The Effect of a Splitter Plate on the Symmetry of Separated Flow Around a Delta Wing of Low Aspect Ratio (Vliyanie Razdelitel'Noi Plastiny Na Simmetrichnost' Otryvnogo Obtekaniya Treugol'Nogo Kryla Malogo Udlineniya)
Abstract
Using the approximation of the theory of slender bodies an investigation is made into the non-uniqueness of solutions for separated flow around a delta wing of low aspect ratio in the presence of a delta splitter plate on the upper surface of the wing and in the plane of symmetry. An improved method of formulation offers increased accuracy, when applied to the solution of similarity problems in vortex sheets. Some substantially asymmetrical solutions to the problem of separated flow around the wing under symmetrical conditions of flow are obtained, as well as some symmetrical ones. Considerable attention is paid to an explanation of the nature of the bifurcations in solutions and to a qualitative description of hysteresis in the aerodynamic characteristics as a result of a quasistationary change in angle of attack and yaw angle by the use of a simplified mathematical model of a vortex sheet 'vortex and cut'.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1990
- Accession Number
- ADA230795
Entities
People
- S. B. Zakharov
Organizations
- Royal Aircraft Establishment