Numerical simulation of maneuvering combat aircraft

Size: px
Start display at page:

Download "Numerical simulation of maneuvering combat aircraft"

Transcription

1 Numerical simulation of maneuvering combat aircraft Andreas Schütte DLR - German Aerospace Center Institute of Aerodynamics and Flow Technology Oct. 14 th 2005, Stuttgart Folie 1 > HLRS 2005 > A. Schütte

2 Numerical simulation of maneuvering combat aircraft Gunnar Einarsson, Britta Schöning, Axel Raichle, Wulf Mönnich, Thomas Alrutz, Jens Neumann, Jörg Heinecke DLR - German Aerospace Center Institute of Aerodynamics and Flow Technology Oct. 14 th 2005, Stuttgart Folie 2 > HLRS 2005 > A. Schütte

3 Overview Motivation Objectives Simulation Environment Experimental Simulation Numerical Results HPC Requirements and Resources Summary and Outlook Folie 3 > HLRS 2005 > A. Schütte

4 HPC Requirements Institut of Aerodynamics and Flow Technology Braunschweig /Göttingen Folie 4 > HLRS 2005 > A. Schütte

5 Motivation Source: Cenaero Folie 5 > HLRS 2005 > A. Schütte

6 Objectives of the DLR Project SikMa Prediction of the unsteady behavior of maneuvering aircraft. Development of a numerical simulation environment for calculating maneuvers of a free flying elastic combat aircraft. Realized a by multi disciplinary time-accurate coupling of CFD, Structure Dynamics and Flight Mechanics within the framework TENT. SikMa is a multidisciplinary project were several DLR Institutes are involved: Institute of Aerodynamics and Flow Technology Institute of Aeroelasticity Institute of Flight Systems DLR Sistec Folie 6 > HLRS 2005 > A. Schütte

7 Simulation Environment TENT Codes are implemented in TENT via wrappers. TENT carries out data transfers and communication between codes. TENT can distribute applications over different platforms SimBrowser: Definition of grid hierarchies for CHIMERA grids definition of all movements of parts and grids relative to each other animation and test of movements creation of motion and hierarchy files for the CFD- Code-TAU Folie 7 > HLRS 2005 > A. Schütte

8 DLR TAU-Code CFD-Code solution of RANS equations for arbitrarily moving bodies on unstructured meshes hybrid meshes (hex., prisms, tetra., pyram.) FV using dual grid approach, MG accelerated unsteady via dual time stepping state-of-the-art turbulence models grid adaptation (refinement & derefinement) CHIMERA technique deforming mesh capability designed for massively parallel computers validated for a large number of test cases Folie 8 > HLRS 2005 > A. Schütte

9 DLR TAU-Code Chimera approach Chimera boundary of the flap Chimera boundary of the wing Realized soon: Automatic hole-cutting approach Folie 9 > HLRS 2005 > A. Schütte

10 DLR TAU-Code Mesh adaptation (unsteady calc.) Stream lines & Total pressure distribution History of mesh adaptation Folie 10 > HLRS 2005 > A. Schütte

11 SIMULA Flight mechanics library Simulation environment SIMULA delivers the solutions of the flight mechanics equations Trimming calculation Analyze stability Maneuver simulations with 6 DoF and control devices Coupling of Aerodynamics/Flight mechanics Implicit time integration scheme Close coupling within each pseudo time-step Implemented models for SikMa Rolling delta-wing with trailing-edge flaps Generic 6-DoF model (e.g. X-31) Folie 11 > HLRS 2005 > A. Schütte

12 CSM-Code Structural mechanics simulation Two approaches Discrete approach: Coupling with the overall FE-Model Modal approach: Coupling with characteristic Eigenmodes Characteristics Coupling Aerodynamics/Structure: Loose/weak coupling scheme coupling within each physical time step Solving the CSM-equations: Implicit Newmark integration-scheme Spatial coupling: Scattered data interpolation methods for force and deformation transfer Coupling in time: Conventional Serial Staggered-algorithm with predictor- /corrector step for the CSM calculation Determination of the system matrices: Reduced system matrices MAA and KAA imported from NASTRAN Folie 12 > HLRS 2005 > A. Schütte

13 Experimental Simulation Wind tunnel experiments Objectives Generating a validation data base for the numerical simulation. Knowledge approach of the aerodynamic behavior of configurations with vortex dominated flow fields Configurations 1. Delta-wing-configuration with movable trailing-edge flaps 2. X-31 CFRP and Remote-Control-Model with remote controlled flaps, rudder and canard for maneuver simulations on the Model-Positioning-Mechanism (MPM) at NWB Folie 13 > HLRS 2005 > A. Schütte

14 Experimental Simulation Wind tunnel facilities Transonic Wind Tunnel Göttingen (TWG) Test section 1x1m Mach number range: (with perf. walls) Re = (based on 0.1 s) Low Speed Wind Tunnel Braunschweig (NWB) Test section m Mach number range: (for open test section) Re = 1.8 x 106 (based on 0.1 s) Folie 14 > HLRS 2005 > A. Schütte

15 Experimental Simulation Wind tunnel models Delta-wing-configuration with trailingedge flaps Internal 6-component piezo-balance Piezo-resistive pressure sensors at 60% and 80% chord length Control device velocity up to 300 /s X-31 configuration with remote controlled control devices CFRP fuselage, steel wing and aluminum made control devices 8 internal servo engines for control device movement Internal 6-component strain gauge Pressure sensors for measuring the unsteady pressure distribution at 60% and 70% chord length Internal 64 channel 16 bit telemetric system for data transfer Folie 15 > HLRS 2005 > A. Schütte

16 MPM - Model Positioning Mechanism Maneuver simulation in the wind tunnel Synchronized, dynamic similar movement of model and control devices in comparison to flight tests Parallel kinematics Steward platform connected to electromagnetic linear motors by 6 rods of constant length Folie 16 > HLRS 2005 > A. Schütte

17 Folie 17 > HLRS 2005 > A. Schütte

18 Numerical Results Guided coupled simulation of CFD and CSM Coupled free-to-roll maneuver simulation of CFD, CSM and Flight Mechanics Coupled free-to-roll maneuver of delta-wing-configuration with movable trailing-edge flaps (CFD-FM-Coupling) X-31: first steady calculations Folie 18 > HLRS 2005 > A. Schütte

19 Numerical Results (1) Delta wing guided rolling motion around longitudinal axis CSM-TAU-Coupling FE-Model of delta-wing and rear sting support Folie 19 > HLRS 2005 > A. Schütte

