XFOIL Version 6.96 Calculated polar for: Marsden 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.500 0.4479 0.10722 0.10140 -0.1557 0.4562 0.0568 -12.250 0.4595 0.10540 0.09960 -0.1565 0.4558 0.0573 -12.000 0.2468 0.06369 0.05774 -0.1809 0.4573 0.0557 -11.750 0.2686 0.06361 0.05774 -0.1798 0.4570 0.0561 -11.500 0.2249 0.05482 0.04883 -0.1860 0.4570 0.0541 -11.250 0.1571 0.04625 0.04000 -0.1913 0.4571 0.0531 -11.000 0.1233 0.04192 0.03546 -0.1923 0.4570 0.0527 -10.750 0.1100 0.03943 0.03283 -0.1920 0.4567 0.0527 -10.500 0.1050 0.03769 0.03099 -0.1912 0.4565 0.0528 -10.250 0.1023 0.03623 0.02944 -0.1899 0.4563 0.0530 -10.000 0.0987 0.03518 0.02831 -0.1879 0.4561 0.0531 -9.750 0.0933 0.03436 0.02740 -0.1851 0.4559 0.0532 -9.500 0.0966 0.03346 0.02642 -0.1834 0.4556 0.0532 -9.250 0.1053 0.03265 0.02552 -0.1823 0.4554 0.0533 -9.000 0.1172 0.03192 0.02471 -0.1814 0.4551 0.0535 -8.750 0.1317 0.03127 0.02399 -0.1806 0.4547 0.0536 -8.500 0.1477 0.03069 0.02335 -0.1798 0.4544 0.0538 -8.250 0.1650 0.03021 0.02280 -0.1790 0.4541 0.0540 -8.000 0.1832 0.02978 0.02233 -0.1781 0.4537 0.0542 -7.750 0.2020 0.02943 0.02193 -0.1773 0.4534 0.0544 -7.500 0.2214 0.02912 0.02158 -0.1764 0.4530 0.0546 -7.250 0.2416 0.02884 0.02127 -0.1756 0.4525 0.0548 -7.000 0.2626 0.02857 0.02095 -0.1749 0.4520 0.0550 -6.750 0.2844 0.02835 0.02069 -0.1743 0.4514 0.0553 -6.500 0.3064 0.02820 0.02051 -0.1737 0.4509 0.0554 -6.250 0.3240 0.02780 0.02014 -0.1720 0.4505 0.0558 -6.000 0.3426 0.02756 0.01994 -0.1705 0.4502 0.0562 -5.750 0.3629 0.02742 0.01984 -0.1695 0.4498 0.0566 -5.500 0.3850 0.02731 0.01976 -0.1688 0.4493 0.0571 -5.250 0.4075 0.02721 0.01968 -0.1682 0.4487 0.0577 -5.000 0.4311 0.02714 0.01962 -0.1679 0.4482 0.0584 -4.750 0.4550 0.02707 0.01956 -0.1676 0.4476 0.0591 -4.500 0.4788 0.02707 0.01956 -0.1673 0.4472 0.0598 -4.250 0.5028 0.02709 0.01959 -0.1670 0.4468 0.0604 -4.000 0.5275 0.02714 0.01964 -0.1669 0.4463 0.0609 -3.750 0.5530 0.02723 0.01973 -0.1670 0.4459 0.0614 -3.500 0.5788 0.02716 0.01970 -0.1673 0.4455 0.0623 -3.250 0.6067 0.02722 0.01980 -0.1680 0.4451 0.0633 -3.000 0.6350 0.02738 0.01999 -0.1687 0.4446 0.0644 -2.750 0.6636 0.02764 0.02026 -0.1695 0.4441 0.0657 -2.500 0.6920 0.02801 0.02065 -0.1703 0.4436 0.0670 -2.250 0.7192 0.02864 0.02129 -0.1711 0.4429 0.0685 -2.000 0.7193 0.03124 0.02406 -0.1683 0.4409 0.0697 -1.750 0.7479 0.03109 0.02397 -0.1691 0.4405 0.0721 -1.500 0.7730 0.03120 0.02411 -0.1692 0.4401 0.0748 -1.250 0.7992 0.03142 0.02443 -0.1699 0.4396 0.0795 -1.000 0.8229 0.03176 0.02486 -0.1701 0.4390 0.0865 -0.750 0.8455 0.03222 0.02548 -0.1705 0.4382 0.1046 -0.500 0.8855 0.03259 0.02636 -0.1750 0.4373 0.2168 -0.250 0.9179 0.03338 0.02754 -0.1780 0.4362 0.3140 0.000 0.9801 0.03418 0.02905 -0.1870 0.4350 0.5126 0.250 0.9754 0.03585 0.03095 -0.1833 0.4336 0.5548 0.500 0.9549 0.03813 0.03339 -0.1780 0.4319 0.5695 0.750 0.9350 0.04063 0.03601 -0.1734 0.4302 0.5812 1.000 0.9277 0.04273 0.03819 -0.1706 0.4289 0.5930 1.250 0.9357 0.04417 0.03964 -0.1694 0.4280 0.6073 1.500 0.9503 0.04504 0.04053 -0.1684 0.4274 0.6179 1.750 0.9665 0.04591 0.04137 -0.1677 0.4268 0.6278 2.000 0.9835 0.04670 0.04215 -0.1670 0.4262 0.6362 2.250 0.9946 0.04758 0.04305 -0.1653 0.4255 0.6441 2.500 1.0051 0.04892 0.04438 -0.1640 0.4248 0.6523 2.750 0.6505 0.09257 0.08859 -0.1639 0.3925 0.5862 3.000 0.6808 0.09229 0.08830 -0.1635 0.3930 0.6118 3.250 0.7090 0.09207 0.08808 -0.1628 0.3934 0.6264 3.750 0.6252 0.10804 0.10423 -0.1634 0.3758 0.6223 4.000 0.6910 0.10317 0.09926 -0.1625 0.3816 0.6410 4.250 0.7119 0.10352 0.09959 -0.1617 0.3813 0.6504 4.500 0.7341 0.10377 0.09981 -0.1611 0.3809 0.6599 4.750 0.7482 0.10413 0.10021 -0.1591 0.3805 0.6677 5.000 0.7029 0.11300 0.10916 -0.1602 0.3696 0.6656