EFFECT OF WING FLEXIBILITY ON THE EXPERIMENTAL AERODYNAMIC CHARACTERISTICS OF AN OBLIQUE WING

摘要

A solid-aluminum oblique wing was designed to deflect considerably under load so as to relieve the asymmetric spanwise stalling that is characteristic of this type of wing by creating washout on the trailing wing panel and washin on the leading wing panel Experimental forces, and pitching, rolling and yawing moments were measured with the wing mounted on a body of revolution In order to vary the dynamic pressure, measurements were made at several unit Reynolds numbers ranging from 3 3X106/m to 8 2X106/m, and at Mach numbers ranging from 0 25 to 2 0 The wing was investigated when unswept (at subsonic Mach numbers only) and when swept 45°, 50°, 55°, and 60° The wing was straight tapered in planform, had an aspect ratio of 7 9 (based on the unswept span) and a profile with a maximum thickness of 4 percent chordnFor the design Mach number of 0 95 and the design dynamic pressure of 15X103 N/m2, the pitching-and rolling-moment curves were considerably more linear than at a dynamic pressure of about half the design value This result substantiates the concept that an oblique wing designed with the proper amount of flexibility can "self relieve" itself of asymmetric spanwise stalling and the associated nonlinear moment curves.