20 Numerical Results (1) Delta wing guided rolling motion around longitudinal axis CSM-TAU-Coupling Folie 20 > HLRS 2005 > A. Schütte

21 Numerical Results (2) Delta wing guided rolling motion around longitudinal axis CSM-TAU-FM-Coupling Folie 21 > HLRS 2005 > A. Schütte

22 Numerical Results (3) Delta wing free-to-roll motion around longitudinal axis TAU-FM-Coupling Ma = 0.5 Re = 3.8Mio Θ = 17 Φ 0 = 0 η = ±5 Folie 22 > HLRS 2005 > A. Schütte

23 Numerical Results (3) Delta wing free-to-roll motion around longitudinal axis TAU-FM-Coupling Folie 23 > HLRS 2005 > A. Schütte

24 Numerical Results (3) Delta wing free-to-roll motion around longitudinal axis TAU-FM-Coupling Flap up Flap down cl OΦ O Folie 24 > HLRS 2005 > A. Schütte

25 Numerical Results (4) Flow simulation around X-31 configuration (clean wing) α=14 α=18 α=22 Folie 25 > HLRS 2005 > A. Schütte

26 Numerical Results (4) Flow topology of X-31 (clean wing) Oil Flow Picture Tau-Calculation Ma=0.12 Re=1.0Mio a=18 separation line attachement line Folie 26 > HLRS 2005 > A. Schütte

27 Numerical Results (4) Flow simulation around X-31 configuration PSP-Measurement: Re = 2.07Mio α =18 TAU-Calculation: Re = 2.07Mio α =18 Folie 27 > HLRS 2005 > A. Schütte

28 HPC Requirements and Resources (1) Calculation times and resources today Folie 28 > HLRS 2005 > A. Schütte

29 HPC Requirements and Resources (2) Requirements on HPC Cluster-Hardware Maneuver Simulation X-31 configuration, movable control devices ~30 Million grid points unsteady simulation with DLR-TAU-Code CFD / CSD / FM Maneuver simulation of 2 seconds real time Aim: 2 weeks Approximation on target platform HWW-Cluster Strider (64 Proc, 64 Bit): 30 Mio. grid points 2 s real time, 2000 physical time steps, 600 inner Iterations ~ 950 h wall clock ~ 40 days on HWW-Cluster Strider (64 Proz) ~ 14 days on Cluster with > 256 Processors Herbstmaneuver: 10 s Folie 29 > HLRS 2005 > A. Schütte

30 Summary Development strategy for the prediction of the behavior of maneuvering aircraft Simulation environment and its elements Experimental simulation for validation data base First results showing the capability of time-accurate coupling of CFD/FM- and CFD/CSD/FM-Coupling First CFD results of the complex flow topology over the X-31 configuration Need for HPC resources were demanded Folie 30 > HLRS 2005 > A. Schütte

TIME-ACCURATE SIMULATION OF THE FLOW AROUND THE COMPLETE BO105 WIND TUNNEL MODEL

TIME-ACCURATE SIMULATION OF THE FLOW AROUND THE COMPLETE BO105 WIND TUNNEL MODEL TIME-ACCURATE SIMULATION OF THE FLOW AROUND THE COMPLETE BO105 WIND TUNNEL MODEL Walid Khier, Thorsten Schwarz, Jochen Raddatz presented by Andreas Schütte DLR, Institute of Aerodynamics and Flow Technology

More information

Current Status and Challenges in CFD at the DLR Institute of Aerodynamics and Flow Technology

Current Status and Challenges in CFD at the DLR Institute of Aerodynamics and Flow Technology Current Status and Challenges in CFD at the DLR Institute of Aerodynamics and Flow Technology N. Kroll, C.-C. Rossow DLR, Institute of Aerodynamics and Flow Technology DLR Institute of Aerodynamics and

More information

CFD Lab Department of Engineering The University of Liverpool

CFD Lab Department of Engineering The University of Liverpool Development of a CFD Method for Aerodynamic Analysis of Large Diameter Horizontal Axis wind turbines S. Gomez-Iradi, G.N. Barakos and X. Munduate 2007 joint meeting of IEA Annex 11 and Annex 20 Risø National

More information

Computational Fluid Dynamics

Computational Fluid Dynamics Aerodynamics Computational Fluid Dynamics Industrial Use of High Fidelity Numerical Simulation of Flow about Aircraft Presented by Dr. Klaus Becker / Aerodynamic Strategies Contents Aerodynamic Vision

More information

Numerical simulation software integration with TENT Software Integration and Workflow Management

Numerical simulation software integration with TENT Software Integration and Workflow Management Numerical simulation software integration with TENT Software Integration and Workflow Management Andreas Schreiber, DLR Simulation and Software Technology Joint ESTEC-DLR Workshop, ESA/ESTEC, Noordwijk,

More information

Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration

Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration 30th AIAA Applied Aerodynamics Conference 25-28 June 2012, New Orleans, Louisiana AIAA 2012-3325 Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration Kerstin C. Huber 1

More information

Aeronautical Testing Service, Inc. 18820 59th DR NE Arlington, WA 98223 USA. CFD and Wind Tunnel Testing: Complimentary Methods for Aircraft Design

Aeronautical Testing Service, Inc. 18820 59th DR NE Arlington, WA 98223 USA. CFD and Wind Tunnel Testing: Complimentary Methods for Aircraft Design Aeronautical Testing Service, Inc. 18820 59th DR NE Arlington, WA 98223 USA CFD and Wind Tunnel Testing: Complimentary Methods for Aircraft Design Background Introduction ATS Company Background New and

More information

Drag Analysis for an Economic Helicopter. S. Schneider, S. Mores, M. Edelmann, A. D'Alascio and D. Schimke

Drag Analysis for an Economic Helicopter. S. Schneider, S. Mores, M. Edelmann, A. D'Alascio and D. Schimke Drag Analysis for an Economic Helicopter S. Schneider, S. Mores, M. Edelmann, A. D'Alascio and D. Schimke Content Numerical Simulation vs. Measurement Wind Tunnel Setup Numerical Simulation Setup Discussion

More information

Numerical Approach Aspects for the Investigation of the Longitudinal Static Stability of a Transport Aircraft with Circulation Control

Numerical Approach Aspects for the Investigation of the Longitudinal Static Stability of a Transport Aircraft with Circulation Control Numerical Approach Aspects for the Investigation of the Longitudinal Static Stability of a Transport Aircraft with Circulation Control Dennis Keller Abstract The aim of the investigation is to gain more

