Addressing The Challenges Of The Design Of Hypersonic .
Addressing the Challenges of the Designof Hypersonic Vehicles with SimulationsValerio Viti, PhD, Lead EngineerScott Marinus, Senior EngineerJeff Tharp, PhD, Principal EngineerCraig Miller, PhD, Principal EngineerAnsys, Inc.
Ansys technical panel2Valerio Viti, PhDLead Application Engineer,Fluids SMEScott MarinusSenior Application Engineer,Mechanical SMEJeff Tharp, PhDPrincipal Application Engineer,Electromagnetic SMECraig Miller, PhDPrincipal Application Engineer.Mechanical/Workflow/DT SME
Webinar outline Introduction‐ Why hypersonics, why now The Ansys hypersonic solution: an overview Hypersonic case studies3
What is hypersonics? In aerodynamics, a hypersonic speed is one that is highly supersonic. Since the 1970s, the term hasgenerally referred to speeds of Mach 5 and above.CFD analysis of X43 courtesy of NASA
What is hypersonics? In aerodynamics, a hypersonic speed is one that is highly supersonic. Since the 1970s, the term hasgenerally referred to speeds of Mach 5 and above.More generally, the definition of the hypersonic regime is loose;there is no sudden and clear change in flow conditions, e.g. formationof a sonic boom, but rather a gradual change in flow and materialproperties.CFD analysis of X43 courtesy of NASA
Why the interest in hypersonicsCourtesy of Lockheed-Martin, hypersonics.html
Why the interest in hypersonicsCourtesy of Hermeus, http://www.hermeus.com/Courtesy of Lockheed-Martin, hypersonics.html
Why now? Differently form other times in the past 30 year, the current impetus behind the development ofhypersonic vehicles is coming from the changed global hypersonic scenario.China DailyRussian Ministry of Defense/Sputnik News
Hypersonic global marketGlobal market forecast for hypersonic weapons by regions, 2019-2027, US BNSource: Hypersonic Missiles Report 2019-2027, Institute for Defense and Government, 2019Estimated global tot: US 127.3B over the next 8 years
What is happening in North America?
Hypersonic NA funding 700M for MDA through 2024 222 (x4 yrs) for DARPA (DARPA does not release 5-year cycles) 2.5B of classified work through 2024 157M for hypersonic defensive weapons (2020, most likely to grow)Tot: 11.4B over the next 5 years
Hypersonic NA funding“It is the sense of Congress that development of hypersoniccapabilities is a key element of the National Defense Strategy.”Section 219 of 2020 SASC draft 700M for MDA through 2024 222 (x4 yrs) for DARPA (DARPA does not release 5-year cycles) 2.5B of classified work through 2024 157M for hypersonic defensive weapons (2020, most likely to grow)Tot: 11.4B over the next 5 years
Not only the military. Civilian market too.Photo: Courtesy of Business Insider/HermeusFlight Global/BoeingPlanetary atmospheric re-entryPhoto: Courtesy of NASACourtesy of StratolaunchPhoto: Courtesy of ESA
Simulation technology for hypersonics The design of these maneuverable hypersonic interceptors requires extensiveunderstanding of all of the physics involved and their interaction aerothermodynamics, structure, electromagnetic, sensors, guidance and control, etc. Physical testing capabilities for very high-speed aerodynamics are limited:Ground Testing Few specialized facilities Limited time duration and physical scale Difficult, if not impossible, to match actual flight conditions Expensive to develop and to runPhoto: NASA LangleyFlight Testing Extremely expensiveOften test cycles lasts 5 yearsLimited instrumentationMost realistic scenarioPhoto: US Air Force/Reuters
Simulation technology for hypersonics The design of these maneuverable hypersonic interceptors requires extensiveunderstanding of all of the physics involved aerothermodynamics, structure, electromagnetic, sensors, guidance and control, etc. Physics-based simulation is a key enabling technology forPhysical testing capabilities for very high speed aerodynamics are limited:the development of this class of vehiclesGround Testing Few specialized facilities Limited time duration and physical scale Difficult, if not impossible, to match actual flight conditions Expensive to develop and to runCFD analysis of X43 courtesy of NASAPhoto: NASA LangleyFlight Testing Extremely expensiveOften test cycles lasts 5 yearsLimited instrumentationMost realistic scenarioPhoto: US Air Force/Reuters
