Dynamic wind tunnel testing of a flexible wing model 13; 13;

Rajamurthy, MS and Balakrishna, S (1990) Dynamic wind tunnel testing of a flexible wing model 13; 13;. Technical Report. National Aeronautical Laboratory, Bangalore, India.

[img] PDF
Restricted to Repository staff only

Download (10MB)
[img] Indexer Terms (Generate index codes conversion from application/pdf to indexcodes)
Restricted to Repository staff only

Download (5kB)


The current state-of-art in the design of modern combat aircraft is to use CCV concepts to obtain high performance at lower weight. This demands an unstable aerodynamic configuration with the stability provided artificially by the control system. This needs longitudinal servo-actuators of high bandwidth. With lower structural frequencies there is scope for interaction and aeroservoelastic problems could occur. This document details a simple experimental study13; of servoelastically exciting a wing to yield transfer function data. The aim of these experiments is to provide a vehicle for generating experimental data for validating aeroservoelastic codes and to obtain insight of flutter I aeroservoelastic phenomena through scaled models.13;

Item Type: Monograph (Technical Report)
Uncontrolled Keywords: Dynamic wind tunnel testing;Flexible wing;Transfer functions;Aeroservoelasticity
Subjects: AERONAUTICS > Aerodynamics
Depositing User: Mrs Manoranjitha M D
Date Deposited: 24 Jul 2006
Last Modified: 24 May 2010 04:16
URI: http://nal-ir.nal.res.in/id/eprint/2250

Actions (login required)

View Item View Item