More information

CFD Based Reduced Order Models for T-tail flutter

CFD Based Reduced Order Models for T-tail flutter CFD Based Reduced Order Models for T-tail flutter A. Attorni, L. Cavagna, G. Quaranta Dipartimento di Ingegneria Aerospaziale Outline NAEMO-CFD software Test bench: Piaggio Avanti P180 T-Tail flutter problem

More information

Programme Discussions Wissenschaftstag Braunschweig 2015 Laminarität für zukünftige Verkehrsflugzeuge

Programme Discussions Wissenschaftstag Braunschweig 2015 Laminarität für zukünftige Verkehrsflugzeuge Programme Discussions Wissenschaftstag Braunschweig 2015 Kevin Nicholls, EIVW Prepared by Heinz Hansen TOP-LDA Leader, ETEA Presented by Bernhard Schlipf, ESCRWG Laminarität für zukünftige Verkehrsflugzeuge

More information

PyFR: Bringing Next Generation Computational Fluid Dynamics to GPU Platforms

PyFR: Bringing Next Generation Computational Fluid Dynamics to GPU Platforms PyFR: Bringing Next Generation Computational Fluid Dynamics to GPU Platforms P. E. Vincent! Department of Aeronautics Imperial College London! 25 th March 2014 Overview Motivation Flux Reconstruction Many-Core

More information

Computational Aerodynamic Analysis on Store Separation from Aircraft using Pylon

Computational Aerodynamic Analysis on Store Separation from Aircraft using Pylon International Journal of Engineering Science Invention (IJESI) ISSN (Online): 2319 6734, ISSN (Print): 2319 6726 www.ijesi.org ǁ PP.27-31 Computational Aerodynamic Analysis on Store Separation from Aircraft

More information

Aerodynamic Department Institute of Aviation. Adam Dziubiński CFD group FLUENT

Aerodynamic Department Institute of Aviation. Adam Dziubiński CFD group FLUENT Adam Dziubiński CFD group IoA FLUENT Content Fluent CFD software 1. Short description of main features of Fluent 2. Examples of usage in CESAR Analysis of flow around an airfoil with a flap: VZLU + ILL4xx

More information

A. Hyll and V. Horák * Department of Mechanical Engineering, Faculty of Military Technology, University of Defence, Brno, Czech Republic

A. Hyll and V. Horák * Department of Mechanical Engineering, Faculty of Military Technology, University of Defence, Brno, Czech Republic AiMT Advances in Military Technology Vol. 8, No. 1, June 2013 Aerodynamic Characteristics of Multi-Element Iced Airfoil CFD Simulation A. Hyll and V. Horák * Department of Mechanical Engineering, Faculty

More information

Coupled CFD and Vortex Methods for Modelling Hydro- and Aerodynamics of Tidal Current Turbines and On- and Offshore Wind Turbines

Coupled CFD and Vortex Methods for Modelling Hydro- and Aerodynamics of Tidal Current Turbines and On- and Offshore Wind Turbines Coupled CFD and Vortex Methods for Modelling Hydro- and Aerodynamics of Tidal Current Turbines and On- and Offshore Wind Turbines SIMPACK User Meeting 2014 Augsburg, Germany October 9 th, 2014 Dipl.-Ing.

More information

High-Speed Demonstration of Natural Laminar Flow Wing & Load Control for Future Regional Aircraft through innovative Wind Tunnel Model

High-Speed Demonstration of Natural Laminar Flow Wing & Load Control for Future Regional Aircraft through innovative Wind Tunnel Model High-Speed Demonstration of Natural Laminar Flow Wing & Load Control for Future Regional Aircraft through innovative Wind Tunnel Model Project organization The project tackles the CfP JTI-CS-2012-1-GRA-02-019

More information

Computational Modeling of Wind Turbines in OpenFOAM

Computational Modeling of Wind Turbines in OpenFOAM Computational Modeling of Wind Turbines in OpenFOAM Hamid Rahimi hamid.rahimi@uni-oldenburg.de ForWind - Center for Wind Energy Research Institute of Physics, University of Oldenburg, Germany Outline Computational

More information

Computational Fluid Dynamics Research Projects at Cenaero (2011)

Computational Fluid Dynamics Research Projects at Cenaero (2011) Computational Fluid Dynamics Research Projects at Cenaero (2011) Cenaero (www.cenaero.be) is an applied research center focused on the development of advanced simulation technologies for aeronautics. Located

More information

Simulation of Fluid-Structure Interactions in Aeronautical Applications

Simulation of Fluid-Structure Interactions in Aeronautical Applications Simulation of Fluid-Structure Interactions in Aeronautical Applications Martin Kuntz Jorge Carregal Ferreira ANSYS Germany D-83624 Otterfing Martin.Kuntz@ansys.com December 2003 3 rd FENET Annual Industry

More information

XFlow CFD results for the 1st AIAA High Lift Prediction Workshop

XFlow CFD results for the 1st AIAA High Lift Prediction Workshop XFlow CFD results for the 1st AIAA High Lift Prediction Workshop David M. Holman, Dr. Monica Mier-Torrecilla, Ruddy Brionnaud Next Limit Technologies, Spain THEME Computational Fluid Dynamics KEYWORDS

More information

Study the Influence of a Gap between the Wing and Slotted Flap over the Aerodynamic Characteristics of Ultra-Light Aircraft Wing Airfoil

Study the Influence of a Gap between the Wing and Slotted Flap over the Aerodynamic Characteristics of Ultra-Light Aircraft Wing Airfoil Journal of Mechanics Engineering and Automation 5 (2015) 278-285 doi: 10.17265/2159-5275/2015.05.002 D DAVID PUBLISHING Study the Influence of a Gap between the Wing and Slotted Flap over the Aerodynamic

More information

- Vortex Interactions with Wakes - Wing elements, fuselage, and landing gear

- Vortex Interactions with Wakes - Wing elements, fuselage, and landing gear - Vortex Interactions with Wakes -, fuselage, and landing gear Ulrich Jung, Christian Breitsamter Introduction Experimental technique Results and Analysis Fuselage Landing gear Conclusions / Prospects

More information

CFD Based Air Flow and Contamination Modeling of Subway Stations

CFD Based Air Flow and Contamination Modeling of Subway Stations CFD Based Air Flow and Contamination Modeling of Subway Stations Greg Byrne Center for Nonlinear Science, Georgia Institute of Technology Fernando Camelli Center for Computational Fluid Dynamics, George

