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Cart3D simulations for the first AIAA sonic boom prediction workshop 52

Cart3D simulations for the first AIAA sonic boom prediction ...

引用

52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014

作者： Aftosmis, Michael J. Nemecy, Marian NASA Ames Applied Modeling and Simulation Branch Moffett Field CA 94035 United States Science and Technology Corp Applied Modeling and Simulation Branch Moffett Field CA 94035 United States

ISBN: (数字)9781624102561

ISBN: (纸本)9781624102561

simulation results for the First AIAA Sonic Boom Prediction Workshop are presented using an inviscid, embedded-boundary Cartesian mesh method. The method employs adjoint-based error estimation and adaptive meshing to automatically determine resolu- tion requirements for each simulation. Results are presented for both mandatory and optional test cases. These include a low-boom body of revolution, a 69 delta wing model and a model of the Lockheed supersonic tri-jet with V-tail and flow-through nacelles. Inaddition to signature data, each example includes an assessment of mesh independence of the near- and mid-fleld pressure signatures. We also show mesh convergence of the adapta- tion functional and demonstrate that both the adjoint correction and remaining error are vanishing as the mesh is refined. Data provided include both the pressure signals required by the workshop and information on code performance in terms of processing time and memory usage. In addition, the discussion demonstrates useful techniques for prediction of extreme off-track pressure signatures and an adjoint-based technique for tracing features of the off-body pressure signature back to speciffic portions of the geometry and flow field.

关键词： Forecasting

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Inviscid and viscous CFD analysis of booster separation for the space launch system vehicle 54

Inviscid and viscous CFD analysis of booster separation for ...

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54th AIAA Aerospace Sciences Meeting, 2016

作者： Dalle, Derek J. Rogers, Stuart E. Chan, William M. Lee, Henry L. Applied Modeling & Simulation Branch Science and Technology Corp NASA Ames Research Center Moffett FieldCA94035 United States Applied Modeling & Simulation Branch NASA Ames Research Center Moffett FieldCA94035 United States

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Skylon aerospace plane and its aerodynamics and plumes

Skylon aerospace plane and its aerodynamics and plumes

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作者： Mehta, Unmeel Aftosmis, Michael Bowles, Jeffrey Pandya, Shishir NASA Ames Research Center Advanced Supercomputing Division Moffett FieldCA94035 United States Applied Modeling and Simulation Branch United States System Analysis Branch United States Fundamental Modeling and Simulation Branch United States

The Skylon concept incorporates the highly innovative synergetic air-breathing rocket engine concept that has the potential to revolutionize the mode of propulsion for transportation of medium-weight payloads to low Earth orbits. An independent partial assessment is provided of the technical viability of the Skylon concept. Pressure lift and drag coefficients derived from Euler simulations for unpowered flight compare very well and fairly well, respectively, with those from engineering methods. The engineering-method coefficients for powered flight are increasingly less acceptable as the freestream Mach number is increased beyond 8.5 because these methods did not account for the increasing favorable (in terms of pressure forces) effect of underexpanded rocket engine plumes on the aft fuselage. At Mach numbers greater than 8.5, the thermal environment around the aft fuselage is a known unknown: A potential design and/or performance risk issue. The adverse effects of shock waves on the aft fuselage and plume-induced flow separation are other potential risks. A preliminary design of Skylon requires the judicious use of a combination of engineering methods, advanced methods based on required physics or analytical fidelity, test data, and independent assessments. The demonstration of a synergetic air-breathing rocket-engine-powered experimental aerospace plane calls for the second revival of the Aerospace Plane Program. Copyright © 2015 by the American Institute of Aeronautics and Astronautics Inc. All rights reserved.

关键词： Rockets

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Detached eddy simulation of the UH-60 rotor wake using adaptive mesh refinement

Detached eddy simulation of the UH-60 rotor wake using adapt...

