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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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Noise characteristics of a four-jet impingement device inside a broadband engine noise simulator 21st

Noise characteristics of a four-jet impingement device insid...

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21st AIAA/CEAS Aeroacoustics Conference, 2015

作者： Brehm, Christoph Housman, Jeffrey A. Kiris, Cetin C. Hutcheson, Florence V. Applied Modeling and Simulation Branch NAS Division MS N258-2 Science and Technology Corporation Moffett FieldCA94035 United States Applied Modeling and Simulation Branch NAS Division MS N258-2 NASA Ames Research Center Moffett FieldCA94035 United States Aeroacoustic Branch NASA Langley Research Center HamptonVA23681 United States

ISBN: (纸本)9781624103674

The noise generation mechanisms for four directly impinging supersonic jets are investigated employing implicit large eddy simulations with a higher-order accurate weighted essentially non-oscillatory shock-capturing scheme. Impinging jet devices are often used as an experimental apparatus to emulate a broadband noise source. Although such devices have been used in many experiments, a detailed investigation of the noise generation mechanisms has not been conducted before. Thus, the underlying physical mechanisms that are responsible for the generation of sound waves are not well understood. The flow field is highly complex and contains a wide range of temporal and spatial scales relevant for noise generation. Proper orthogonal decomposition of the flow field is utilized to characterize the unsteady nature of the flow field involving unsteady shock oscillations, large coherent turbulent flow structures, and the sporadic appearance of vortex tubes in the center of the impingement region. The causality method based on Lighthill’s acoustic analogy is applied to link fluctuations of flow quantities inside the source region to the acoustic pressure in the far field. It will be demonstrated that the entropy fluctuation term in the Lighthill’s stress tensor plays a vital role in the noise generation process. Consequently, the understanding of the noise generation mechanisms is employed to develop a reduced-order linear acoustic model of the four-jet impingement device. Finally, three linear acoustic FJID models are used as broadband noise sources inside an engine nacelle and the acoustic scattering results are validated against far-field acoustic experimental data. © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Flow fields

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Numerical simulation of bolide entry with ground footprint prediction 54

Numerical simulation of bolide entry with ground footprint p...

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54th AIAA Aerospace Sciences Meeting, 2016

作者： Aftosmis, Michael J. Nemec, Marian Mathias, Donovan L. Berger, Marsha J. Computational Aerosciences Branch NASA Ames Moffett FieldCA United States Applied Modeling and Simulation Branch Science & Tech. Corp Moffett FieldCA United States NASA Ames Moffett FieldCA United States Courant Institute NYU 251 Mercer St. NY United States

ISBN: (数字)9781624103933

ISBN: (纸本)9781624103933

As they decelerate through the atmosphere, meteors transfer mass, momentum and energy into the surrounding air at tremendous rates. The entry of such bolides produces strong blast waves that can propagate hundreds of kilometers and cause substantial terrestrial damage even when no ground impact occurs. We develop a new technique for meteoroid airburst modeling based upon conservation analysis for the deposition of mass, momentum and energy. These sources are then used to drive simulations of blast propagation using a fully-conservative, finite-volume solver on a multilevel Cartesian mesh. We examine the ability of this method to accurately propagate the blast over hundreds of kilometers of terrain. Initial verification of the method is presented through the canonical problem of a spherical charge. A detailed reconstruction of the 2013 Chelyabinsk meteor provides additional validation. These simulations show very good prediction of the surface overpressure and blast arrival times throughout the ground footprint. Further investigations examine the impact of simplifications to the modeling on both accuracy and computational efficiency using a line-source blast model and a static spherical charge. Both approaches are shown to be useful simplifications and limitations on their use are discussed. © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA . All rights reserved.

关键词： Computational efficiency

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Development and application of the SAFEDI tool for virtual dynamic interface ship airwake analysis 54

Development and application of the SAFEDI tool for virtual d...