More information

Status and Future Challenges of CFD in a Coupled Simulation Environment for Aircraft Design

Status and Future Challenges of CFD in a Coupled Simulation Environment for Aircraft Design Status and Future Challenges of CFD in a Coupled Simulation Environment for Aircraft Design F. CHALOT, T. FANION, M. MALLET, M. RAVACHOL and G. ROGE Dassault Aviation 78 quai Dassault 92214 Saint Cloud

More information

Knowledge Based Aerodynamic Optimization

Knowledge Based Aerodynamic Optimization 4th SST CFD Workshop Tokyo, 12-13 Oct 26 Knowledge Based Aerodynamic Optimization Helmut Sobieczky DLR German Aerospace Center Bunsenstr. 1, 3773 Göttingen, Germany e-mail: helmut.sobieczky@dlr.de... internet:

More information

ANSYS CFD results for the AIAA High Lift Prediction Workshop

ANSYS CFD results for the AIAA High Lift Prediction Workshop ANSYS CFD results for the AIAA High Lift Prediction Workshop Robin Steed ANSYS Canada Ltd. Waterloo, Ontario, Canada Greg Stuckert ANSYS, Inc. Lebanon, NH, USA 2009 ANSYS, Inc. All rights reserved. 1 Outline

More information

DCTA/IAE Aeroelasticity Branch Theoretical and Experimental Aeroelasticity Activities

DCTA/IAE Aeroelasticity Branch Theoretical and Experimental Aeroelasticity Activities DCTA/IAE Aeroelasticity Branch Theoretical and Experimental Aeroelasticity Activities Roberto GIL Annes da Silva Research Engineer - DCTA/IAE/ALA-L Adjunct Professor - ITA/IEA Outline Applied Aeroelasticity

More information

Circulation Control NASA activities

Circulation Control NASA activities National Aeronautics and Space Administration Circulation Control NASA activities Dr. Gregory S. Jones Dr. William E. Millholen II Research Engineers NASA Langley Research Center Active High Lift and Impact

More information

The influence of mesh characteristics on OpenFOAM simulations of the DrivAer model

The influence of mesh characteristics on OpenFOAM simulations of the DrivAer model The influence of mesh characteristics on OpenFOAM simulations of the DrivAer model Vangelis Skaperdas, Aristotelis Iordanidis, Grigoris Fotiadis BETA CAE Systems S.A. 2 nd Northern Germany OpenFOAM User

More information

CROR Noise Generation Mechanism #3: Installation Effects (& Quadrupole Noise)

CROR Noise Generation Mechanism #3: Installation Effects (& Quadrupole Noise) CROR Noise Generation Mechanism #3: Installation Effects (& Quadrupole Noise) Arne Stuermer & Jianping Yin Institute of Aerodynamics & Flow Technology DLR Braunschweig Germany 14th CEAS-ASC Workshop October

More information

HPC Deployment of OpenFOAM in an Industrial Setting

HPC Deployment of OpenFOAM in an Industrial Setting HPC Deployment of OpenFOAM in an Industrial Setting Hrvoje Jasak h.jasak@wikki.co.uk Wikki Ltd, United Kingdom PRACE Seminar: Industrial Usage of HPC Stockholm, Sweden, 28-29 March 2011 HPC Deployment

More information

ESSENTIAL COMPUTATIONAL FLUID DYNAMICS

ESSENTIAL COMPUTATIONAL FLUID DYNAMICS ESSENTIAL COMPUTATIONAL FLUID DYNAMICS Oleg Zikanov WILEY JOHN WILEY & SONS, INC. CONTENTS PREFACE xv 1 What Is CFD? 1 1.1. Introduction / 1 1.2. Brief History of CFD / 4 1.3. Outline of the Book / 6 References

More information

Aerospace Systems. Industry Spotlight

Aerospace Systems. Industry Spotlight 4 Aerospace Systems Engineering simulation is an integral part of the development process for critical components and major subsystems on today s aircraft from nose to tail. By Simon Pereira Senior Application

More information

A Primer on Using CFD to Tackle UAV Aerodynamics Problems

A Primer on Using CFD to Tackle UAV Aerodynamics Problems A W H I T E WP AH PIE TR EF R OP MA AP N ES YR S, I N C. A Primer on Using CFD to Tackle UAV Aerodynamics Problems Christoph Hiemcke, PhD, Fluent Inc. I INTRODUCTION You are an engineering manager or analyst,

More information

CFD Analysis of Civil Transport Aircraft

CFD Analysis of Civil Transport Aircraft IJSRD - International Journal for Scientific Research & Development Vol. 3, Issue 06, 2015 ISSN (online): 2321-0613 CFD Analysis of Civil Transport Aircraft Parthsarthi A Kulkarni 1 Dr. Pravin V Honguntikar

More information

LINEAR REDUCED ORDER MODELLING FOR GUST RESPONSE ANALYSIS USING THE DLR TAU CODE

LINEAR REDUCED ORDER MODELLING FOR GUST RESPONSE ANALYSIS USING THE DLR TAU CODE IFASD-213-36A LINEAR REDUCED ORDER MODELLING FOR GUST RESPONSE ANALYSIS USING THE DLR TAU CODE S. Timme 1, K. J. Badcock 1, and A. Da Ronch 2 1 School of Engineering, University of Liverpool Liverpool

More information

HPC enabling of OpenFOAM R for CFD applications

HPC enabling of OpenFOAM R for CFD applications HPC enabling of OpenFOAM R for CFD applications Towards the exascale: OpenFOAM perspective Ivan Spisso 25-27 March 2015, Casalecchio di Reno, BOLOGNA. SuperComputing Applications and Innovation Department,

More information

Overset Grids Technology in STAR-CCM+: Methodology and Applications

Overset Grids Technology in STAR-CCM+: Methodology and Applications Overset Grids Technology in STAR-CCM+: Methodology and Applications Eberhard Schreck, Milovan Perić and Deryl Snyder eberhard.schreck@cd-adapco.com milovan.peric@cd-adapco.com deryl.snyder@cd-adapco.com

More information

Aerospace Engineering 3521: Flight Dynamics. Prof. Eric Feron Homework 6 due October 20, 2014

