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Application of nastran to large deflection supersonic flutter of panels
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Rogers Jr., J. L. Mei, C. |
| Copyright Year | 1976 |
| Description | Flat panel flutter at high supersonic Mach number is analyzed using NASTRAN Level 16.0 by means of modifications to the code. Two-dimensional plate theory and quasi-steady aerodynamic theory are employed. The finite element formulation and solution procedure are presented. Modifications to the NASTRAN code are discussed. Convergence characteristics of the iteration processes are also briefly discussed. Effects of aerodynamic damping, boundary support condition and applied in-plane loading are included. Comparison of nonlinear vibration and linear flutter results with analytical solutions demonstrate that excellent accuracy is obtained with NASTRAN. |
| File Size | 833825 |
| Page Count | 31 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770013546 |
| Archival Resource Key | ark:/13960/t9z07x76t |
| Language | English |
| Publisher Date | 1976-10-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Finite Element Method Panel Flutter Flat Plates Supersonic Flutter Nastran Aerodynamic Characteristics Mach Number Convergence Structural Analysis Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |