XFOIL Version 6.94 Calculated polar for: BOEING-VERTOL VR-7 AIRFOIL WITH 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.1824 0.00882 0.00366 -0.0177 0.6436 0.9741 0.500 0.2590 0.00883 0.00346 -0.0221 0.6296 1.0000 1.000 0.3168 0.00896 0.00344 -0.0230 0.6163 1.0000 1.500 0.3759 0.00915 0.00341 -0.0240 0.6031 1.0000 2.000 0.4370 0.00926 0.00348 -0.0253 0.5888 1.0000 2.500 0.4972 0.00945 0.00355 -0.0264 0.5747 1.0000 3.000 0.5571 0.00961 0.00358 -0.0274 0.5580 1.0000 3.500 0.6176 0.00974 0.00370 -0.0286 0.5401 1.0000 4.000 0.6777 0.00997 0.00393 -0.0297 0.5225 1.0000 4.500 0.7373 0.01026 0.00418 -0.0307 0.5051 1.0000 5.000 0.7965 0.01057 0.00447 -0.0317 0.4868 1.0000 5.500 0.8555 0.01089 0.00478 -0.0327 0.4658 1.0000 6.000 0.9142 0.01124 0.00517 -0.0337 0.4432 1.0000 6.500 0.9725 0.01160 0.00559 -0.0347 0.4172 1.0000 7.000 1.0289 0.01219 0.00602 -0.0357 0.3664 1.0000 7.500 1.0838 0.01304 0.00671 -0.0367 0.3080 1.0000 8.500 1.1730 0.01737 0.00991 -0.0380 0.1172 1.0000 9.000 1.2137 0.01937 0.01169 -0.0378 0.0740 1.0000 9.500 1.2519 0.02125 0.01353 -0.0372 0.0547 1.0000 10.000 1.2830 0.02346 0.01568 -0.0362 0.0336 1.0000 10.500 1.3039 0.02596 0.01821 -0.0341 0.0250 1.0000 11.000 1.3249 0.02877 0.02114 -0.0327 0.0206 1.0000 11.500 1.3437 0.03202 0.02454 -0.0318 0.0181 1.0000 12.000 1.3612 0.03559 0.02830 -0.0313 0.0165 1.0000 12.500 1.3739 0.03981 0.03266 -0.0310 0.0139 1.0000 13.000 1.3845 0.04435 0.03739 -0.0310 0.0124 1.0000 13.500 1.3922 0.04930 0.04254 -0.0312 0.0113 1.0000 14.000 1.3975 0.05463 0.04810 -0.0316 0.0103 1.0000 14.500 1.3994 0.06059 0.05428 -0.0323 0.0094 1.0000 15.000 1.4006 0.06694 0.06086 -0.0335 0.0069 1.0000 15.500 1.3939 0.07459 0.06867 -0.0353 0.0030 1.0000 16.000 1.3816 0.08339 0.07767 -0.0377 0.0024 1.0000 16.500 1.3678 0.09281 0.08733 -0.0407 0.0021 1.0000 17.000 1.3534 0.10264 0.09742 -0.0442 0.0020 1.0000 17.500 1.3371 0.11313 0.10818 -0.0483 0.0019 1.0000 18.000 1.3195 0.12419 0.11952 -0.0532 0.0019 1.0000 18.500 1.3003 0.13606 0.13166 -0.0589 0.0019 1.0000 19.000 1.2802 0.14868 0.14456 -0.0657 0.0019 1.0000 19.500 1.2591 0.16220 0.15834 -0.0735 0.0019 1.0000 20.000 1.2349 0.17736 0.17378 -0.0828 0.0019 1.0000 21.000 1.1804 0.21332 0.21028 -0.1059 0.0022 1.0000 21.500 1.1622 0.23117 0.22834 -0.1174 0.0024 1.0000 22.000 1.1527 0.24764 0.24497 -0.1279 0.0026 1.0000 22.500 1.1531 0.26104 0.25845 -0.1367 0.0026 1.0000 23.000 1.1595 0.27215 0.26960 -0.1443 0.0026 1.0000 24.000 1.1689 0.31015 0.30745 -0.1637 0.0043 1.0000 24.500 1.1843 0.31622 0.31353 -0.1687 0.0047 1.0000