22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-1.6.1

WING DESIGN OF AN OBLIQUE WING COMBAT AIRCRAFT

R. K. Nangia (1), D. I. Greenwell (2)
(1) Nangia Aero Research Associates, UK; (2) Defence Evaluation Research Agency, UK

Keywords: design,oblique wing, combat aircraft

The Oblique Wing (OW) concept is a proposition for meeting rigourous aerodynamic performance goals to Mach about 1.7 over a wide flight envelope up to 40,000 ft. With appropriate wing sweep, high efficiencies can be obtained at low speed. The handling, stability and control issues remain a strong design challenge to ensure adequate stability in pitch, yaw and roll. This has led to a work programme with the objective of assessing the suitability of such concepts for manned and UAV combat aircraft applications. The military application has a wide operating flight envelope under stealth constraints (30° raked wing-tips). Several types of flows from the planform edges flows interact in different ways as the wing sweep and Mach combinations alter. After a brief description of flow features, this paper addresses the design case for transonic cruise at low altitudes. This has emphasised control over LE suctions as desired within the neutral point and CG constraints.

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