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  • 1
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    Development of computational methods for heavy lift launch vehicles (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The research effort has been focused on the development of an advanced flow solver for complex viscous turbulent flows with shock waves. The three-dimensional Euler and full/thin-layer Reynolds-averaged Navier-Stokes equations for compressible flows are solved on structured hexahedral grids. The Baldwin-Lomax algebraic turbulence model is used for closure. The space discretization is based on a cell-centered finite-volume method augmented by a variety of numerical dissipation models with optional total variation diminishing limiters. The governing equations are integrated in time by an implicit method based on lower-upper factorization and symmetric Gauss-Seidel relaxation. The algorithm is vectorized on diagonal planes of sweep using two-dimensional indices in three dimensions. A new computer program named CENS3D has been developed for viscous turbulent flows with discontinuities. Details of the code are described in Appendix A and Appendix B. With the developments of the numerical algorithm and dissipation model, the simulation of three-dimensional viscous compressible flows has become more efficient and accurate. The results of the research are expected to yield a direct impact on the design process of future liquid fueled launch systems.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-CR-192298 , NAS 1.26:192298 , MCAT-93-03
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Development and validation of CNS (compressible Navier-Stokes) for hypersonic external flows (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: CNS, a new computational fluid dynamics procedure, has been developed to aid in hypersonic vehicle design. The code can be used to model the entire external flow around hypersonic vehicle shapes, from the captured shock at the nose to the beginning of the wake. Unlike space-marching codes, the technique allows axially separated flow regions to be modeled. Validation trials using sphere-cone data reveal good solution accuracy for the surface pressure and flowfield temperature.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-1839
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    CFD research, parallel computation and aerodynamic optimization (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Over five years of research in Computational Fluid Dynamics and its applications are covered in this report. Using CFD as an established tool, aerodynamic optimization on parallel architectures is explored. The objective of this work is to provide better tools to vehicle designers. Submarine design requires accurate force and moment calculations in flow with thick boundary layers and large separated vortices. Low noise production is critical, so flow into the propulsor region must be predicted accurately. The High Speed Civil Transport (HSCT) has been the subject of recent work. This vehicle is to be a passenger vehicle with the capability of cutting overseas flight times by more than half. A successful design must surpass the performance of comparable planes. Fuel economy, other operational costs, environmental impact, and range must all be improved substantially. For all these reasons, improved design tools are required, and these tools must eventually integrate optimization, external aerodynamics, propulsion, structures, heat transfer and other disciplines.
    Keywords: AERODYNAMICS
    Type: NASA-CR-197748 , NAS 1.26:197748 , MCAT-95-18
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    CFD Research, Parallel Computation and Aerodynamic Optimization (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: During the last five years, CFD has matured substantially. Pure CFD research remains to be done, but much of the focus has shifted to integration of CFD into the design process. The work under these cooperative agreements reflects this trend. The recent work, and work which is planned, is designed to enhance the competitiveness of the US aerospace industry. CFD and optimization approaches are being developed and tested, so that the industry can better choose which methods to adopt in their design processes. The range of computer architectures has been dramatically broadened, as the assumption that only huge vector supercomputers could be useful has faded. Today, researchers and industry can trade off time, cost, and availability, choosing vector supercomputers, scalable parallel architectures, networked workstations, or heterogenous combinations of these to complete required computations efficiently.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-CR-200760 , NAS 1.26:200760 , Rept-95-18
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Hypersonic flow analysis (1987)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: While the zonal grid system of Transonic Navier-Stokes (TNS) provides excellent modeling of complex geometries, improved shock capturing, and a higher Mach number range will be required if flows about hypersonic aircraft are to be modeled accurately. A computational fluid dynamics (CFD) code, the Compressible Navier-Stokes (CNS), is under development to combine the required high Mach number capability with the existing TNS geometry capability. One of several candidate flow solvers for inclusion in the CNS is that of F3D. This upwinding flow solver promises improved shock capturing, and more accurate hypersonic solutions overall, compared to the solver currently used in TNS.
    Keywords: AERODYNAMICS
    Type: NASA-CR-181332 , NAS 1.26:181332
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Parallel computation of 3-D Navier-Stokes flowfields for supersonic vehicles (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Multidisciplinary design optimization of aircraft will require unprecedented capabilities of both analysis software and computer hardware. The speed and accuracy of the analysis will depend heavily on the computational fluid dynamics (CFD) module which is used. A new CFD module has been developed to combine the robust accuracy of conventional codes with the ability to run on parallel architectures. This is achieved by parallelizing the ARC3D algorithm, a central-differenced Navier-Stokes method, on the Intel iPSC/860. The computed solutions are identical to those from conventional machines. Computational speed on 64 processors is comparable to the rate on one Cray Y-MP processor and will increase as new generations of parallel computers become available.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-0064 , AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States|; 13 p.
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    High speed civil transport aerodynamic optimization (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This is a report of work in support of the Computational Aerosciences (CAS) element of the Federal HPCC program. Specifically, CFD and aerodynamic optimization are being performed on parallel computers. The long-range goal of this work is to facilitate teraflops-rate multidisciplinary optimization of aerospace vehicles. This year's work is targeted for application to the High Speed Civil Transport (HSCT), one of four CAS grand challenges identified in the HPCC FY 1995 Blue Book. This vehicle is to be a passenger aircraft, with the promise of cutting overseas flight time by more than half. To meet fuel economy, operational costs, environmental impact, noise production, and range requirements, improved design tools are required, and these tools must eventually integrate optimization, external aerodynamics, propulsion, structures, heat transfer, controls, and perhaps other disciplines. The fundamental goal of this project is to contribute to improved design tools for U.S. industry, and thus to the nation's economic competitiveness.
    Keywords: AERODYNAMICS
    Type: NASA-CR-196960 , NAS 1.26:196960
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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