WING DESIGN OF AN OBLIQUE WING COMBAT AIRCRAFT

摘要

The Oblique Wing (OW) concept is arnproposition for meeting rigourous aerodynamicrnperformance goals to Mach about 1.7 over arnwide flight envelope up to 40,000 ft. Withrnappropriate wing sweep, high efficiencies canrnbe obtained at low speed. The handling, stabilityrnand control issues remain a strong designrnchallenge to ensure adequate stability in pitch,rnyaw and roll. This has led to a work programmernwith the objective of assessing the suitability ofrnsuch concepts for manned and UAV combatrnaircraft applications.rnThe military application has a widernoperating flight envelope under stealthrnconstraints (30° raked wing-tips). Several typesrnof flows from the planform edges flows interactrnin different ways as the wing sweep and Machrncombinations alter.rnAfter a brief description of flow features,rnthis paper addresses the design case forrntransonic cruise at low altitudes. This hasrnemphasised control over LE suctions as desiredrnwithin the neutral point and CG constraints.We have addressed a major off-designrnimplications e.g. low speed flight with a novelrn"one-piece" TE that is torsionally flexible.rnCalculations show that the high-speedrnsupersonic dash will require an amount ofrn"uncambering" with the flexible TE envisaged.rnSeveral avenues for further work havernarisen.