Requirements in the 1990's for high enthalpy ground test facilities for CFD validation

Neumann, Richard D.

doi:10.2514/6.1990-1401

Cited by 8 publications

(3 citation statements)

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“…Such a contamination is caused by two main mechanisms: 1) diffusion through the interface and 2) the so called "jetting" phenomenon. 6 As will be seen later, it was experimentally observed that this con40r tamination can be minimized by using a high molecular weight gas separating the driver gas from the driven gas. The use of this separating gas will also improve the final equilibrium condition achieved by this technique.…”

Section: Introductionmentioning

confidence: 95%

“…References 4 and 5 present the utilization of the described method for near ambient temperature helium drivers, while Ref. 6 reports the application of the technique to combustion heated helium drivers.…”

Section: Introductionmentioning

confidence: 99%

“…1 shows the energy requirements 1 for the flight duplication for a selected NASP trajectory. In order to meet this challenge the present investigation examines the utilization of a 1.22-m-diam Combustion Driver Hypersonic Shock Tunnel, 2 operating at an equilibrium interface Presented as Paper 92-0569 at the AIAA 30th Aerospace Sciences Meeting, Reno, NV, Jan. [6][7][8][9]1992; received Sept. 3,1992; revision received June 22, 1993; accepted for publication July 9, 1993. Copyright © 1992 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.…”

Section: Introductionmentioning

confidence: 99%

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Combustion shock tunnel and interface compression to increase reservoir pressure and enthalpy

Minucci¹,

Nagamatsu

Myrabo

1994

Journal of Thermophysics and Heat Transfer

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This article discusses the production of hypervelocitv -hypersonic flows in a combustion shock tunnel operating in the equilibrium interface mode. In this mode of operation, the additional compression provided by the approaching interface is used to obtain higher pressures and temperatures, as opposed to the reflected method. A computer code was developed to model the operation of a shock tunnel in the equilibrium interface condition. In this article, all the calculations were made for the Rensselaer Polytechnic Institute (RPI) 1.22-m-diam Combustion Driver Hypersonic Shock Tunnel. The major drawback of the interface compression technique, which is the contamination of the driven gas by the driver gas, was overcome through the utilization of a small volume region separating the two gases. Numerical results indicate that the RPI facility will be able to generate reservoir temperatures of the order of 20,000 K and reservoir pressures of the order of 30,000 psi. These reservoir conditions can be used to produce test section Mach numbers of 35. A h M P T Nomenclature cross-sectional area specific enthalpy Mach number pressure absolute temperature Subscripts c = corrected for area change at diaphragm station s -incident shock conditions t -shock tube conditions 1 = driven tube initial conditions 4 = driver tube postcombustion conditions 5 = reflected conditions oo = freestream conditions Superscripts , = equilibrium interface conditions * = nozzle throat conditions

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Section: Introductionmentioning

confidence: 95%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Combustion shock tunnel and interface compression to increase reservoir pressure and enthalpy

Minucci¹,

Nagamatsu

Myrabo

1994

Journal of Thermophysics and Heat Transfer

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Verification and validation in computational fluid dynamics

Oberkampf

Trucano

2002

Progress in Aerospace Sciences

837

360

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Verification and validation (V&V) are the primary means to assess accuracy and reliability in computational simulations. This paper presents an extensive review of the literature in V&V in computational fluid dynamics (CFD), discusses methods and procedures for assessing V&V, and develops a number of extensions to existing ideas. The review of the development of V&V terminology and methodology points out the contributions from members of the operations research, statistics, and CFD communities. Fundamental issues in V&V are addressed, such as code verification versus solution verification, model validation versus solution validation, the distinction between error and uncertainty, conceptual sources of error and uncertainty, and the relationship between validation and prediction. The fundamental strategy of verification is the identification and quantification of errors in the computational model and its solution. In verification activities, the accuracy of a computational solution is primarily measured relative to two types of highly accurate solutions: analytical solutions and highly accurate numerical solutions. Methods for determining the accuracy of numerical solutions are presented and the importance of software testing during verification activities is emphasized. The fundamental strategy of 1 Accepted for publication in the review journal Progress in Aerospace Sciences.3 validation is to assess how accurately the computational results compare with the experimental data, with quantified error and uncertainty estimates for both. This strategy employs a hierarchical methodology that segregates and simplifies the physical and coupling phenomena involved in the complex engineering system of interest. A hypersonic cruise missile is used as an example of how this hierarchical structure is formulated. The discussion of validation assessment also encompasses a number of other important topics. A set of guidelines is proposed for designing and conducting validation experiments, supported by an explanation of how validation experiments are different from traditional experiments and testing. A description is given of a relatively new procedure for estimating experimental uncertainty that has proven more effective at estimating random and correlated bias errors in wind-tunnel experiments than traditional methods. Consistent with the authors' contention that nondeterministic simulations are needed in many validation comparisons, a three-step statistical approach is offered for incorporating experimental uncertainties into the computational analysis. The discussion of validation assessment ends with the topic of validation metrics, where two sample problems are used to demonstrate how such metrics should be constructed. In the spirit of advancing the state of the art in V&V, the paper concludes with recommendations of topics for future research and with suggestions for needed changes in the implementation of V&V in production and commercial software.4 Acknowledgements

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Hypersonic shock-tunnel testing at an equilibrium interface condition of 4100 K

Minucci¹,

Nagamatsu

1993

Journal of Thermophysics and Heat Transfer

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Requirements in the 1990's for high enthalpy ground test facilities for CFD validation

Cited by 8 publications

References 8 publications

Combustion shock tunnel and interface compression to increase reservoir pressure and enthalpy

Combustion shock tunnel and interface compression to increase reservoir pressure and enthalpy

Verification and validation in computational fluid dynamics

Hypersonic shock-tunnel testing at an equilibrium interface condition of 4100 K

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