Ansys Hypersonic solutionPlatform and workflowo Platform agnosticAerothermodynamics Heat fluxes and aero forcesShock location and behaviorLaminar-Turbulent transitionFlow controlChemical non-equilibriumThermodynamic non-equilibriumAblationAero opticsProcess Integration andDesign Optimization Platform agnostic Multiphysics Parametric analysis Design optimization Data and process mngt Traceability Data and process management TraceabilityCommunication and tracking Antennas and sensors Radio/GPS jamming Radar/IR signature Structural deformation Vibration impact Communication black-outStructure and materials FSI/Deformation: steady-state transient Fracture and fatigue Structural integrity Material intelligenceSystem integration Control system integration Sensor fusion and actuation Navigation, guidance andcontrol “Wargaming” and mission-levelsimulation: AGIThermal managementPropulsion Radiation, Conv., Cond.Conjugate Heat TransferActive coolingPhase change: boiling,evapor./condensation Melting/solidification Electronics coolingRAM/SCRAMJET combustionSolid/Liquid rocketGas, liquid and solid fuelsThermal loadsStructural deformation
New Ansys R&D collaborations in hypersonics University of Texas, Arlington‐‐‐‐Aerodynamic Research Lab (ARC): Director Prof MaddalenaThe only US academic institution with arc-jet facility.Inaugurated in summer 2019, with 1.5M funding from US Navy/DARPACutting-edge experimental research in hypersonics (aerothermodynamics, SCRAMJET propulsion,ablation)‐ Currently working with AFRL/NRL/DARPA Missouri Science and Technology, RollaThese universities and Ansys are members of theUniversity Consortium for Applied Hypersonics‐ Aerodynamic Computational Lab led by Prof Hosder‐ Research sponsored by NASA and Missile Defense Agency: Simulation technology for high-speed flows Effect of particles on high-speed vehicles Uncertainty Quantification‐ ARL has recently won an NSF grant for 2M to deploy a supercomputer dedicated to computersimulations. University of Colorado, Boulder‐ Collaboration with UC Boulder’s Non-Equilibrium Gas and Plasma Dynamics Lab on hybridcoupling of CFD and DSMC methods for rarefied flows.
Ansys CFD Hypersonic TrainingImprove engineering productivity using advanced engineering simulationLearn how to use Ansys CFD to design and analyze hypersonic systems 2-day on-site course (1-week mentoring project total) Combination of lectures and hands-on workshops Work on your own problem on the second day Maximum 10 students per classExtending training material toinclude structural andelectromagnetic modules ANSYSContact: Rodger.Zhao@ansys.comWhat you will learn The value of simulation for hypersonic systems Using Ansys CFD for hypersonic vehicles Modeling advanced physical processes includingchemical non-equilibrium Simulation strategies to improve productivity
OutlineAerothermodynamic environment and propulsionStructural integrity and deformation for a hypersonicvehicleSensor reliability in high heat-flux environmentPredicting communication degradation and blackoutTool-chaining and workflow assembly for hypersonics19
OutlineAerothermodynamic environment and propulsionStructural integrity and deformation for a hypersonicvehicleSensor reliability in high heat-flux environmentPredicting communication degradation and blackoutTool-chaining and workflow assembly for hypersonics20Valerio Viti
