Io-ft x 7-ft Tunnel Tests up to M = 0.94 of Nose Droop and a Blunt-Nosed NACA 3-00nType Section on a 7 1/2 per cent Thick 50 deg Swept Wing

摘要

This note describes further tests made during 1954 in the Royal Aircraft Establishment 10 ft x 7 ft High Speed Tunnel, as part of a research programme to improve the subsonic longitudinal stability characteristics of a 50 deg swept wing of aspect ratio 3 .1 by means such as nose-droop, chord extensions, fences, change of aerofoil section, etc.nLift, drag, pitching-moment and root bending moment were measured with the basic7 1/2 per cent thick RAE 101 section, with a symmetrical blunt-nosed NACA 3-007-5 section, and with a full-span drooped and thickened nose, at Mach numbers up to 0-94 and Reynolds numbers between 1.7 x 106 and 6 x 106.