Aerospace Engineering 3521: Flight Dynamics. Prof. Eric Feron Homework 6 due October 20, 2014 Aerospace Engineering 3521: Flight Dynamics Prof. Eric Feron Homework 6 due October 20, 2014 1 Problem 1: Lateral-directional stability of Navion With the help of Chapter 2 of Nelson s textbook, we established

More information

Scalable Distributed Schur Complement Solvers for Internal and External Flow Computations on Many-Core Architectures

Scalable Distributed Schur Complement Solvers for Internal and External Flow Computations on Many-Core Architectures Scalable Distributed Schur Complement Solvers for Internal and External Flow Computations on Many-Core Architectures Dr.-Ing. Achim Basermann, Dr. Hans-Peter Kersken, Melven Zöllner** German Aerospace

More information

Drag Prediction of Engine Airframe Interference Effects with CFX-5

Drag Prediction of Engine Airframe Interference Effects with CFX-5 JOURNAL OF AIRCRAFT Vol. 42, No. 6, November December 2005 Drag Prediction of Engine Airframe Interference Effects with CFX-5 R. B. Langtry, M. Kuntz, and F. R. Menter ANSYS CFX Germany, 83624 Otterfing,

More information

Aerodynamic Optimization Using Response Surface Model

Aerodynamic Optimization Using Response Surface Model Aerodynamic Optimization Using Response Surface Model Outline Background Response Surface Model Application Data Mining Background Many research of aerodynamic optimization for aerospace design problems

More information

Computational Analysis of Stress-strain State, Dynamics, Strength and Stability of Load-bearing Concrete Structures of NPP Evaporative Cooling Towers

Computational Analysis of Stress-strain State, Dynamics, Strength and Stability of Load-bearing Concrete Structures of NPP Evaporative Cooling Towers Prof. Alexandr Belostotskiy, Assoc. Prof. Sergey Dubinsky, PhD student Sergey Petryashev, PhD student Nicolay Petryashev Computational Analysis of Stress-strain State, Dynamics, Strength and Stability

More information

CFD analysis for road vehicles - case study

CFD analysis for road vehicles - case study CFD analysis for road vehicles - case study Dan BARBUT*,1, Eugen Mihai NEGRUS 1 *Corresponding author *,1 POLITEHNICA University of Bucharest, Faculty of Transport, Splaiul Independentei 313, 060042, Bucharest,

More information

CFD Applications using CFD++ Paul Batten & Vedat Akdag

CFD Applications using CFD++ Paul Batten & Vedat Akdag CFD Applications using CFD++ Paul Batten & Vedat Akdag Metacomp Products available under Altair Partner Program CFD++ Introduction Accurate multi dimensional polynomial framework Robust on wide variety

More information

Marine CFD applications using OpenFOAM

Marine CFD applications using OpenFOAM Marine CFD applications using OpenFOAM Andrea Penza, CINECA 27/03/2014 Contents Background at CINECA: LRC experience CFD skills Automatic workflow Reliability workflow OpenFOAM solvers for marine CFD analysis

More information

THE CFD SIMULATION OF THE FLOW AROUND THE AIRCRAFT USING OPENFOAM AND ANSA

THE CFD SIMULATION OF THE FLOW AROUND THE AIRCRAFT USING OPENFOAM AND ANSA THE CFD SIMULATION OF THE FLOW AROUND THE AIRCRAFT USING OPENFOAM AND ANSA Adam Kosík Evektor s.r.o., Czech Republic KEYWORDS CFD simulation, mesh generation, OpenFOAM, ANSA ABSTRACT In this paper we describe

More information

WIND TUNNEL INVESTIGATION OF THE WING LOAD CONTROL USING SELF-SUPPLYING FLUIDIC DEVICES

WIND TUNNEL INVESTIGATION OF THE WING LOAD CONTROL USING SELF-SUPPLYING FLUIDIC DEVICES Journal of KONES Powertrain and Transport, Vol. 21, No. 2 2014 WIND TUNNEL INVESTIGATION OF THE WING LOAD CONTROL USING SELF-SUPPLYING FLUIDIC DEVICES Andrzej Krzysiak Institute of Aviation (IoA) Krakowska

More information

Module 6 Case Studies

Module 6 Case Studies Module 6 Case Studies 1 Lecture 6.1 A CFD Code for Turbomachinery Flows 2 Development of a CFD Code The lecture material in the previous Modules help the student to understand the domain knowledge required

More information

ENGINEERING MECHANICS 2012 pp. 169 176 Svratka, Czech Republic, May 14 17, 2012 Paper #15

ENGINEERING MECHANICS 2012 pp. 169 176 Svratka, Czech Republic, May 14 17, 2012 Paper #15 . 18 m 2012 th International Conference ENGINEERING MECHANICS 2012 pp. 169 176 Svratka, Czech Republic, May 14 17, 2012 Paper #15 AEROELASTIC CERTIFICATION OF LIGHT SPORT AIRCRAFT ACCORDING "LTF" REGULATION

More information

2013 Code_Saturne User Group Meeting. EDF R&D Chatou, France. 9 th April 2013

2013 Code_Saturne User Group Meeting. EDF R&D Chatou, France. 9 th April 2013 2013 Code_Saturne User Group Meeting EDF R&D Chatou, France 9 th April 2013 Thermal Comfort in Train Passenger Cars Contact For further information please contact: Brian ANGEL Director RENUDA France brian.angel@renuda.com

More information

Model-Based Design of a New Light-weight Aircraft

Model-Based Design of a New Light-weight Aircraft Model-Based Design of a New Light-weight Aircraft Arkadiy Turevskiy 1, Stacey Gage 2, and Craig Buhr 3 The MathWorks, Inc. Natick, MA, 01760 This paper uses a combination of free and commercial off-the-shelf

More information

C²A²S²E Newsletter - Issue 03 - October Center for Computer Applications in AeroSpace Science and Engineering

C²A²S²E Newsletter - Issue 03 - October Center for Computer Applications in AeroSpace Science and Engineering C²A²S²E - C²A²S²E Center for Computer Applications in AeroSpace Science and Engineering C²A²S²E - running into application C²A²S²E project is widely focused on requirements from the aircraft development

More information

Computational Simulation of Flow Over a High-Lift Trapezoidal Wing

Computational Simulation of Flow Over a High-Lift Trapezoidal Wing Computational Simulation of Flow Over a High-Lift Trapezoidal Wing Abhishek Khare a,1, Raashid Baig a, Rajesh Ranjan a, Stimit Shah a, S Pavithran a, Kishor Nikam a,1, Anutosh Moitra b a Computational