ANSYS Technology Stack for HypersonicsAerodynamicsPropulsionMaterials & StructuresCommunication & TrackingAerothermodynamicsAero opticso Shock capturing and locationo Pressure distributiono Skin friction, Wall heat fluxo Inlet conditions for engineso Turbulence transitiono Flow controlSystem IntegrationAblationo Surface finite-rate reactionso Charring and erosiono Surface recessiono LE/Nose/flap shape changeo Shock and turbulenceo OPL/OPD computationAircraft/boosterSeparationActive coolingo Single/Multi-phaseo Radiation, Convection, Condo Phase change: boiling,evaporation/condensationo Jet impingemento Trajectory computationo Aerodynamic interferenceo Shock impingementChemical non-equilibriumo Species transport, finite-rate reactionso Dissociation, ionization, recombinationo Equilibrium and non-equilibriumo Flexible and powerful chemical solver21Plasma activationo Ion concentrationo Lorentz forceso Communication blackoutConjugate HTo Radiation, Convection, Condo Surface and structure conductiono Melting/solidification
Hyp-01Hypersonic60,10AerospikeExtensive suite of validations for hypersonic flowscaseflow regimeMach No.AoAgeometryT-1Transonic0.6 to 0.8Range from -5 to 2T-2Transonic0.852.5 to onic0.850.4, 0.8, 0.90.95, 1.21.2-20165, 180PublicationExp ReferenceDLR-F6 wing-body and wingbody-nacelle-pylonEisenhut, S. & Frank, T. 2nd AIAA Drag Prediction Workshop, DLR-F6Aircraft Model, WB and WBNP Configuration, Orlando, FL, June 2122, 2003.2nd AIAA CFD Drag Prediction WorkshopCRM wing-body and wingbodynacelle-pylonZore, K., Sasanapuri, B., Shah, S., Bish, E., & Sotkes, J. ANSYSSimulation Results for the 6th AIAA Drag Prediction Workshop,Washington , DC, June 16-17, 2016.6th AIAA CFD Drag Prediction WorkshopTransonic Cavity NoiseKurtabatskii, K., Menter, F., Schuetze, J., & Fujii, A. NumericalSimulation of Transonic Cavity Noise using Scale‐AdaptiveSimulation (SAS) Turbulence Model, Internoise 2011, Osaka, Japan,September 4-7, 2011.M. J. Henshaw, "M219 Cavity Case," Verification andValidation Data for Computational Unsteady Aerodynamics, Tech.Rep. RTO‐TR‐26, AC/323(AVT)TP/19 (2000).RAE wing bodyAnsys internal validationTreadgold, D., Jones, A., and Wilson, K., "Pressure DistributionMeasured in the RAE 8ft x 6ft Transonic Wind Tunnel on RAE Wing‘A’ in Combination with an Axi‐Symmetric Body at Mach Numbers of0.4, 0.8 and 0.9," AGARD-AR-138, Appendix B4.store drop - delta wingSnyder, D.O., Koutsavdis, E.K., Anttonen, J.S.R.: “Transonic storeseparation using unstructured CFD with dynamic meshing”,Technical Report AIAA-2003-3913, 33th AIAA Fluid DynamicsConference and Exhibition, American Institute of Aeronautics andAstronautics, 2003.Heim, E. : "CFD wing/pylon/finned store mutual interference windtunnel experiment", DTIC Document, (1991).Apollo capsuleSup-2Supersonic3.480re-entry capsule w/ counterflowing jetSup-3Supersonic2.5,3.5Range from -5 to 18tandem canard missileSup-4Supersonic2.4-SCRAMJET Hyp-02Hyp-03HypersonicHypersonic6.57.93-Hypersonic SCRAMJET0Hypersonic flow over MarsPathfinder (70 degree spherecone)Hyp-04Hypersonic8.3-Hypersonic double fin inletHyp-05Hypersonic100Hyperboloid 8Hypersonic19.4Biconic Reentry Vehicle withSix Extended Flaps00sharp-nosed double coneFIRE II re-entry vehicleimageAnsys internal validationAnsys internal validationRao, V., Viti, V., & Abanto, J. CFD simulations of super/hypersonicmissiles: validation, sensitivity analysis, andimproved design, AIAA SciTech Forum, 6-10 January 2020, Orlando,FL, January 2020.Ansys internal validationRao, V., Viti, V., & Abanto, J. CFD simulations of super/hypersonicmissiles: validation, sensitivity analysis, andimproved design, AIAA SciTech Forum, 6-10 January 2020, Orlando,FL, January 2020.Hyp-02Hypersonic6.5-Hypersonic SCRAMJETHyp-03Hypersonic7.930Hypersonic flow over MarsPathfinder (70 degree spherecone)Hyp-04Hypersonic8.3-Hypersonic double fin inletHyp-05Hypersonic100Hyperboloid ic Reentry Vehicle withSix Extended Flaps019.40FIRE II re-entry vehicleHyp-09Hypersonic250blunt axisymmetric sphereconeAnsys internal c10.6, 11.10Hypersonic transition on a FlatPlateBlair, Jr., A. B., Allen, J. M., Hernandez, G., Effect of tail-fin span onstability and