Assessment of predictive capabilities for aerodynamic heating in hypersonic flow

Knight, Doyle; Chazot, Olivier; Austin, Joanna; Badr, Mohammad Ali; Candler, Graham V.; Çelik, Bayram; Rosa, Donato De; Donelli, Raffaele; Komives, Jeffrey R.; Lani, Andrea; Levin, Deborah A.; Nompelis, Ioannis; Panesi, Marco; Pezzella, Giuseppe; Reimann, Bodo; Tumuklu, Ozgur; Yuceil, K. B.

doi:10.1016/j.paerosci.2017.02.001

Cited by 72 publications

(25 citation statements)

References 40 publications

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“…In particular, Figure 5 points out that CFD predicts well the recirculation bubble and the peak heat transfer location, but the numerical value is about 43% of that measured during the experiment [10].…”

Section: Advances In Some Hypersonic Vehicles Technologiesmentioning

confidence: 88%

See 1 more Smart Citation

Launcher Aerodynamics: A Suitable Investigation Approach at Phase-A Design Level

Pezzella¹,

Viviani²

2018

Advances in Some Hypersonic Vehicles Technologies

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This chapter deals with launcher aerodynamic design activities at phase-A level. The goal is to address the preliminary aerodynamic database of a typical launch vehicle configuration as input for launcher performances evaluations, control, sizing, and staging design activities. In this framework, different design approaches relying on both engineering and numerical methods are considered. Indeed, engineering-based aerodynamic analyses by means of a three-dimensional panel methods code, based on local surface inclination theory, were performed. Then, accuracy of design analysis increased using steady-state computational fluid dynamics with both Euler and Navier-Stokes approximations.

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Section: Advances In Some Hypersonic Vehicles Technologiesmentioning

confidence: 88%

“…This is typical for the Edney type IV interaction. After the peak, the pressure suddenly drops toward the asymptotic pressure due to the strong expansion at the end of ramp [10].…”

Section: Advances In Some Hypersonic Vehicles Technologiesmentioning

confidence: 99%

Launcher Aerodynamics: A Suitable Investigation Approach at Phase-A Design Level

Pezzella¹,

Viviani²

2018

Advances in Some Hypersonic Vehicles Technologies

Self Cite

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“…The inter-species relaxation time is taken from Millikan and White [30]. As in most previous studies [16], we assume the flow to be laminar due to the low Reynolds number (Re ∼ 10 3 − 10 4 ).…”

Section: Modelsmentioning

confidence: 99%

“…In Komives et al [18], a three-dimensional calculation of the case was performed to 50 flow-times where strong three-dimensional effects at the separation region were observed; however, a very high CFL number of 100 was used in this work, and the results are not considered time-accurate. Although the study of Levin and Tumuklu (see Knight et al [16]) also suggested that there might be important spanwise effects, there is not enough experimental information to confirm this and modern studies still focus on 2D simulations. The study of Khraibut and Gai [22] achieved steady-state solutions beyond experimental test times for the 8 MJ/kg cases, and although good agreement is obtained with both nitrogen and air, the reattachment heat transfer peak was under-predicted.…”

Section: Introductionmentioning

confidence: 99%

Computational investigations into heat transfer over a double wedge in hypersonic flows

Exposito

Rana

2019

Aerospace Science and Technology

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Recently developed OpenFOAM application hy2FOAM is employed to predict the aerodynamic heat transfer numerically and compared with the experimental data from the University of Illinois. Mach 7 nitrogen flow at 2.1 MJ/kg stagnation enthalpy, and Mach 7 nitrogen and air flows at 8 MJ/kg stagnation enthalpy over a double wedge geometry have been reproduced numerically assuming chemical and thermal non-equilibrium. Good agreement of mean heat transfer profiles has been observed, although none of the simulations achieved a steady-state. The reattachment heat transfer peak in the high enthalpy air case showed an improved agreement with the experimental data, which is due to the non-equilibrium in the flow field.

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“…Measurements of transitional SBLI are exceedingly difficult due to the inherent three-dimensionality and non-linear processes. 41,42 However, with modern advancements in computational capability and experimental techniques there is a renewed interest in transitional SBLI.…”

Section: Boundary-layer Transition Measurements Through a Finite mentioning

confidence: 99%

Measurements in the Boeing/AFOSR Mach-6 Quiet Tunnel on Hypersonic Boundary-Layer Transition

Chynoweth

Edelman

Gray

et al. 2017

47th AIAA Fluid Dynamics Conference

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This paper presents results from four different research projects currently ongoing at Purdue University. (1) Different criteria for detecting the edge of the boundary layer were investigated on the flared cone geometry. It was determined that a method based on the total enthalpy profile would be used for future edge-detection computations on the flared cone geometry. A Rod Insertion Method (RIM) roughness insert was measured using a Zygo ZeGage optical profiler. Experimental results with a single RIM insert are presented. Maximum second-mode magnitudes of nearly 27% were measured 2.5 cm upstream from where spectral filling and intermittency algorithms compute that transition has begun. (2) Preliminary data from a new model shows that high-frequency secondary instabilities of stationary crossflow waves are localized under the troughs of the stationary vortices. Measurements of the growth of the secondary instabilities are reported for two different vortices. (3) In order to better understand the effects that probe geometry has on measured pressure fluctuations, pitot measurements were taken using various sleeves which alter the forward-facing diameter of the probe. The results indicate a clear effect of probe size on the measured power spectral densities. Furthermore, it was found that the geometry effects are Reynolds number dependent. (4) Experiments on a cone with a slice and ramp were completed to determine if transitional shock wave-boundary layers interactions can be measured within the Boeing/AFOSR Mach-6 Quiet Tunnel. Initial experiments showed that with a newly designed model it is possible to measure transitional interactions.

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Assessment of predictive capabilities for aerodynamic heating in hypersonic flow

Cited by 72 publications

References 40 publications

Launcher Aerodynamics: A Suitable Investigation Approach at Phase-A Design Level

Launcher Aerodynamics: A Suitable Investigation Approach at Phase-A Design Level

Computational investigations into heat transfer over a double wedge in hypersonic flows

Measurements in the Boeing/AFOSR Mach-6 Quiet Tunnel on Hypersonic Boundary-Layer Transition

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