More information

The Influence of Aerodynamics on the Design of High-Performance Road Vehicles

The Influence of Aerodynamics on the Design of High-Performance Road Vehicles The Influence of Aerodynamics on the Design of High-Performance Road Vehicles Guido Buresti Department of Aerospace Engineering University of Pisa (Italy) 1 CONTENTS ELEMENTS OF AERODYNAMICS AERODYNAMICS

More information

Co-Simulation and modal reduction for multifield problems in multibody dynamics

Co-Simulation and modal reduction for multifield problems in multibody dynamics Co-Simulation and modal reduction for multifield problems in multibody dynamics 7th Workshop on Descriptor Systems March 2005, Paderborn Martin Arnold [martin.arnold@mathematik.uni-halle.de] Martin Luther

More information

Aeroelastic Investigation of the Sandia 100m Blade Using Computational Fluid Dynamics

Aeroelastic Investigation of the Sandia 100m Blade Using Computational Fluid Dynamics Aeroelastic Investigation of the Sandia 100m Blade Using Computational Fluid Dynamics David Corson Altair Engineering, Inc. Todd Griffith Sandia National Laboratories Tom Ashwill (Retired) Sandia National

More information

2014.10.10. Measurement and Prediction Technology of Cooling Capability for Hybrid Drivetrain Components. Tadashi Yamada TOYOTA MOTOR CORPORATION

2014.10.10. Measurement and Prediction Technology of Cooling Capability for Hybrid Drivetrain Components. Tadashi Yamada TOYOTA MOTOR CORPORATION 2014.10.10 Measurement and Prediction Technology of Cooling Capability for Hybrid Drivetrain Components Tadashi Yamada TOYOTA MOTOR CORPORATION Contents 1, Introduction 2, Cooling mechanism of the Hybrid

More information

Application of a Tightly-Coupled CFD/6-DOF Solver For Simulating Offshore Wind Turbine Platforms

Application of a Tightly-Coupled CFD/6-DOF Solver For Simulating Offshore Wind Turbine Platforms Application of a Tightly-Coupled CFD/6-DOF Solver For Simulating Offshore Wind Turbine Platforms Alexander J. Dunbar 1, Brent A. Craven 1, Eric G. Paterson 2, and James G. Brasseur 1 1 Penn State University;

More information

Overset and Adaptive Meshes for Stabilized Finite-Element Scheme

Overset and Adaptive Meshes for Stabilized Finite-Element Scheme Overset and Adaptive Meshes for Stabilized Finite-Element Scheme W. Kyle Anderson, Behzad Ahrabi, and Chao Liu 2014 CFD Summer School Modern Techniques for Aerodynamic Analysis and Design Beijing Computational

More information

Chapter 6 Lateral static stability and control - 3 Lecture 21 Topics

Chapter 6 Lateral static stability and control - 3 Lecture 21 Topics Chapter 6 Lateral static stability and control - 3 Lecture 21 Topics 6.11 General discussions on control surface 6.11.1 Aerodynamic balancing 6.11.2 Set back hinge or over hang balance 6.11.3 Horn balanace

More information

8 High Lift Systems and Maximum Lift Coefficients

8 High Lift Systems and Maximum Lift Coefficients 8-1 8 High Lift Systems and Maximum Lift Coefficients In Section 7 the wing was examined with flaps retracted (clean wing). According to the assumptions from Section 5, the wing is, however, supposed to

More information

ABOUT THE GENERATION OF UNSTRUCTURED MESH FAMILIES FOR GRID CONVERGENCE ASSESSMENT BY MIXED MESHES

ABOUT THE GENERATION OF UNSTRUCTURED MESH FAMILIES FOR GRID CONVERGENCE ASSESSMENT BY MIXED MESHES VI International Conference on Adaptive Modeling and Simulation ADMOS 2013 J. P. Moitinho de Almeida, P. Díez, C. Tiago and N. Parés (Eds) ABOUT THE GENERATION OF UNSTRUCTURED MESH FAMILIES FOR GRID CONVERGENCE

More information

Aerodynamic Simulation. Viscous CFD Code Validation

Aerodynamic Simulation. Viscous CFD Code Validation Aerodynamic Simulation using STAR-CCM+ Viscous CFD Code Validation 19 March 2013 CD-adapco STAR-CCM+ Code Validation Efforts Kenneth E. Xiques CRM Solutions 4092 Memorial Pkwy SW, Suite 200 Huntsville,

More information

High-Lift Systems. High Lift Systems -- Introduction. Flap Geometry. Outline of this Chapter

High-Lift Systems. High Lift Systems -- Introduction. Flap Geometry. Outline of this Chapter High-Lift Systems Outline of this Chapter The chapter is divided into four sections. The introduction describes the motivation for high lift systems, and the basic concepts underlying flap and slat systems.

More information

CFD Simulation of the NREL Phase VI Rotor

CFD Simulation of the NREL Phase VI Rotor CFD Simulation of the NREL Phase VI Rotor Y. Song* and J. B. Perot # *Theoretical & Computational Fluid Dynamics Laboratory, Department of Mechanical & Industrial Engineering, University of Massachusetts

More information

MEL 807 Computational Heat Transfer (2-0-4) Dr. Prabal Talukdar Assistant Professor Department of Mechanical Engineering IIT Delhi

MEL 807 Computational Heat Transfer (2-0-4) Dr. Prabal Talukdar Assistant Professor Department of Mechanical Engineering IIT Delhi MEL 807 Computational Heat Transfer (2-0-4) Dr. Prabal Talukdar Assistant Professor Department of Mechanical Engineering IIT Delhi Time and Venue Course Coordinator: Dr. Prabal Talukdar Room No: III, 357

More information

Cefiro: An Aircraft Design Project in the University of Seville

Cefiro: An Aircraft Design Project in the University of Seville Cefiro: An Aircraft Design Project in the University of Seville Carlos Bernal Ortega, Andrés Fernández Lucena, Pedro López Teruel, Adrián Martín Cañal, Daniel Pérez Alcaraz, Francisco Samblás Carrasco

More information

Application of STAR-CCM+ in Marine and Off-Shore Engineering: State-of-the-Art and New Developments. M. Perić, F. Schäfer, E. Schreck, J.

