Application of Forced Unsteady Aerodynamics to a Forward Swept Wing X-29 Model
Abstract
Numerous studies have hinted at possible use of controlled unsteady separated flows for lift enhancement on maneuvering aircraft. To verify these hypotheses and demonstrate application potential, an experimental study of forced unsteady flow fields about a 1/10 scale, reflection-plane model of the X- 29 aircraft was conducted. Orthogonal view flow visualization was conducted with model angle of attack between zero and ten degrees and the canard angle of attack with respect to the model centerline between plus and minus 40 degrees. Static tests exhibit canard and wing stall characteristics and the upwash and downwash flow patterns. The dynamic (oscillating canard) tests demonstrate reduction of canard stall tendencies and decreased effective angles of attack at the wing root. Also, three-dimensional dynamic interactions were observed between the canard-generated leading edge vortices and the unsteady canard tip vortices. These complex flows convect downstream and impinge upon the wing. The interactions appear reproducible and controllable. Keywords: Flow visualization; Sweptforward wings; Angle of attack; Canard configurations; Wind tunnel models; Vortices; Dynamic tests.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 11, 1988
- Accession Number
- ADA228100
Entities
People
- J. Ashworth
- M. Luttges
- T. Mouch
Organizations
- United States Air Force Academy