Comparative Heat Flux Measurements Between Three Hypersonic Test Facilities at NAL

Kuchi-Ishi, Shigeru; Watanabe, Shigeya; Nakakita, Kazuyuki; Koyama, Tadao; Ueda, Shuichi; Itoh, Katsuhiro

doi:10.2514/6.2003-4254

Cited by 7 publications

(6 citation statements)

References 8 publications

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“…10 together with a result obtained using the 1.27 m hypersonic wind tunnel in JAXA (1.27 m HWT) using a larger HB-2 model. 5) Except for a constant difference, the agreement for variation with the angle of attack seems good.…”

Section: Aerodynamic Characteristics Of the Hb-2 Modelmentioning

confidence: 94%

Aerodynamic Force Extraction from Shock Tunnel Measurements Using the Oscillation Identification Technique

Watari¹

2007

Trans. Japan Soc. Aero. S Sci.

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Force measurements using internal balances in a hypersonic shock tunnel are contaminated by inertial forces exerted by model oscillations. It is essential to extract aerodynamic forces from oscillation-contaminated short-period measurement data. This paper proposes an oscillation identification technique method. It was assumed that the inertial forces are exponentially decreasing sinusoidal oscillations, and therefore a parameter-matching technique was applied to identify the oscillation characteristics. This method was verified by applying it to standard HB-2 model measurements.

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Section: Aerodynamic Characteristics Of the Hb-2 Modelmentioning

confidence: 94%

Aerodynamic Force Extraction from Shock Tunnel Measurements Using the Oscillation Identification Technique

Watari¹

2007

Trans. Japan Soc. Aero. S Sci.

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“…While not focused on direct comparative measurements, there are a limited number of studies in which both thin film and thermocouple surface heat transfer data are available. In a recent study at the National Aerospace Laboratory in Japan, both coaxial and thin film thermocouples were used to compare the operation of the Hypersonic Wind Tunnel, the High Enthalpy Shock Tube, and the Hypersonic Shock Tube to establish guidelines for the use of the facilities [31]. The thermocouple data were found to be in good agreement with IR thermography, and the non-dimensional heat transfer agreed to within a few percent between all three facilities.…”

Section: Previous Implementation Of Heat Transfer Gagesmentioning

confidence: 97%

Yip-08 Hypervelocity Boundary Layer Studies for Axisymmetric Engine Flowpaths

Austin¹,

Flaherty²

2011

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“…To validate, the hybrid solver, a standard AGARD HB-2 model, which is a sphere-cone-cylinder-flare geometry, with a core diameter of 100mm as shown in Fig. 1 is chosen and for which hypersonic wind tunnel data [18] are available in the open literature. The experiments are conducted in JAXA 1.27 m blow-down cold type hypersonic wind tunnel and one of the objectives of the tests is for generating good quality experimental results for HB-2 geometry, which would serve as benchmark for hypersonic computational fluid dynamics codes.…”

Section: Problem Definitionmentioning

confidence: 99%

Computation of Heat Flux in Hypersonic Flow with a Cartesian Mesh Using Near-Wall Resolution

Ashok,

Joseph,

Adimurthy

2023

joast

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A hybrid solution methodology is developed to solve laminar hypersonic flow with a Cartesian mesh approach. The hybrid grid consisting of a Cartesian mesh together with an unstructured prism layer near the wall to capture the large gradients close to the surface is used for the near wall viscous resolution. The prism layer is generated by extruding the panels formed by the intersection of the Cartesian grid and the body and is stitched with the outer Cartesian mesh away from the wall for solving axi-symmetric flows. For three dimensional flows, since the prism layer cells are not stitched to the outer Cartesian mesh, the inviscid solution is carried out first for background Cartesian mesh and later this solution is mapped to the extruded prism layer cells and laminar Navier-Stokes solution is carried out for the prism layer cells alone. The developed solver gives an unstructured prism layer solution near the wall and standard Cartesian mesh solution away from the wall. This hybrid solution methodology is validated against the experimentally measured heat flux data and could predict the heat flux with good accuracy. The present methodology thus enables the computation of a viscous solution using a Cartesian mesh based approach.

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Comparative Heat Flux Measurements Between Three Hypersonic Test Facilities at NAL

Cited by 7 publications

References 8 publications

Aerodynamic Force Extraction from Shock Tunnel Measurements Using the Oscillation Identification Technique

Aerodynamic Force Extraction from Shock Tunnel Measurements Using the Oscillation Identification Technique

Yip-08 Hypervelocity Boundary Layer Studies for Axisymmetric Engine Flowpaths

Computation of Heat Flux in Hypersonic Flow with a Cartesian Mesh Using Near-Wall Resolution

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