Experimental Flutter Analysis of Wing in Pitch and Plunge Mode

Flutter is one of the most violent instability that the wing and tails of aircraft can exhibit in the cross flow. Coupled mode flutter of aircraft wing can be easily modeled using the two-mode approximation of the kinematics and steady flow approximation for the aerodynamic forces. In this s

Project Title

Experimental Flutter Analysis of Wing in Pitch and Plunge Mode

Project Area of Specialization

Cloud Infrastructure,

Project Summary

Flutter is one of the most violent instability that the wing and tails of aircraft can exhibit in the cross flow. Coupled mode flutter of aircraft wing can be easily modeled using the two-mode approximation of the kinematics and steady flow approximation for the aerodynamic forces. In this study, the development of flutter mechanism in the low speed wind tunnel to evaluate the flutter velocity and to study the aeroelastic responses is described. Two-dimensional flutter analysis is performed on the wing of the MALE UAV. The wing is elastically supported in pitch and plunge mode in the test section of the wind tunnel. The experimental set up is designed such that it can accommodate maximum variation in all the  parameters. The flutter response of the wing is observed experimentally using strain gauges and sensors. The experimental model is based on the two – dimensional mathematical model. First mode bending and torsional stiffness are evaluated using ANSYS. These stiffnesses are modeled on the wind tunnel using experimental flutter mechanism to exhibit flutter on a low speed. The multiparameter experimental study has been done using NACA 2415 and NACA 4415. The study shows that the experimental mechanism is reliable set up to perform the aeroelastic studies on the wind tunnel. The flutter speed or critical speed is observed after initial disturbances. Later, it was observed the critical velocity of the MALE UAV wings is far out of the flight envelope.

Project Objectives

1. To design flexible flutter mount system for the subsonic open circuit wind tunnel.

2. To find the flutter speed of Medium Altitude Long Endurance (MALE) Unmanned Aerial Vehicle (UAV)  through experimental model.

Project Implementation Method

1. Understanding the project

2. literature Review

3. Study design concepts

4. CAD Model

5. Design Modification/improvements

6. Analysis of modified design/improvement

7. Prototype  fabrication

8. Experimental Analysis

Benefits of the Project

1. Design and Fabrication of the flutter analysis system.

2. Experimental setup for analysis.

3. Evaluation of flutter Velocity of Medium Altitude Long Endurance (MALE) Unmanned Aerial Vehicle (UAV) wing in Wind tunnel using developed experimental setup.

Technical Details of Final Deliverable

Technical Details

1. This experimetal system can be used for any type of flutter analysis test.
2. This experimental system will be mounted on the wind tunnel.
3. Evaluation of flutter speed of any aircraft can be performed through this setup.

Resources Required:

1. Sensors
2. Fabrication Facility
3. DAQ System
4. 3D printer
5. Wind tunnel
6. Computational Power

Final Deliverable of the Project

HW/SW integrated system

Type of Industry

Manufacturing , Others

Technologies

Cloud Infrastructure

Sustainable Development Goals

Quality Education

Required Resources

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