Investigation into Active Spanwise Camber Deformation on the Lateral Stability and Roll Control of the X-56A Compared to Conventional Ailerons
Abstract
This research compares the stability and roll characteristics of an X-56A using AFRLs Variable Camber Complaint wing technology to actively change wing camber compared to conventional ailerons deflected at set angles. An analysis of the stability and roll characteristics was modeled using a 3-D vortex lattice theory simulation, and that data was compared to wind tunnel testing to verify and validate the model results. Wind tunnel data was collected using 19 inch 3-D printed scale models with wings fabricated with a pre-determined percentage of camber deformation, as well as models with fixed aileron deflections. Wind tunnel testing was performed at a Reynolds number range from 30,000 to 150,000. Testing indicated at high speeds and low angles of attack, the camber deformed wings produced a roll moment and roll rate equivalent to, or greater than conventional ailerons. Because of early onset stall, the camber deformed wing had a lower lift coefficient with increased drag. The camber deformed models did not result in aerodynamic moment instability; however, they did demonstrate a decrease in roll and pitch stability. The 3-D model predicted accurate trends in roll and stability, but could not model viscous effects due to the inviscid nature of the simulation.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 2016
- Accession Number
- AD1054206
Entities
People
- Eric T. Yerly
Organizations
- Air Force Institute of Technology