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54th AIAA Aerospace Sciences Meeting, 2016

作者： Polsky, Susan A. Wilkinson, Colin H. Nichols, James Ayers, Douglas Mercado-Perez, Johana Davis, T. Scott Naval Air Systems Command Applied Aerodynamics and Store Separation Branch 48110 Shaw Rd. Suite 1320B Patuxent RiverMD20670 United States Naval Air Systems Command Flight Vehicles Modeling and Simulation Branch 48183 Switzer Rd Bldg 2035 Patuxent RiverMD20670 United States American Systems 22289 Exploration Drive Suite 401 Lexington ParkMD20653 United States

ISBN: (数字)9781624103933

ISBN: (纸本)9781624103933

Dynamic interface refers to shipboard aircraft launch and recovery operations including the testing required to determine flight envelope limits as a function of wind speed and direction. Ship-based flight operations must contend with challenges unique to the maritime environment such as ship motion and airwake turbulence created by the ship’s superstructure. Ship airwake affects aircraft performance and handling qualities characteristics which in turn impact pilot workload. Ship airwake characteristics vary from ship to ship and also from one relative wind angle to the next for the same ship. The ability to assess ship airwake severity in a simulation environment allows airwake related design considerations, such as ship geometric layout and aircraft flight control design, to be addressed during the design process. NAVAIR has developed a desktop airwake analysis tool to model the handling characteristics of an aircraft when subjected to time accurate ship airwake velocities created with Computational Fluid Dynamics (CFD). The tool has been applied to multiple ship configurations to assess airwake impact on both rotary wing and fixed wing aircraft. This work describes the real-time aircraft flight dynamics models and CFD airwake models that make up the airwake evaluation tool, summarizes verification and validation efforts, and describes the comparative process used to evaluate ship airwake severity for an example ship configuration. © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA, All rights reserved.

关键词： Fixed wings

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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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Optimized off-design performance of flexible wings with continuous trailing-edge flaps 56

Optimized off-design performance of flexible wings with cont...

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56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 2015

作者： Rodriguez, David L. Aftosmis, Michael J. Nemec, Marian Anderson, George R. Applied Modeling and Simulation Branch Science and Technology Corp MS 258-5 Moffett FieldCA94035 United States Applied Modeling and Simulation Branch NASA Ames Research Center MS 258 Moffett FieldCA94035 United States Aeronautics and Astronautics Stanford University StanfordCA94305 United States

ISBN: (数字)9781624103421

ISBN: (纸本)9781624103421

This work assesses the potential aerodynamic performance benefits of a variablecamber, continuous-trailing-edge flap system on a generic transport aircraft at off-design conditions. A process to optimize transport wings while addressing static aeroelastic effects is presented. To establish a proper baseline, a transport wing is first aerodynamically optimized at a mid-cruise flight condition using an inviscid, aeroelastic analysis tool. The optimized wing is then analyzed at off-design cruise conditions. The optimization is repeated at these off-design conditions to determine how much performance is lost by the wing optimized solely for the mid-cruise condition. The full-span flap system is then adapted to maximize performance of the mid-cruise-optimized wing at these off-design conditions. The measured improvement is quantified by a comparison with wings designed specifically for the off-design conditions. To evaluate the effects of aeroelasticity on the effectiveness of the flap system, this entire process is performed on both a conventionally stiff wing and a modern, more flexible wing. The results indicate that the flap system allows for recovery of near-optimal performance throughout cruise and is found to be advantageous even for wings with increased flexibility. Moreover, the flaps appear to provide a means for active wave drag reduction during flight. © 2015, American Institute of Aeronautics and Astronautics Inc. All rights reserved.

关键词： Flexible wings

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Aerodynamic shape optimization benchmarks with error control and automatic parameterization 53

Aerodynamic shape optimization benchmarks with error control...

