1.0000 17.000 1.3979 0.06276 0.05774 0.0186 0.0167 1.0000 17.250 1.3781 0.06961 0.06476 0.0156 0.0166 1.0000 17.500 1.3543 0.07751 0.07285 0.0119 0.0166 1.0000 17.750 1.3263 0.08636 0.08188 0.0077 0.0166 1.0000 18.000 1.2962 0.09562 0.09132 0.0034 0.0167 1.0000 18.250 1.2654 0.10485 0.10070 -0.0007 0.0169 1.0000