Surface Catalysis and Oxidation on Stagnation Point Heat Flux Measurements in High Enthalpy Arc Jets

Nawaz, Anuscheh; Driver, David M.; Terrazas-Salinas,

doi:10.2514/6.2013-3138

Cited by 32 publications

(20 citation statements)

References 19 publications

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“…In 2013 Nawaz et al [40] confirmed that exposing the copper calorimeters to a flow inside an arc-jet for only 2-3 sec is sufficient to create an oxidized layer, this is shown in Fig. 3.10.…”

Section: Chapter 3 Experimental Research In Catalycitymentioning

confidence: 78%

“…The former is black in color whereas the latter is red. This distinction is rather important since copper can oxidize in either of the two with different catalytic behavior as discussed by Nawaz et al [40]. When considering the catalytic efficiencies of copper and copper oxide for oxygen in Table 3.3, it can be seen that there is a significant variation in the values.…”

Section: Copper and Copper Oxide Catalytic Efficiencymentioning

confidence: 91%

“…The oxide layer causes the red color, hence a darker red color corresponds to a thicker layer. It was noted by Nawaz et al [40] that even though the slug used at 5 MJ/kg does not show any color change, after XPS analysis it was found that oxidation has taken place.…”

Section: Chapter 3 Experimental Research In Catalycitymentioning

confidence: 99%

“…A significant amount of research has been conducted on the catalytic efficiency of copper and copper oxide, summarized in Table 3.3 which has been based mainly on the table made by Nawaz et al [40]. It should be noted that several authors only mentioned "room temperature" in their papers.…”

Section: Copper and Copper Oxide Catalytic Efficiencymentioning

confidence: 99%

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Nitrogen Catalytic Recombination on Copper Oxide in Tertiary Gas Mixtures

Cheung

Schrijer

Park

2016

Journal of Spacecraft and Rockets

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PrefaceThis master thesis represents the work that I have conducted at KAIST (Republic of Korea) from July 2013 until December 2013 and August 2014 until March 2015. During these period I have studied the field of aerothermodynamics, learned the necessary steps to conduct experiments individually, explored and studied various numerical programs to fulfill the goal of this research. This thesis is the final step in the journey to acquire the degree of Master of Science in Aerospace Engineering at Delft University of Technology.This report consists of three main parts. One part discusses the shock tube and the fabrication of heat transfer gauges. The second part introduces the numerical programs which are used to simulate the conditions inside the shock tube and around the model, whereas the third part covers the theory regarding heat flux and catalycity. These three parts together form a chain of required steps to acquire the desired results for this thesis.

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Section: Chapter 3 Experimental Research In Catalycitymentioning

confidence: 78%

Section: Copper and Copper Oxide Catalytic Efficiencymentioning

confidence: 91%

Section: Chapter 3 Experimental Research In Catalycitymentioning

confidence: 99%

Section: Copper and Copper Oxide Catalytic Efficiencymentioning

confidence: 99%

See 2 more Smart Citations

Nitrogen Catalytic Recombination on Copper Oxide in Tertiary Gas Mixtures

Cheung

Schrijer

Park

2016

Journal of Spacecraft and Rockets

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“…For values lower than 0.1 the uncertainties become larger. Panerai [9] at Plasmatron and Nawaz et al [28] show that the copper catalycity for the reference condition is lower than 0.1. Therefore, this conventional method is ruled out for the reference condition of this study.…”

Section: Plasmatron Measurements and Uncertainty Characterizationmentioning

confidence: 99%

Hypersonic Aerothermochemistry Duplication in Ground Plasma Facilities: A Flight-to-Ground Approach

Sakraker

Turchi

Chazot

2015

Journal of Spacecraft and Rockets

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High conservative safety margins, applied to the design of spacecraft thermal protection systems for planetary entry, need to be reduced for higher efficiency of future space missions. Ground testing of such protection systems is of great importance during the design phase. This study covers a methodology for simulating the complex hypersonic entry aerothermochemistry in a plasma wind tunnel for a given spacecraft geometry without any assumption on axisymmetry or bluntness. A demonstration of this proposed methodology is made on the Qubesat for Aerothermodynamic Research and Measurements on AblatioN, QARMAN mission, which is a rectangular reentry CubeSat with a cork-based ablative thermal protection system in the front unit. The reacting boundary-layer profiles of the hypersonic entry probe compare well with the ones developing at the stagnation region of the plasma test model, defined with the proposed flight-to-ground duplication method.

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