Application of STAR-CCM+ in Marine and Off-Shore Engineering: State-of-the-Art and New Developments. M. Perić, F. Schäfer, E. Schreck, J. Application of STAR-CCM+ in Marine and Off-Shore Engineering: State-of-the-Art and New Developments M. Perić, F. Schäfer, E. Schreck, J. Singh Contents Main features of STAR-CCM+ relevant for marine and

More information

AUTOMOTIVE COMPUTATIONAL FLUID DYNAMICS SIMULATION OF A CAR USING ANSYS

AUTOMOTIVE COMPUTATIONAL FLUID DYNAMICS SIMULATION OF A CAR USING ANSYS International Journal of Mechanical Engineering and Technology (IJMET) Volume 7, Issue 2, March-April 2016, pp. 91 104, Article ID: IJMET_07_02_013 Available online at http://www.iaeme.com/ijmet/issues.asp?jtype=ijmet&vtype=7&itype=2

More information

Faculty of Aerospace Engineering

Faculty of Aerospace Engineering Delft University of Technology Dr. ir. Roeland De Breuker and Dr. Arvind Rao 20-3-2013 Delft University of Technology Challenge the future Delft University of Technology General Information Founded in

More information

CAMRAD II COMPREHENSIVE ANALYTICAL MODEL OF ROTORCRAFT AERODYNAMICS AND DYNAMICS

CAMRAD II COMPREHENSIVE ANALYTICAL MODEL OF ROTORCRAFT AERODYNAMICS AND DYNAMICS CAMRAD II COMPREHENSIVE ANALYTICAL MODEL OF ROTORCRAFT AERODYNAMICS AND DYNAMICS 1 CAMRAD II IS AN AEROMECHANICAL ANALYSIS OF HELICOPTERS AND ROTORCRAFT INCORPORATING ADVANCED TECHNOLOGY multibody dynamics

More information

High Performance Computing: A Review of Parallel Computing with ANSYS solutions. Efficient and Smart Solutions for Large Models

High Performance Computing: A Review of Parallel Computing with ANSYS solutions. Efficient and Smart Solutions for Large Models High Performance Computing: A Review of Parallel Computing with ANSYS solutions Efficient and Smart Solutions for Large Models 1 Use ANSYS HPC solutions to perform efficient design variations of large

More information

Effect of Propeller on Airplane Dynamics

Effect of Propeller on Airplane Dynamics Effect of Propeller on Airplane Dynamics The propeller creates considerable unfavorable forces that need to be trimmed out to keep the airplane flying in a desirable manner. Many airplanes are rigged to

More information

Wind-Tunnel Simulation using TAU on a PC-Cluster: Resources and Performance Stefan Melber-Wilkending / DLR Braunschweig

Wind-Tunnel Simulation using TAU on a PC-Cluster: Resources and Performance Stefan Melber-Wilkending / DLR Braunschweig Wind-Tunnel Simulation using TAU on a PC-Cluster: Resources and Performance Stefan Melber-Wilkending / DLR Braunschweig Folie 1 > Vortrag > Stefan Melber-Wilkending Wind-Tunnel Simulation using TAU on

More information

Using Computational Fluid Dynamics for Aerodynamics Antony Jameson and Massimiliano Fatica Stanford University

Using Computational Fluid Dynamics for Aerodynamics Antony Jameson and Massimiliano Fatica Stanford University Using Computational Fluid Dynamics for Aerodynamics Antony Jameson and Massimiliano Fatica Stanford University In this white paper we survey the use of computational simulation for aerodynamics, focusing

More information

University Turbine Systems Research 2012 Fellowship Program Final Report. Prepared for: General Electric Company

University Turbine Systems Research 2012 Fellowship Program Final Report. Prepared for: General Electric Company University Turbine Systems Research 2012 Fellowship Program Final Report Prepared for: General Electric Company Gas Turbine Aerodynamics Marion Building 300 Garlington Rd Greenville, SC 29615, USA Prepared

More information

F1 Fuel Tank Surging; Model Validation

F1 Fuel Tank Surging; Model Validation F1 Fuel Tank Surging; Model Validation Luca Bottazzi and Giorgio Rossetti Ferrari F1 team, Maranello, Italy SYNOPSIS A Formula One (F1) car can carry more than 80 kg of fuel in its tank. This has a big

More information

Introductory FLUENT Training

Introductory FLUENT Training Chapter 10 Transient Flow Modeling Introductory FLUENT Training www.ptecgroup.ir 10-1 Motivation Nearly all flows in nature are transient! Steady-state assumption is possible if we: Ignore transient fluctuations

More information

Multiphase Flow - Appendices

Multiphase Flow - Appendices Discovery Laboratory Multiphase Flow - Appendices 1. Creating a Mesh 1.1. What is a geometry? The geometry used in a CFD simulation defines the problem domain and boundaries; it is the area (2D) or volume

More information

Aerodynamic Properties of Avian Flight as a Function of Wing Shape. Andrew March Charles Bradley Advisor: Ephrahim Garcia

Aerodynamic Properties of Avian Flight as a Function of Wing Shape. Andrew March Charles Bradley Advisor: Ephrahim Garcia Aerodynamic Properties of Avian Flight as a Function of Wing Shape Andrew March Charles Bradley Advisor: Ephrahim Garcia Biomimetics The Fusion of Biology and Engineering Natural Selection as an optimization

More information

DESIGN AND ANALYSIS OF A TYPICAL WING RIB FOR PASSENGER AIRCRAFT

DESIGN AND ANALYSIS OF A TYPICAL WING RIB FOR PASSENGER AIRCRAFT DESIGN AND ANALYSIS OF A TYPICAL WING RIB FOR PASSENGER AIRCRAFT Bindu H.C 1,Muhammad Muhsin Ali.H 2 P.G. Student, Department of Mechanical Engineering, Ghousia college of Engineering, Ramanagaram, Karnataka,

More information

Efficient Convergence Acceleration for a Parallel CFD Code

Efficient Convergence Acceleration for a Parallel CFD Code Efficient Convergence Acceleration for a Parallel CFD Code R.D. Williams a, J. Häuser b, and R. Winkelmann b a California Institute of Technology, Pasadena, California b Center of Logistics and Expert

More information

If we let the vertical tail lift coefficient depend on a vertical tail lift curve slope and a rudder deflection we can write it as:

If we let the vertical tail lift coefficient depend on a vertical tail lift curve slope and a rudder deflection we can write it as: Roll and Yaw Moments and Stability Yaw Moment Equation The yaw moment is the moment about the z body axis and is positive if it moves the nose of the plane to the right. The big contributor to the yaw

More information

APPENDIX 3-B Airplane Upset Recovery Briefing. Briefing. Figure 3-B.1

APPENDIX 3-B Airplane Upset Recovery Briefing. Briefing. Figure 3-B.1 APPENDIX 3-B Airplane Upset Recovery Briefing Industry Solutions for Large Swept-Wing Turbofan Airplanes Typically Seating More Than 100 Passengers Briefing Figure 3-B.1 Revision 1_August 2004 Airplane

More information

CFD++ High Speed Flow Analysis on Turrets

CFD++ High Speed Flow Analysis on Turrets CFD++ High Speed Flow Analysis on Turrets P. Gratton*, E. Zuppel*, N. Stathopoulos**, O. Trifu *Bombardier Aerospace, Controlled Facilities & Engineering Services (CFES), Montreal, QC, patrice.gratton@aero.bombardier.com,

More information

A python pre-processing module for Chimera assembly. S. Péron, C. Benoit ONERA, CFD and Aeroacoustics Dept.

