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Computational Aerodynamics Applications in Aerospace Engineering João Luiz F. Azevedo Instituto de Aeronáutica e Espaço São José dos Campos, SP, Brazil FAPESP Week 2016 – University of Michigan

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Page 1: Computational Aerodynamics Applications in Aerospace ... · Computational Aerodynamics Applications in Aerospace ... Open-source C++ fluid dynamics ... around reentry vehicles; •

Computational

Aerodynamics Applications in Aerospace Engineering

João Luiz F. AzevedoInstituto de Aeronáutica e Espaço

São José dos Campos, SP, Brazil

FAPESP Week 2016 – University of Michigan

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CONTRIBUTIONS

• William Roberto Wolf

• Edson Basso

• Ricardo Galdino da Silva

• Sami Yamouni

• Carlos Alberto Junqueira Branco Jr.

• Rodrigo C. Palharini

• Carlos Breviglieri Jr.

• Fábio Mallaco Moreira

• Luiz Augusto C. A. Schiavo

• Antonio Batista de Jesus

• Bruno Backes

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OUTLINE

• Background information

• Location

• DCTA and its Institutes

• CFD laboratory

• Research interests

• Some representative results of our current work

• Concluding remarks

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São José dos Campos

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Dutra

Carvalho Pinto

Tamoios

DCTA and its Institutes

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INPE

Embraer

DCTA and its Institutes

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A BIT OF HISTORY

• CTA (currently DCTA) was created together ITA in the late

40’s by (then) Col. Casimiro Montenegro Filho

• Instituto Tecnológico de Aeronáutica (ITA) is probably the

most well-known institute in our center.

• DCTA is an organization of the Brazilian Air Force Command

• Our responsibility is to do research and to develop technology

relevant for aerospace applications

• In particular case of IAE, the work is focused on systems

which are to be fielded right now or in the near future

• In this context, our group’s work is directed towards CFD

applications and developments relevant to DCTA.

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CFD Laboratory

• Researchers and/

or professors (5)

• Post-doctoral

researchers (3)

• PhD students (5)

• MS students (16)

• Undergraduate

students (4)

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AREAS OF RESEARCH INTEREST

• Code Development and Verification-Validation

• Applied CFD and Turbulence Modeling

• LES and Aeroacoustics

• Aeroelasticity and Fluid-Structure Interaction

• High-Order CFD Methods

• High-Speed Flows (Hypersonics)

• Aerodynamic Optimization

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CODE DEVELOPMENT

Development of in-house software

BRU3D, v2.xx

Reynolds-averaged Navier-Stokes (RANS) formulation

Several turbulence models available (SA, low Reynolds Wilcox 𝜅-𝜔,

realizable 𝜅-𝜀, SST, modified Craft-Launder RSM, stressBSL EARSM,

Wallin-Johansson EARSM)

Finite Volume Method (FVM), cell centered, general unstructured grids

Spatial discretization: centered scheme (+ artificial dissipation) and Roe

scheme

Temporal discretization: explicit Runge-Kutta schemes + point implicit

solver

Convergence acceleration for steady state: local time stepping +

agglomeration multigrid

Parallel code (MPI + OpenMP)

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CODE DEVELOPMENT

Development of in-house software

BRU3D, v3.0

C++, templates, CGNS, parallel I/O

General unstructured grids

High-order spatial discretization

MPI + OpenMP + CUDA

JAZzY, v1.0

Parallel compressible LES code (with MPI)

Structured meshes, CGNS+HDF5, parallel I/O

Standard and dynamic Smagorinsky sub-grid scale models

dsmcFOAM

Open-source C++ fluid dynamics toolbox OpenFOAM

Ballistic particle tracking

Probabilistic collisions

Quantum-kinetic chemistry model

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APPLIED CFD

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APPLIED CFDRANS solutions used to improve the understanding of stall behavior.

Fence effect at Re = 3 X 106 , M = 0.25 and AoA = 15 deg

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APPLIED CFDRANS solutions used to improve the understanding of stall behavior.

Interaction between vortical structures and boundary layer.

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APPLIED CFD

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APPLIED CFD

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HYPERSONIC FLOWSNumerical Investigation of Hypersonic Vehicles under

Thermochemical Non-Equilibrium Conditions

The project includes the

development of a space

platform for experiments in

microgravity, called Satélite

de Reentrada Atmosférica

(SARA)

• Low circular orbit (300

km), 10 days max

• Reentry Simulation: 95 km

altitude, Mach 28, vel.

