Measurements of Maximum Lift on 26 Aerofoil Sections at High Mach Number Part I. Tests on 19 Aerofoils Part II. Tests on a Further 7 Aerofoils

摘要

There is some evidence that the low Reynolds number of the tests is not important and that the following general conclusions may be held to apply to the full-scale aeroplane.n(1) In almost every case, at Mach numbers above about 0-75 the lift vs. incidence curve comes to no definite maximum but is still rising at the limiting incidence of test (about' 15 deg), though the rate of rise is much less above a certain incidence.nIn the following conclusions, (2) to (5), the ' maximum lift' at a given Mach number is defined by the first peak on the CL/a. curve, but for the higher Mach numbers where there is no maximum a dotted extension of the curves of CLmaX against M shows the lift at approximately the same incidence as that at which the last maximum was measured.n(2) For Mach numbers greater than 0-6, thin aerofoils have greater maximum lift than thick ones, whether symmetrical or cambered, of conventional or of low-drag design.