Analysis of the Static and Dynamic Response of a T-38 Wing and Comparison With Experimental Data
Abstract
This report documents the investigation of a three-dimensional finite element model for calculating the static displacement and dynamic structural response of a T-38 wing and comparison of the analytical results with T-38 wing experimental data from Northrop Aircraft, Inc. The wing structure is modeled by rod and bar (beam), quadrilateral plate, triangular plate, and shear panel finite elements. The general structural analysis programs MSC/NASTRAN and MSC/ PAL2 are used to calculate deflections, natural frequencies, and mode shapes. The wing finite element model yielded excellent agreement between calculated and experimental results for the eight loading conditions studied. The methodology developed in this study is expected to provide a valuable tool for the static aeroelastic response and dynamic analysis of wing structures in conjunction with aircraft ballistic vulnerability assessments.... T-38 Wing, Deflection, Natural frequency, Finite element methods, Shear panel, MSC/NASTRAN; MSC/PAL 2, Resonant frequency.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1993
- Accession Number
- ADA262363
Entities
People
- Jong-ho Woo
Organizations
- United States Army Research Laboratory