28,000 km/h

• Suborbital SARA vehicle,

350 kg, launched through

modified VS-40 sounding

rocket

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HYPERSONIC FLOWS

Suborbital SARA Vehicle

• Reentry condition – 95 km, 28,000 km/h, Mach 28;

• Reactive flow (QK) vs Non-reactive flow (NR) – DSMC technique;

• “Quantum Kinetic” reaction model – 5 species and 19 reactions (dissociation andexchange reactions);

• Overprediction of shock wave temperature and heat transfer.

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HYPERSONIC FLOWSImplementation of ionization reactions

(reaction rates: dsmcFoam vs analytical solution)

Applications:

• - Plasma formation around reentry vehicles;

• - Development and design of reliable thermal protection systems;

• - Radio signal blackout;

• - Plasma propulsion systems for satellite altitude control.

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HIGH-ORDER METHODS

Spectral Difference Method

Development of High-Order Code

• Expectation of reduction in the man-hours required to achieve solution

• Compressible flows

• Work is mostly directed towards method development

• However, there are other issues which need effort

• High-order geometry representation and grid generation

• High-order visualization

• Robust solvers

• Robust discontinuity capturing method

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HIGH-ORDER METHODS

Ringleb Flow Problem

High-order geometryrepresentation

Entropy error = 3.88 X 10-4 Close to ideal spatial convergence rate6th-order formulation

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HIGH-ORDER METHODS

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HIGH-ORDER METHODS

M = 3, transient computation until t = 4.0

2nd order method on an unstructured grid of approximately 17,000 quadrilaterals

Robustness to deal with strong shocks

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HIGH-ORDER METHODS

Mach = 2 flow over a wedge

2nd-order 3rd-order 4th-order

Limiting process extendable to higher-order formulations

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LES and AEROACOUSTICSLarge Eddy Simulation and Aeroacoustics of Perfectly Expanded

Supersonic Jets

DEVELOPMENT OF A COMPRESSIBLE LES SOLVER

Upgrade of a serial RANS solver to a parallel compressible LES solver.

Perfectly expanded supersonic jet configurations.

NOISE PREDICTION AND PROPAGATION

Development of physics-based noise predictiontools for analysis ofaerodynamic noise sources.

Fast multipole method(FMM) + boundary elementmethod (BEM) for acousticscattering.

Fast multiple method(FMM) + Ffowcs Williamsand Hawkings (FWH) forsound propagation.

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LES and AEROACOUSTICS

15 million mesh points: 150 days on CESUP (200 cores)40 days on CEPID (1000 cores)

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LES and AEROACOUSTICS

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AIRFOIL NOISE

Airfoil Immersed in a Wake Vortex

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TURBULENT FLOW

Lambda Shock Formation• All turbulence models (SA, SST and BSL-EARSM) were able to predict a lambda

shock formation over the ONERA M6 wing upper surface

• Numerical results predict the shock merging location more inboard than

experimental data

Flight conditions:

M = 0.84

AoA = 3.06 deg.

Re = 11.72 mi

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Mesh Generation

Surface mesh according to each mesh refinement level.

Coarse mesh Baseline mesh

Fine mesh

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Mesh Generation

Cut sections of the volumetric mesh located at the wing

midspan position

Coarse mesh Baseline mesh

Fine mesh

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Wing Tip Vortex Visualization

Coarse Mesh

SA SST BSL-EARSM

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Wing Tip Vortex Visualization

Baseline Mesh

SA SST BSL-EARSM

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Wing Tip Vortex Visualization

Fine Mesh

SA SST BSL-EARSM

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Wing Tip Vortex Visualization

SA Turbulence Model

Coarse Mesh Baseline Mesh Fine Mesh

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Wing Tip Vortex Visualization

SST Turbulence Model

Coarse Mesh Baseline Mesh Fine Mesh

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Wing Tip Vortex Visualization

BSL-EARSM Turbulence Model

Coarse Mesh Baseline Mesh Fine Mesh

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TURBULENT FLOW

Effects of Adverse Pressure Gradients

● Flow in a converging-

diverging channel.

●New physical mechanism

observed in APG regions

● Separation and reattachment

points studied

● Streak instability (or streak

bursting)

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TURBULENT FLOW

Effects of Adverse Pressure Gradients

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TURBULENT FLOW

Effects of Adverse Pressure Gradients

(need for reduced order models due to size of files involved)

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CONCLUDING REMARKS

• I hope that this brief overview of part of our work was able to

give some idea of the research/development performed.

• Recently, areas of turbulence modeling, either RANS or LES

formulations, and high-order methods have been the most

active ones.

• A great deal of the work here described is performed under a

FAPESP RIDC project (center): CeMEAI (Center for Industrial

Mathematics Applications).

• The availability of the computational resources at the CeMEAI

RIDC is absolutely essential for our work.

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THANK YOU