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Aerothermoelasticity of 2D shell with Finite Volume and Gallerkin Method
Hamid Moosazadeh
1Behzad Ghadiri Dehkordi
2*Masud Rasekh
1- Department of Aerospace Engineering, TarbiatModares University, Tehran, Iran 2- Department of Aerospace Engineering, TarbiatModares University, Tehran, Iran 3- Department of Mechanical Engineering, Tafresh University, Tafresh, Iran
*P.O.B. 14115-143 Tehran, Iran, [email protected]
A RTICLE I NFORMATION A BSTRACT
Original Research Paper Received 19 March 2015 Accepted 14 May 2015 Available Online 04 July 2015
The panel flutter is concentrated with aerospace researchers because of fatigue failure on structures. The usage of the numerical simulation is in good company with analytical method. The 2D cylindrical panel flutter is simulated with Navier Stokes equations for fluid flow with finite volume theory. Also, simulation is prepared with piston theory for analytical solution of irrotational fluid. Comparison of full numerical finite volume and assumed mode method in post flutter domain is produced. Non-linear shell with the effect of in-plane load, thermal load and aerodynamic load with 3rd order piston theory is modeled to solve with assumed mode method.
The effect of camber in flutter and post flutter is investigated with both methods. Pressure distribution is defined numerically and analytically for viscid and inviscid flow. The effect of expansion waves decreased the pressure of the second half of shell in analytical method compared to numerical. The principle of Hamilton is used and virtual work, virtual potential energy and virtual kinetic energy are developed. The 4th order Runge-Kutta method is used to solve nonlinear ODEs numerically. The most important output depends on similar result for flat plate and different result on curved plate with numerical and analytical solution.
Keywords:
Shell flutter Viscose flow Finite element Finite volume gallerkin
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