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68th American Helicopter Society International Annual Forum 2012

作者： Chaderjian, Neal M. Ahmad, Jasim U. Fundamental Modeling and Simulation Branch NASA Ames Research Center Moffett Field CA 94035 United States Applied Modeling and Simulation Branch NASA Ames Research Center Moffett Field CA 94035 United States

ISBN: (纸本)9781622760510

Time-dependent Navier-Stokes flow simulations have been carried out for a UH-60 rotor with simplified hub in forward flight and hover flight conditions. Flexible rotor blades and flight trim conditions are modeled and established by loosely coupling the OVERFLOW Computational Fluid Dynamics (CFD) code with the CAMRAD II helicopter comprehensive code. High order spatial differences, Adaptive Mesh Refinement (AMR), and Detached Eddy simulation (DES) are used to obtain highly resolved vortex wakes, where the largest turbulent structures are captured. Special attention is directed towards ensuring the dual time accuracy is within the asymptotic range, and verifying the loose coupling convergence process using AMR. The AMR/DES simulation produced vortical worms for forward flight and hover conditions, similar to previous results obtained for the TRAM rotor in hover. AMR proved to be an efficient means to capture a rotor wake without apriori knowledge of the wake shape.

关键词： Wakes

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Verification and validation studies for the LAVA CFD solver

Verification and validation studies for the LAVA CFD solver

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21st AIAA Computational Fluid Dynamics Conference

作者： Moini-Yekta, Shayan Barad, Michael F. Sozer, Emre Brehm, Christoph Housman, Jeffrey A. Kiris, Cetin C. Applied Modeling and Simulation Branch NASA Ames Research Center Moffett Field CA 94035 United States Applied Modeling and Simulation Branch Science and Technology Corporation Moffett Field CA 94035 United States Mechanical and Aeronautical Engineering University of California Davis United States

Verification and validation studies applied to the Launch Ascent and Vehicle Aerodynamics (LAVA) computational fluid dynamics (CFD) solver is presented. A modern strategy for verification and validation is implemented incorporating verification tests, validation benchmarks, continuous integration and version control methods for automated testing in a collaborative development environment. The purpose of the approach is to integrate the verification and validation process into the development of the solver and improve productivity. The procedure uses the Method of Manufactured Solutions (MMS) for the verification of 2D Euler equations and 3D Navier-Stokes equations. A method for systematic refinement of unstructured grids is also presented. Inviscid vortex propagation and flow over a flat plate are included in the verification study. simulation results using laminar and turbulent flow past a NACA 0012 airfoil and ONERA M6 wing are validated against experimental data compare to existing numerical results.

关键词： Computational fluid dynamics

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Skylon airframe aerodynamics and SABRE plumes 20th

Skylon airframe aerodynamics and SABRE plumes

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20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015

作者： Mehta, Unmeel Aftosmis, Michael Bowles, Jeffrey Pandya, Shishir NASA Ames Research Center Moffett FieldCA94035 United States NASA Advanced Supercomputing Division United States Applied Modeling and Simulation Branch United States System Analysis Branch United States Fundamental Modeling and Simulation Branch United States

ISBN: (纸本)9781624103209

An independent partial assessment is provided of the viability of the Skylon aerospace plane concept, developed by Reaction Engines Limited (REL). The objectives are to verify REL’s engineering estimates of airframe aerodynamics during powered flight and to assess the impact of Synergetic Air-Breathing Rocket Engine (SABRE) plumes on the aft fuselage. Airframe lift and drag coefficients derived from simulations conducted with Euler equations for unpowered flight compare very well with those REL computed with engineering methods. The REL coefficients for powered flight are increasingly less acceptable as the freestream Mach number is increased beyond 8.5, because the engineering estimates did not account for the increasing favorable (in terms of drag and lift coefficients) effect of under-expanded rocket engine plumes on the aft fuselage. At Mach numbers greater than 8.5, the thermal environment around the aft fuselage is a potential high-risk issue. The adverse effects of shock waves on the aft fuselage and plume-induced flow separation are other potential design and performance risks. The mitigation of these risks may require changes in the design of the Skylon concept and its operation during flight. © 2015, AIAA American Institute of Aeronautics and Astronautics. All rights Reserved.

关键词： Rockets

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CFD-based computations of flexible helicopter blades for stability analysis

CFD-based computations of flexible helicopter blades for sta...