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53rd AIAA Aerospace Sciences Meeting, 2015

作者： Anderson, George R. Nemec, Marian Aftosmis, Michael J. Stanford University Department of Aeronautics and Astronautics StanfordCA United States Science and Technology Corp. Applied Modeling and Simulation Branch MS 258-5 Moffett FieldCA United States NASA Ames Research Center Applied Modeling and Simulation Branch MS 258-5 Moffett FieldCA United States

ISBN: (数字)9781624103438

ISBN: (纸本)9781624103438

Results are presented for four optimization benchmark problems posed by the AIAA Aerodynamic Design Optimization Discussion Group. The benchmarks involve drag minimization for airfoils and wings, subject to geometric and aerodynamic constraints. Our design approach involves two forms of adaptation. First, the shape parameterization is gradually and automatically enriched from a coarse initial search space. Second, adjoint solutions are used to drive adaptive mesh refinement to control discretization error. The highest-resolution parameterizations and the finest, most accurate flow meshes are each used only when nearing the optimum, thus introducing greater complexity and accuracy only when necessary to further improve the design. The first benchmark is an inviscid airfoil design problem, where we reduce the drag by a factor of 10. This example also shows how the combination of progressive parameterization and tiered discretization error control can dramatically accelerate the optimization. Next, we improve the span efficiency factor of a straight wing in inviscid flow by optimizing the twist distribution. On a viscous transonic airfoil design problem, we use an inviscid optimization approach to substantially reduce the total drag of the viscous solution. Finally, we perform automatic, multistage optimization of the Common Research Model wing, managing to hold drag roughly fixed while meeting a substantially more restrictive pitching moment constraint. This work demonstrates the ability of our shape optimization system to solve representative aerodynamic design problems, using automatic flow meshing and shape parameterization refinement. © 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Parameterization

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Numerical simulations of shock/plume interaction using structured overset grids 33

Numerical simulations of shock/plume interaction using struc...

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33rd AIAA applied Aerodynamics Conference, 2015

作者： Housman, Jeffrey A. Kiris, Cetin C. Applied Modeling and Simulation Branch NAS Division NASA Ames Research Center Moffett Field M/S 258-2 CA94035 United States

ISBN: (数字)9781624103636

ISBN: (纸本)9781624103636

Computational simulations using structured overset grids with the Launch Ascent and Vehicle Aerodynamics (LAVA) solver framework are presented for predicting oblique shock/plume interaction effects to near-field sonic boom signatures. Standard second-order accurate as well as higher-resolution numerical discretizations are utilized and the results are compared with supersonic wind-tunnel data. The cases studied include an empty wind- tunnel at the operating conditions, an isolated shock-generating diamond wedge within the tunnel, and a nozzle with diamond wedge configuration at five different nozzle pressure ratios. Solution sensitivity to numerical discretization is analyzed. Favorable comparisons between the computational results and experimental data of near-field pressure signatures are obtained. A simple prediction method for plume induced shock deection is developed and results are compared with the CFD data. © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Wind tunnels

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Adaptive shape control for aerodynamic design 56

Adaptive shape control for aerodynamic design

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56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 2015

作者： Anderson, George R. Aftosmis, Michael J. Dept of Aeronautics and Astronautics Stanford University CA United States Applied Modeling and Simulation Branch NASA Ames Research Center MS 258-5 Moffett FieldCA United States

ISBN: (数字)9781624103421

ISBN: (纸本)9781624103421

We present an approach to aerodynamic optimization in which the shape parameterization is progessively and automatically refined. The process consists of an alternating sequence of optimizing within the current search space, and then refining the parameterization to enable the discovery of superior designs. We show that this approach reduces computational cost by optimizing in search spaces of appropriate dimensionality. By automating time-consuming aspects of shape control refinement, it also reduces human cost and dependence on designer expertise. In addition to uniform shape control refinement, we also discuss adaptive refinement, where the goal is to selectively add only the shape control with the most potential to improve the aerodynamic performance. Potential design improvement is estimated by comparing local objective and constraint gradients, which are computed at low cost by reusing existing adjoint solutions. A priority queue of the most effective candidate shape parameters is then maintained using an efficient constructive search procedure. We first demonstrate adaptive shape control on an multipoint airfoil drag miminization problem with many constraints, where our system achieves equivalent design improvement to a fine, fixed parameterization, but in one-third of the wall-clock time. We also establish a 3D shape-matching benchmark, in which our system automatically discovers the shape parameters necessary to match a target shape. This approach is an important step towards greater automation in solving the unfamiliar aerodynamic shape design problems of the future. © 2015, American Institute of Aeronautics and Astronautics Inc. All rights Reserved.

关键词： Parameterization

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