A python pre-processing module for Chimera assembly. S. Péron, C. Benoit ONERA, CFD and Aeroacoustics Dept. A python pre-processing module for Chimera assembly S. Péron, C. Benoit ONERA, CFD and Aeroacoustics Dept. Outline of talk Motivation Principle of the Chimera assembly Basic examples Implementation in

More information

A Computational Approach for Optimizing the First Flyer Using STAR-CCM+

A Computational Approach for Optimizing the First Flyer Using STAR-CCM+ A Computational Approach for Optimizing the First Flyer Using STAR-CCM+ Abdul H. Aziz* 1 Research Computing and Cyberinfrastructure The Pennsylvania State University, University Park, PA *Corresponding

More information

External bluff-body flow-cfd simulation using ANSYS Fluent

External bluff-body flow-cfd simulation using ANSYS Fluent External bluff-body flow-cfd simulation using ANSYS Fluent External flow over a bluff body is complex, three-dimensional, and vortical. It is massively separated and it exhibits vortex shedding. Thus,

More information

TwinMesh for Positive Displacement Machines: Structured Meshes and reliable CFD Simulations

TwinMesh for Positive Displacement Machines: Structured Meshes and reliable CFD Simulations TwinMesh for Positive Displacement Machines: Structured Meshes and reliable CFD Simulations 05.06.2014 Dipl.-Ing. Jan Hesse, Dr. Andreas Spille-Kohoff CFX Berlin Software GmbH Karl-Marx-Allee 90 A 10243

More information

Using CFD to improve the design of a circulating water channel

Using CFD to improve the design of a circulating water channel 2-7 December 27 Using CFD to improve the design of a circulating water channel M.G. Pullinger and J.E. Sargison School of Engineering University of Tasmania, Hobart, TAS, 71 AUSTRALIA Abstract Computational

More information

AOE Graduate Level Course Prerequisites

AOE Graduate Level Course Prerequisites AOE Graduate Level Course Prerequisites AOE 5024: Vehicle AOE 5135 5136 (ME 5135 5136): Vehicle Propulsion Prerequisites: AOE 3114 and ME 3134 or Graduate AOE 5034 (ESM 5304): Mechanical and Structural

More information

Reynolds Averaged Navier-Stokes Analysis for Civil Transport Aircraft using Structured and Unstructured grids

Reynolds Averaged Navier-Stokes Analysis for Civil Transport Aircraft using Structured and Unstructured grids 14 th Annual CFD Symposium 10 th 11 th August 2012, Bangalore Reynolds Averaged Navier-Stokes Analysis for Civil Transport Aircraft using Structured and Unstructured grids Vishal S. Shirbhate CTFD Division,

More information

Formula 1 Aerodynamic Assessment by Means of CFD Modelling

Formula 1 Aerodynamic Assessment by Means of CFD Modelling Formula 1 Aerodynamic Assessment by Means of CFD Modelling DANSIS Automotive Fluid Dynamics Seminar 25 March 2015 Copenhagen Denmark Dr. Lesmana Djayapertapa Senior CFD Consultant LR Senergy Aberdeen -

More information

Requirements to servo-boosted control elements for sailplanes

Requirements to servo-boosted control elements for sailplanes Requirements to servo-boosted control elements for sailplanes Aerospace Research Programme 2004 A. Gäb J. Nowack W. Alles Chair of Flight Dynamics RWTH Aachen University 1 XXIX. OSTIV Congress Lüsse, 6-136

More information

Simulation at Aeronautics Test Facilities A University Perspective Helen L. Reed, Ph.D., P.E. ASEB meeting, Irvine CA 15 October 2014 1500-1640

Simulation at Aeronautics Test Facilities A University Perspective Helen L. Reed, Ph.D., P.E. ASEB meeting, Irvine CA 15 October 2014 1500-1640 Simulation at Aeronautics Test A University Perspective Helen L. Reed, Ph.D., P.E. ASEB meeting, Irvine CA 15 October 2014 1500-1640 Questions How has the ability to do increasingly accurate modeling and

More information

CFD Simulations and Wind Tunnel Experiments of a Generic Split-Canard Air-to-Air Missile at High Angles of Attack in Turbulent Subsonic Flow

CFD Simulations and Wind Tunnel Experiments of a Generic Split-Canard Air-to-Air Missile at High Angles of Attack in Turbulent Subsonic Flow AIAA Atmospheric Flight Mechanics Conference 08-11 August 2011, Portland, Oregon AIAA 2011-6335 CFD Simulations and Wind Tunnel Experiments of a Generic Split-Canard Air-to-Air Missile at High Angles of

More information

SIX DEGREE-OF-FREEDOM MODELING OF AN UNINHABITED AERIAL VEHICLE. A thesis presented to. the faculty of

SIX DEGREE-OF-FREEDOM MODELING OF AN UNINHABITED AERIAL VEHICLE. A thesis presented to. the faculty of SIX DEGREE-OF-FREEDOM MODELING OF AN UNINHABITED AERIAL VEHICLE A thesis presented to the faculty of the Russ College of Engineering and Technology of Ohio University In partial fulfillment of the requirement

More information

Towards cooperative high-fidelity aircraft MDO: comparison of Breguet and ODE evaluation of the cruise mission segment

Towards cooperative high-fidelity aircraft MDO: comparison of Breguet and ODE evaluation of the cruise mission segment www.dlr.de Chart 1 STAB Symposium 2014 Munich, November 4, 2014 Towards cooperative high-fidelity aircraft MDO: comparison of Breguet and ODE evaluation of the cruise mission segment Časlav Ilić, Tanja

More information