control characteristics of a canardcontrolled missile atsupersonic Mach number, NASA Technical Paper 2157, June 1983.Burrows, M. C. and Kurkov, A. P., "Analytical and Experimental Studyof Supersonic Combustion of Hydrogen in a Vitiated Airstream,"NASA-TM-X-2828, Sep. 1973.Paterna, D., Monti, R., Savino, R., & Esposito, A., Experimental andNumerical Investigation of Martian Atmosphere Entry, Journal ofSpacecraft and Rockets, Vol. 39, No. 2, March-April 2002.upcoming AIAA paper Viti, V., Crawford, B., Arguinzoni, C., Rao, V.,& Zori, L. Numerical simulations of four hypersonic vehicles using a Kussoy, M.I., Horstman, K. C., Horstman, C. C., Hypersonic Crossingdensity-based CFD solver: validation, analysis and sensitivity toShock-Wave/Turbulent Boundary-Layer Interactions, AIAA Journalmaterial properties31 No. 12, 2197-2203, 19932020.Sagnier, Ph., Joly, V, and Marmignon, C., “Analysis ofKurbatskii, K.A, Kumar, R., and Mann, D., “Simulation of ExternalNonequilibrium Flow Calculations and Experimental Results AroundHypersonic Problems Using Fluent 6.3 Density-Based Coupleda Hyperboloid‐flare Configuration”, 2nd European Symposium onSolver”, 2nd European Conference for Aerospace SciencesAerodynamics for Space Vehicles, 1995.upcoming AIAA paper Viti, V., Crawford, B., Arguinzoni, C., Rao, V.,& Zori, L. Numerical simulations of four hypersonic vehicles using a Jordan, T.M., Buffington, R.J., Aerodynamic Model for adensity-based CFD solver: validation, analysis and sensitivity toHemispherically-Capped Biconic Reentry Vehicle with Six Dragmaterial propertiesFlaps. AIAA Paper 87-2364, 1987.2020.upcoming AIAA paper Viti, V., Crawford, B., Arguinzoni, C., Rao, V.,Effect of Vibrational Non-Equilibrium on Hypersonic Double-Cone& Zori, L. Numerical simulations of four hypersonic vehicles using aExperiments Ioannis Nompelis and Graham V. Candler (AIAAdensity-based CFD solver: validation, analysis and sensitivity toJournal Vol.41, No.11, Nov 2003material properties 2020.upcoming AIAA paper Viti, V., Crawford, B., Arguinzoni, C., Rao, V.,& Zori, L. Numerical simulations of four hypersonic vehicles using adensity-based CFD solver: validation, analysis and sensitivity tomaterial properties2020.Hash, D., Olejniczak, J., Wright, M., Prabhu, D., Pulsonetti, M., Hollis,B., Gnoffo, P., Barnhardt, M., Nompelis, I., FIRE II Calculations forHypersonic Nonequilibrium Aerothermodynamics CodeVerification: DPLR, LAURA,and US3D, 45th AIAA Aerospace SciencesMeeting and Exhibit, Reno, NV, AIAA Paper 2007-605, January 2007.Wright, M., Loomis, M., Papadopoulos, P., Aerothermal Analysis ofthe Project Fire II Afterbody Flow, Journal of Thermophysics andHeat Transfer, vol. 17 No.2, April-June 2003.Paterna, D., Monti, R., Savino, R., & Esposito, A., Experimental andNumerical Investigation of Martian Atmosphere Entry, Journal ofSpacecraft and Rockets, Vol. 39, No. 2, March-April 2002.upcoming AIAA paper Viti, V., Crawford, B., Arguinzoni, C., Rao, V.,& Zori, L. Numerical simulations of four hypersonic vehicles using a Kussoy, M.I., Horstman, K. C., Horstman, C. C., Hypersonic Crossingdensity-based CFD solver: validation, analysis and sensitivity toShock-Wave/Turbulent Boundary-Layer Interactions, AIAA Journalmaterial properties31 No. 12, 2197-2203, 19932020.Sagnier, Ph., Joly, V, and Marmignon, C., “Analysis ofKurbatskii, K.A, Kumar, R., and Mann, D., “Simulation of ExternalNonequilibrium Flow Calculations and Experimental Results AroundHypersonic Problems Using Fluent 6.3 Density-Based Coupleda Hyperboloid‐flare Configuration”, 2nd European Symposium onSolver”, 2nd European Conference for Aerospace SciencesAerodynamics for Space Vehicles, 1995.upcoming AIAA paper Viti, V., Crawford, B., Arguinzoni, C., Rao, V.,& Zori, L. Numerical simulations of four hypersonic vehicles using a Jordan, T.M., Buffington, R.J., Aerodynamic Model for adensity-based CFD solver: validation, analysis and sensitivity toHemispherically-Capped Biconic