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52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

作者： Guruswamy, Guru P. NASA Advanced Supercomputing Division Ames Research Center Applied Modeling and Simulation Branch Moffett Field CA United States

ISBN: (纸本)9781600869518

As a collaborative effort among government aerospace research laboratories, an advanced version of a widely used computational fluid dynamics code, OVERFLOW2.1z, was recently released. This latest version includes additions to model multiple flexible, rotating blades. This paper describes how the OVERFLOW code is applied to improve the accuracy of airload computations from the linear lifting line theory that uses displacements from the beam model. In the case used, data transfers required at every revolution are managed through a Unix-based script that runs jobs on large supercluster computers. Results are demonstrated for the 4-bladed UH-60A helicopter, deviations of computed data from flight data are evaluated, and Fourier analysis post-processings suitable for aeroelastic stability computations are performed. Use of airload data for flutter speed computations needed for stability analysis is demonstrated for a typical section of a blade.

关键词： Research laboratories

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Large scale aeroelastic data for design of rotating blades using Navier-Stokes equations 12

Large scale aeroelastic data for design of rotating blades u...

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12th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference and 14th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference

作者： Guruswamy, Guru P. NASA Advanced Supercomputing Division Ames Research Center Applied Modeling and Simulation Branch Moffett Field CA United States

ISBN: (数字)9781600869303

ISBN: (纸本)9781600869303

Bending-torsion flutter boundaries for rotating blades are computed using unsteady aerodynamic data obtained by time accurately solving the Navier-Stokes equations. A modal approach is used for computing the flutter boundary. Flutter speeds are computed by solving eigenvalue equations that track down the system damping to identify flutter point. Aerodynamic data required for the analysis is computed by time accurately integrating aerodynamic equations while the blades are undergoing modal motions at various oscillating frequencies. Validity of the approach is established by comparing the flutter speed results with those measured for a non-rotating blade. Results are demonstrated for a typical rotating blade. Parallel computing resources are utilized to cope with computational costs associated with use of the Navier-Stokes equations.

关键词： Navier Stokes equations

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Fluid/structure interaction modeling of helicopters using Navier Stokes equations

Fluid/structure interaction modeling of helicopters using Na...

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AIAA modeling and simulation Technologies Conference 2012

作者： Guruswamy, Guru P. Applied Modeling and Simulation Branch NASA Advanced Supercomputing Division Ames Research Center Moffett Field CA United States

ISBN: (纸本)9781624101830

A time-accurate procedure to model fluid/structure interactions of helicopter blades is presented. The Navier-Stokes equations in conjunction with the one-equation Spalart-Allmaras turbulence model are used to compute the flow. Structural dynamics is modeled using the modal equations. The aerodynamic and structural dynamic equations are coupled time-accurately using the linear acceleration method of Newmark direct integration scheme. Effects of time accuracy on the computed results are investigated. Results are compared with experimental data for a full rotor blade system.

关键词： Structural dynamics

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Static aeroelastic analysis with an inviscid cartesian method 55

Static aeroelastic analysis with an inviscid cartesian metho...

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55th AIAA/ASMe/ASCE/AHS/SC Structures, Structural Dynamics, and Materials Conference - SciTech Forum and Exposition 2014

作者： Rodriguez, David L. Aftosmis, Michael J. Nemec, Marian Smith, Stephen C. Science and Technology Corp Applied Modeling and Simulation Branch MS 258-5 Moffett Field CA 94305 United States NASA Ames Research Center Applied Modeling and Simulation Branch MS 258-5 Moffett Field CA 94305 United States Zee Aero Mountain View CA 94043 United States

ISBN: (数字)9781624103148

An embedded-boundary, Cartesian-mesh flow solver is coupled with a three degree-offreedom structural model to perform static, aeroelastic analysis of complex aircraft geometries. The approach solves a nonlinear, aerostructural system of equations using a looselycoupled strategy. An open-source, 3-D discrete-geometry engine is utilized to deform a triangulated surface geometry according to the shape predicted by the structural model under the computed aerodynamic loads. The deformation scheme is capable of modeling large deflections and is applicable to the design of modern, very-flexible transport wings. The coupling interface is modular so that aerodynamic or structural analysis methods can be easily swapped or enhanced. After verifying the structural model with comparisons to Euler beam theory, two applications of the analysis method are presented as validation. The first is a relatively stiff, transport wing model which was a subject of a recent workshop on aeroelasticity. The second is a very flexible model recently tested in a low speed wind tunnel. Both cases show that the aeroelastic analysis method produces results in excellent agreement with experimental data.

关键词： Aeroelasticity

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