Simulation of hypersonic shock wave laminar boundary layer interaction on hollow cylinder flare, Part II

Nadia Kianvashrad, Doyle Knight

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Citations (Scopus)

Abstract

Recent interest in hypersonic flight has focused attention on the capability of CFD models for predicting non-equilibrium hypersonic shock wave laminar boundary layer interactions. A recent set of experiments performed at the Calspan University of Buffalo Research Center (CUBRC) provide a test matrix for assessment of CFD models. Experimental data include surface heat transfer and surface pressure. Previous CFD simulations by several researchers have shown significant discrepancies with experimental peak surface heat transfer and surface pressure. The present research examines the effect of non-equilibrium translational-vibrational energy transfer and effect of temperature dependency of specific heat capacity (cp) and transport models (viscosity (µ) and thermal conductivity (k)) on the prediction of surface heat transfer and surface pressure for a hollow cylinder flare con- figuration at Mach numbers from 11.5 to 13.2 and stagnation enthalpies from 10.43 to 21.85 MJ/kg. Including the energy exchange between translational and vibrational modes has negligible effect on surface pressure and surface heat transfer for these experiments. However, the temperature dependency of specific heat and transport model has significant effect on prediction of peak surface pressure and surface heat transfer.

Original languageEnglish (US)
Title of host publication47th AIAA Fluid Dynamics Conference, 2017
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105005
StatePublished - Jan 1 2017
Event47th AIAA Fluid Dynamics Conference, 2017 - Denver, United States
Duration: Jun 5 2017Jun 9 2017

Publication series

Name47th AIAA Fluid Dynamics Conference, 2017

Other

Other47th AIAA Fluid Dynamics Conference, 2017
CountryUnited States
CityDenver
Period6/5/176/9/17

Fingerprint

Laminar boundary layer
Hypersonic aerodynamics
Shock waves
Heat transfer
Specific heat
Computational fluid dynamics
Engine cylinders
Energy transfer
Mach number
Enthalpy
Thermal conductivity
Experiments
Viscosity
Temperature

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Engineering (miscellaneous)

Cite this

Kianvashrad, N., & Knight, D. (2017). Simulation of hypersonic shock wave laminar boundary layer interaction on hollow cylinder flare, Part II. In 47th AIAA Fluid Dynamics Conference, 2017 (47th AIAA Fluid Dynamics Conference, 2017). American Institute of Aeronautics and Astronautics Inc, AIAA.
Kianvashrad, Nadia ; Knight, Doyle. / Simulation of hypersonic shock wave laminar boundary layer interaction on hollow cylinder flare, Part II. 47th AIAA Fluid Dynamics Conference, 2017. American Institute of Aeronautics and Astronautics Inc, AIAA, 2017. (47th AIAA Fluid Dynamics Conference, 2017).
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Kianvashrad, N & Knight, D 2017, Simulation of hypersonic shock wave laminar boundary layer interaction on hollow cylinder flare, Part II. in 47th AIAA Fluid Dynamics Conference, 2017. 47th AIAA Fluid Dynamics Conference, 2017, American Institute of Aeronautics and Astronautics Inc, AIAA, 47th AIAA Fluid Dynamics Conference, 2017, Denver, United States, 6/5/17.

Simulation of hypersonic shock wave laminar boundary layer interaction on hollow cylinder flare, Part II. / Kianvashrad, Nadia; Knight, Doyle.

47th AIAA Fluid Dynamics Conference, 2017. American Institute of Aeronautics and Astronautics Inc, AIAA, 2017. (47th AIAA Fluid Dynamics Conference, 2017).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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Kianvashrad N, Knight D. Simulation of hypersonic shock wave laminar boundary layer interaction on hollow cylinder flare, Part II. In 47th AIAA Fluid Dynamics Conference, 2017. American Institute of Aeronautics and Astronautics Inc, AIAA. 2017. (47th AIAA Fluid Dynamics Conference, 2017).