Reentry Vehicle with Six Dragmaterial propertiesFlaps. AIAA Paper 87-2364, 1987.2020.upcoming AIAA paper Viti, V., Crawford, B., Arguinzoni, C., Rao, V.,Effect of Vibrational Non-Equilibrium on Hypersonic Double-Cone& Zori, L. Numerical simulations of four hypersonic vehicles using aExperiments Ioannis Nompelis and Graham V. Candler (AIAAdensity-based CFD solver: validation, analysis and sensitivity toJournal Vol.41, No.11, Nov 2003material properties 2020.HypersonicDaso, O. E. et. al., " Dynamics of Shock Dispersion and Interactions inSupersonic Freestreams with Counterflowing Jets," AIAA Journal,Vol. 47, No. 6, June 2009.Huebner, L., et al., Experimental results on the feasibility of anaerospike for hypersonic missiles, 33rd Aerospace Sciences Meetingand Exhibit, Aerospace Sciences Meetings, Reno, NV, 1995.Ansys internal validationHyp-08Moseley, W. Graham, R., & Hughes, J., Aerodynamic StabilityCharacteristics of the Apollo Command Module, NASA-TN D-4688,August 1968.aerospike for hypersonic missiles, 33rd Aerospace Sciences Meetingand Exhibit, Aerospace Sciences Meetings, Reno, NV, 1995.Kumaran, K. & Babu, V., Mixing and combustion characteristics ofBabu, V., Run Like the Wind, ANSYS Advantage, Volume VIII, Issue 1,kerosene in a model supersonic combustor, Journal of Propulsion2014.and Power 25 (3), 583-592.upcoming AIAA paper Viti, V., Crawford, B., Arguinzoni, C., Rao, V.,& Zori, L. Numerical simulations of four hypersonic vehicles using adensity-based CFD solver: validation, analysis and sensitivity tomaterial properties2020.Hash, D., Olejniczak, J., Wright, M., Prabhu, D., Pulsonetti, M., Hollis,B., Gnoffo, P., Barnhardt, M., Nompelis, I., FIRE II Calculations forHypersonic Nonequilibrium Aerothermodynamics CodeVerification: DPLR, LAURA,and US3D, 45th AIAA Aerospace SciencesMeeting and Exhibit, Reno, NV, AIAA Paper 2007-605, January 2007.Wright, M., Loomis, M., Papadopoulos, P., Aerothermal Analysis ofthe Project Fire II Afterbody Flow, Journal of Thermophysics andHeat Transfer, vol. 17 No.2, April-June 2003.Lee, K. & Gupta, R. , Viscous-Shock-Layer Analysis of HypersonicFlows over Long Slender Vehicles, NASA Contractor Report 189614March 1992.Widhopf, G. F., and Wang, J. C. T., “A TVD Finite‐Volume Techniquefor Nonequilibrium Chemically Reacting Flows”, AIAA Paper 1988‐2711 Dellinger, T. C., “Computation of Nonequilibrium MergedStagnation Shock Layers by Successive Accelerated Replacement”,AIAA Journal, 9(2):262-269, 1971.Holden, M., MacLean, M., Wadhams, T., and Mundy, E.,"Experimental Studies of Shock Wave/Turbulent Boundary LayerInteraction in High Reynolds Number Supersonic and HypersonicAliaga, C., Guan, K., Selvanayagam, J., Sokes, J., Viti, V., & Menter, F. Flows to Evaluate the Performance of CFD Codes", AIAA 2010-4468,Hypersonic Applications of the Laminar-Turbulent Transition SST40th Fluid Dynamics Conference and Exhibit, Chicago, Illinois, JuneModel in ANSYS Fluent AIAA Hypersonic Transition Paper to be28, 2010. Marvin, J.G., Brown, J.L., and Gnoffo, P.A., “Experimentalpublished in 2020.Database with Baseline CFD Solutions: 2-D and AxisymmetricHypersonic Shock‐Wave/Turbulent‐Boundary‐Layer Interactions”,NASA/TM-2013-216604, NASA: Ames Research Center, MoffettField, CA, November 2013.Kurbatskii, K.A, Kumar, R., and Mann, D., “Simulation of ExternalHypersonic Problems Using FLUENT 6.3 Density-Based CoupledSolver”, 2nd European Conference for Aerospace Sciences.Hyp-12Hypersonic7.1902d axisymmetric Hypersonictransition on a Blunt ConeCylinder Flare junctionsame as aboveMacLean, M., Wadhams, T., Holden, M., and Johnson, H., “AComputational Analysis of Ground Test Studies of HIFiRE-1Transi
Feb 25, 2021 · Photo: NASA Langley Photo: US Air Force/Reuters The design of these maneuverable hypersonic interceptors requires extensive understanding of all of the physics involved and their interaction aerothermodynamics, struct
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