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Folie 1 > HLRS 2005 > A. Schütte14. Oktober 2005
Andreas Schütte
DLR - German Aerospace CenterInstitute of Aerodynamics and Flow Technology
Oct. 14th 2005, Stuttgart
Numerical simulation of maneuvering combat aircraft
Folie 2 > HLRS 2005 > A. Schütte14. Oktober 2005
Gunnar Einarsson, Britta Schöning, Axel Raichle,Wulf Mönnich, Thomas Alrutz, Jens Neumann, Jörg Heinecke
DLR - German Aerospace CenterInstitute of Aerodynamics and Flow Technology
Oct. 14th 2005, Stuttgart
Numerical simulation of maneuvering combat aircraft
Folie 3 > HLRS 2005 > A. Schütte14. Oktober 2005
OverviewMotivation
Objectives
Simulation Environment
Experimental Simulation
Numerical Results
HPC Requirements and Resources
Summary and Outlook
Folie 4 > HLRS 2005 > A. Schütte14. Oktober 2005
HPC – RequirementsInstitut of Aerodynamics and
Flow TechnologyBraunschweig /Göttingen
Folie 5 > HLRS 2005 > A. Schütte14. Oktober 2005
Motivation
Source: Cenaero
Folie 6 > HLRS 2005 > A. Schütte14. Oktober 2005
Objectivesof 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 TechnologyInstitute of AeroelasticityInstitute of Flight SystemsDLR Sistec
Folie 7 > HLRS 2005 > A. Schütte14. Oktober 2005
Simulation Environment TENTCodes 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 gridsdefinition of all movements of parts and grids relative to each otheranimation and test of movements creation of “motion” and “hierarchy” files for the CFD-Code-TAU
Folie 8 > HLRS 2005 > A. Schütte14. Oktober 2005
DLR TAU-CodeCFD-Code
solution of RANS equations for arbitrarily moving bodies on unstructured meshes hybrid meshes (hex., prisms, tetra., pyram.)FV using dual grid approach, MG acceleratedunsteady via dual time stepping state-of-the-art turbulence modelsgrid adaptation (refinement & de-refinement)CHIMERA techniquedeforming mesh capability designed for massively parallel computersvalidated for a large number of test cases
Folie 9 > HLRS 2005 > A. Schütte14. Oktober 2005
DLR TAU-Code Chimera approach
Chimera boundary of the flap
Chimera boundary of the wing
Realized soon: Automatic hole-cutting approach
Folie 10 > HLRS 2005 > A. Schütte14. Oktober 2005
Stream lines & Total pressure distribution
DLR TAU-Code Mesh adaptation (unsteady calc.)
History of mesh adaptation
Folie 11 > HLRS 2005 > A. Schütte14. Oktober 2005
SIMULAFlight mechanics library
Simulation environment SIMULA delivers the solutions of the flight mechanics equations
Trimming calculationAnalyze stabilityManeuver simulations with 6 DoF and control devices
Coupling of Aerodynamics/Flight mechanicsImplicit time integration schemeClose coupling within each pseudo time-step
Implemented models for SikMaRolling delta-wing with trailing-edge flapsGeneric 6-DoF model (e.g. X-31)
Folie 12 > HLRS 2005 > A. Schütte14. Oktober 2005
CSM-CodeStructural mechanics simulation
Two approachesDiscrete approach: Coupling with the overall FE-ModelModal approach: Coupling with characteristic Eigenmodes
CharacteristicsCoupling Aerodynamics/Structure: Loose/weak coupling scheme –coupling within each physical time stepSolving the CSM-equations: Implicit Newmark integration-schemeSpatial coupling: Scattered data interpolation methods for force and deformation transferCoupling in time: Conventional Serial Staggered-algorithm with predictor- /corrector step for the CSM calculationDetermination of the system matrices: Reduced system matrices MAA and KAA imported from NASTRAN
Folie 13 > HLRS 2005 > A. Schütte14. Oktober 2005
Experimental SimulationWind tunnel experiments
ObjectivesGenerating a validation data base for the numerical simulation.Knowledge approach of the aerodynamic behavior of configurations with vortex dominated flow fields
