Static Aeroelastic Response of an Aircraft With Asymmetric Wing Planforms Representative of Combat Damage
Abstract
This report describes an analysis of the static aeroelastic response of an aircraft with asymmetrical wing planforms representing combat damage. The analysis was performed using the MSC/NASTRAN Aeroelastic Code. Structural and aerodynamic models are based on the finite element approach and are created independently for both the damaged and undamaged cases. Fuselage, wings (with aileron), stabilators, an vertical wings (with rudders) are considered as lifting and control surfaces in the aerodynamic model. Five different wings structural models, one undamaged and four damaged, are examined in this report. Doublet-Lattice subsonic theory is used to account for interference effects among multiple lifting surfaces and bodies. The stability and control derivatives, airloads, and trim values are obtained for the damaged-wing aircraft. Effects of damage, including the influence of wing-body interference, on the aircraft's flight dynamics are discussed.... T-38 Aircraft, Aerodynamic model, Control and stability derivatives, MSC/NASTRAN, Aeroelasticity, Damage wing, Control surfaces
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1993
- Accession Number
- ADA266890
Entities
People
- Jong-ho Woo
Organizations
- United States Army Research Laboratory