NASA Technical Reports Server (NTRS) 20030064926: A Conceptual Wing Flutter Analysis Tool for Systems Analysis and Parametric Design StudyReportar como inadecuado




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An interactive computer program was developed for wing flutter analysis in the conceptual design stage. The objective was to estimate flutt er instability boundaries of a typical wing, when detailed structural and aerodynamic data are not available. Effects of change in key flu tter parameters can also be estimated in order to guide the conceptual

Autor: NASA Technical Reports Server (NTRS)

Fuente: https://archive.org/


Introducción



A CONCEPTUAL WING FLUTTER ANALYSIS TOOL FOR SYSTEMS ANALYSIS AND PARAMETRIC DESIGN STUDY Vivek Mukhopadhyay NASA Langley Research Center, Hampton, VA 23681, USA e-mail: v.mukhopadhyay@larc.nasa.gov Key words: Conceptual Flutter analysis, wing design parameters, Regier number, flutter number, bending, torsion, frequency, blended wing body. Abstract: An interactive computer program was developed for wing flutter analysis in the conceptual design stage.
The objective was to estimate flutter instability boundaries of a typical wing, when detailed structural and aerodynamic data are not available.
Effects of change in key flutter parameters can also be estimated in order to guide the conceptual design.
This userfriendly software was developed using MathCad and Matlab codes.
The analysis method was based on non-dimensional parametric plots of two primary flutter parameters, namely Regier number and Flutter number, with normalization factors based on wing torsion stiffness, sweep, mass ratio, taper ratio, aspect ratio, center of gravity location and pitch-inertia radius of gyration. These parametric plots were compiled in a Chance-Vought Corporation report from database of past experiments and wind tunnel test results.
An example was presented for conceptual flutter analysis of outer-wing of a Blended-Wing-Body aircraft. 1 INTRODUCTION During conceptual design of a wing, it is often necessary to obtain initial estimates of the wing or tail flutter boundary, when only the basic plan-form is known, and much of the structural data, frequency, mass and inertia properties are yet to be established.
It is also very useful to conduct a parametric study to determine the effect of change in Mach number, dynamic pressure, torsion frequency, wing sweep-back angle, mass ratio, aspect ratio, taper ratio, center of gravity, and pitch moment of inertia, on the flutter boundary.
For this purpose, an interactive computer program was developed using MathCad1 and Matlab application software...






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