Mach Number Determination in a High-Enthalpy Supersonic Arc-Heated Plasma Wind Tunnel

Chinnaraj, Rajesh Kumar; Oh, Phil Yong; Shin, Eui Sup; Hong, Bong Guen; Choi, Seong Man

doi:10.1007/s42405-018-0128-x

Cited by 7 publications

(5 citation statements)

References 8 publications

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“…The PWT used for this study is a 0.4 MW class segmented-type arc-jet plasma PWT, capable of producing supersonic plasma flows in the range of either Mach 2 or Mach 3, depending on the dimensions of the convergent-divergent flow exit nozzle used. The exit nozzle used for this study has an exit diameter of 16 mm and a throat diameter of 10.6 mm, which produces supersonic flow in the range of Mach 2 [ 39 ]. The main components of the PWT system are a gas supply manifold, segmented type arc plasma torch, vacuum test chamber, diffuser, heat exchanger, cooling water supply, DC power supply, and vacuum pump system.…”

Section: Methodsmentioning

confidence: 99%

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Arc-Jet Tests of Carbon–Phenolic-Based Ablative Materials for Spacecraft Heat Shield Applications

2023

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We developed and tested two carbon–phenolic-based ablators for future Korean spacecraft heat shield applications. The ablators are developed with two layers: an outer recession layer, fabricated from carbon–phenolic material, and an inner insulating layer, fabricated either from cork or silica–phenolic material. The ablator specimens were tested in a 0.4 MW supersonic arc-jet plasma wind tunnel at heat flux conditions ranging from 6.25 MW/m2 to 9.4 MW/m2, with either specimen being stationary or transient. Stationary tests were conducted for 50 s each as a preliminary investigation, and the transient tests were conducted for ~110 s each to stimulate a spacecraft’s atmospheric re-entry heat flux trajectory. During the tests, each specimen’s internal temperatures were measured at three locations: 25 mm, 35 mm, and 45 mm from the specimen stagnation point. During the stationary tests, a two-color pyrometer was used to measure specimen stagnation-point temperatures. During the preliminary stationary tests, the silica–phenolic-insulated specimen’s reaction was normal compared to the cork-insulated specimen; hence, only the silica–phenolic-insulated specimens were further subjected to the transient tests. During the transient tests, the silica–phenolic-insulated specimens were stable, and the internal temperatures were lower than 450 K (~180 °C), achieving the main objective of this study.

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Section: Methodsmentioning

confidence: 99%

“…The extrusion of the generated air plasma through the convergent–divergent exit nozzle into the test chamber resulted in a supersonic air plasma flow to which the specimens were exposed. Additional details on the PWT specifications and schematics can be found in [ 39 , 40 ]. Table 1 shows the PWT operating conditions used for this study.…”

Section: Methodsmentioning

confidence: 99%

Arc-Jet Tests of Carbon–Phenolic-Based Ablative Materials for Spacecraft Heat Shield Applications

2023

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“…By virtue of the high pressure difference between the plasma torch and the test chamber, the hot air plasma exited the plasma torch's convergent-divergent nozzle as a supersonic high enthalpy plasma flow, to which the specimen was exposed. More details on JBNU's 0.4 MW supersonic arc-jet PWT operating procedures, specifications and schematics can be found in [35,36].…”

Section: Methodsmentioning

confidence: 99%

“…In all conducted tests, the internal temperature data showed that each specimen's internal temperatures were higher than the room temperature of 293.15 K (20 • C) moments before their exposure to the plasma test flow. The reason for this is an increase in ambient temperature inside the PWT test chamber caused by the generation of the plasma test flow, as the plasma test flow temperature was measured previously as 4350 K [35]. In the case of specimen Hemi-15-1, there was a considerable delay in its exposure to the plasma test flow after the start of plasma generation.…”

Section: Hemispherical-faced Specimen Stationary Testsmentioning

confidence: 95%

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Thermal Behavior of Carbon-Phenolic/Silica Phenolic Dual-Layer Ablator Specimens through Arc-Jet Tests

Chinnaraj,

Kim,

Choi

2023

Materials

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We studied the behavioral characteristics of a newly developed dual-layer ablator, which uses carbon-phenolic as a recession layer and silica-phenolic as an insulating layer. The ablator specimens were tested in a 0.4 MW supersonic arc-jet plasma wind tunnel, employing two different shapes (flat-faced and hemispherical-faced) and varying thicknesses of the carbon-phenolic recession layer. The specimens underwent two test conditions, namely, stationary tests (7.5 MW/m2, ~40 s) and transient tests simulating an interplanetary spacecraft re-entry heat flux trajectory (6.25↔9.4 MW/m2, ~108 s). During the stationary tests, stagnation point temperatures of the specimens were measured. Additionally, internal temperatures of the specimens were measured at three locations for both stationary and transient tests: inside the carbon-phenolic recession layer, inside the silica-phenolic insulating layer, and at the recession layer–insulating layer intersection. The hemispherical-faced specimen surface temperatures were about 3000 K, which is about 350 K higher than those of flat-faced specimens, resulting in higher internal temperatures. The recession layer internal temperatures rose more exponentially when moved closer to the specimen stagnation point. Layer interaction and insulating layer internal temperatures were found to be dependent on both the recession layer thickness and the exposed surface shape. The change in exposed surface shape increased mass loss and recession, with hemispherical-faced specimens showing ~1.4-fold higher values than the flat-faced specimens.

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Ablation Experiments of Ultra-High-Temperature Ceramic Coating on Carbon–Carbon Composite Using ICP Plasma Wind Tunnel

Chinnaraj

Hong

Kim

et al. 2020

Int. J. Aeronaut. Space Sci.

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Mach Number Determination in a High-Enthalpy Supersonic Arc-Heated Plasma Wind Tunnel

Cited by 7 publications

References 8 publications

Arc-Jet Tests of Carbon–Phenolic-Based Ablative Materials for Spacecraft Heat Shield Applications

Arc-Jet Tests of Carbon–Phenolic-Based Ablative Materials for Spacecraft Heat Shield Applications

Thermal Behavior of Carbon-Phenolic/Silica Phenolic Dual-Layer Ablator Specimens through Arc-Jet Tests

Ablation Experiments of Ultra-High-Temperature Ceramic Coating on Carbon–Carbon Composite Using ICP Plasma Wind Tunnel

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