Configurations1. 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 14 > HLRS 2005 > A. Schütte14. Oktober 2005
Experimental SimulationWind tunnel facilities
Transonic Wind Tunnel Göttingen (TWG)
Test section 1x1mMach number range: 0.3 ÷1.2 (with perf. walls)Re = 1.8 × 106 (based on 0.1√s)
Low Speed Wind Tunnel Braunschweig (NWB)
Test section 3.25 × 2.8mMach number range: 0 ÷0.26 (for open test section)Re = 1.8 x 106 (based on 0.1√s)
Folie 15 > HLRS 2005 > A. Schütte14. Oktober 2005
Experimental SimulationWind tunnel models
Delta-wing-configuration with trailing-edge flaps
Internal 6-component piezo-balancePiezo-resistive pressure sensors at 60% and 80% chord lengthControl device velocity up to 300°/s
X-31 configuration with remote controlled control devices
CFRP fuselage, steel wing and aluminum made control devices8 internal servo engines for control device movementInternal 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 16 > HLRS 2005 > A. Schütte14. Oktober 2005
MPM - ”Model Positioning Mechanism”Maneuver simulation in the wind tunnel
Synchronized, dynamic similarmovement of model and control devices in comparison to flight tests
Parallel kinematicsSteward platform connected to electromagnetic linear motors by 6 rods of constant length
Folie 17 > HLRS 2005 > A. Schütte14. Oktober 2005
Folie 18 > HLRS 2005 > A. Schütte14. Oktober 2005
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 19 > HLRS 2005 > A. Schütte14. Oktober 2005
FE-Model of delta-wing andrear sting support
Numerical Results (1)Delta wing guided rolling motion around longitudinal axisCSM-TAU-Coupling
Folie 20 > HLRS 2005 > A. Schütte14. Oktober 2005
Numerical Results (1)Delta wing guided rolling motion around longitudinal axisCSM-TAU-Coupling
Folie 21 > HLRS 2005 > A. Schütte14. Oktober 2005
Numerical Results (2)Delta wing guided rolling motion around longitudinal axisCSM-TAU-FM-Coupling
Folie 22 > HLRS 2005 > A. Schütte14. Oktober 2005
Numerical Results (3)Delta wing free-to-roll motion around longitudinal axisTAU-FM-Coupling
Ma = 0.5Re = 3.8MioΘ = 17°Φ0 = 0°η = ±5°
Folie 23 > HLRS 2005 > A. Schütte14. Oktober 2005
Numerical Results (3)Delta wing free-to-roll motion around longitudinal axisTAU-FM-Coupling
12 3
4
Folie 24 > HLRS 2005 > A. Schütte14. Oktober 2005
Numerical Results (3)Delta wing free-to-roll motion around longitudinal axisTAU-FM-Coupling
Flap down
Flap up
O clO Φ
Folie 25 > HLRS 2005 > A. Schütte14. Oktober 2005
α=14°α=18°α=22°
Numerical Results (4)Flow simulation around X-31 configuration (clean wing)
Folie 26 > HLRS 2005 > A. Schütte14. Oktober 2005
separation line
attachement line
Tau-CalculationOil Flow Picture
Numerical Results (4)Flow topology of X-31 (clean wing)
Ma=0.12Re=1.0Mioa=18°
Folie 27 > HLRS 2005 > A. Schütte14. Oktober 2005
Numerical Results (4)Flow simulation around X-31 configuration
TAU-Calculation:Re = 2.07Mioα =18°
PSP-Measurement:Re = 2.07Mioα =18°
Folie 28 > HLRS 2005 > A. Schütte14. Oktober 2005
HPC Requirements and Resources (1)Calculation times and resources today
Folie 29 > HLRS 2005 > A. Schütte14. Oktober 2005
Herbstmaneuver: 10 s
HPC Requirements and Resources (2)Requirements on HPC Cluster-HardwareManeuver Simulation
X-31 configuration, movable control devices~30 Million grid pointsunsteady simulation with DLR-TAU-CodeCFD / CSD / FMManeuver simulation of 2 seconds real timeAim: 2 weeks
Approximation on target platformHWW-Cluster Strider (64 Proc, 64 Bit): 30 Mio. grid points2 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
Folie 30 > HLRS 2005 > A. Schütte14. Oktober 2005
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