Heating Augmentation for Short Hypersonic Protuberances

Mazaheri, Alireza; Wood, William A.

doi:10.2514/6.2008-4255

Cited by 2 publications

(2 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The transport and thermodynamic properties in the flow-field environment were computed from species collision integrals [12][13][14] and curve fit data [15], respectively. Further details on the flow solver and previous applications can be found in the literature [16][17][18][19][20][21][22].…”

Section: Arc-jet Plenum Profile Estimationmentioning

confidence: 99%

Computational Predictions of the Hypersonic Material Environmental Test System Arcjet Facility

Brune

Bruce

Glass

et al. 2019

Journal of Thermophysics and Heat Transfer

View full text Add to dashboard Cite

The Hypersonic Materials Environmental Test System arc-jet facility located at the NASA Langley Research Center in Hampton, Virginia, is primarily used for the research, development, and evaluation of high-temperature thermal protection systems for hypersonic vehicles and reentry systems. In order to improve testing capabilities and knowledge of the test article environment, a detailed three-dimensional model of the arc-jet nozzle and free-jet portion of the flow field has been developed. The computational fluid dynamics model takes into account non-uniform inflow state profiles at the nozzle inlet as well as catalytic recombination efficiency effects at the probe surface. Results of the numerical simulations are compared to calibrated Pitot pressure and stagnation-point heat flux for three test conditions at low, medium, and high enthalpy. Comparing the results and test data indicates an effectively fully-catalytic copper surface on the heat flux probe of about 10% recombination efficiency and a 2-3 kPa pressure drop from the total pressure measured at the plenum section, prior to the nozzle. With these assumptions, the predictions are within the uncertainty of the stagnation pressure and heat flux measurements.The predicted velocity conditions at the nozzle exit were also compared and showed good agreement with radial and axial velocimetry data.

show abstract

Section: Arc-jet Plenum Profile Estimationmentioning

confidence: 99%

Computational Predictions of the Hypersonic Material Environmental Test System Arcjet Facility

Brune

Bruce

Glass

et al. 2019

Journal of Thermophysics and Heat Transfer

View full text Add to dashboard Cite

show abstract

“…All fluid flow simulations were computed with the Langley Aerothermodynamic Upwind Relaxation Algorithm (LAURA)-5 code. 11 LAURA-5 is a hypersonic viscous reacting flow solver that has been applied to analyze flight data in previous NASA missions, such as Fire II, 12 the Space Shuttle Orbiter, 13,14 and the Mars Science Laboratory (MSL), 15 and is being used in current programs, such as the Multi-Purpose Crew Vehicle (MPCV), 16 the Inflatable Reentry Vehicle Experiment-3 (IRVE-3), and the HEART vehicle. 17 During the CFD process, the computational grid was adapted and refined around the bow shock (Fig.…”

Section: Shockmentioning

confidence: 99%

Methodology for Flight-Relevant Arc-Jet Testing of Flexible Thermal Protection Systems

Mazaheri

Bruce

Mesick

et al. 2014

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

A methodology to correlate flight aeroheating environments to the arc-jet environment is presented. For a desired hot-wall flight heating rate, the methodology provides the arcjet bulk enthalpy for the corresponding cold-wall heating rate. A series of analyses were conducted to examine the effects of the test sample model holder geometry to the overall performance of the test sample. The analyses were compared with arc-jet test samples and challenges and issues are presented. The transient flight environment was calculated for the Hypersonic Inflatable Aerodynamic Decelerator (HIAD) Earth Atmospheric Reentry Test (HEART) vehicle, which is a planned demonstration vehicle using a large inflatable, flexible thermal protection system to reenter the Earth's atmosphere from the International Space Station. A series of correlations were developed to define the relevant arc-jet test environment to properly approximate the HEART flight environment. The computed arcjet environments were compared with the measured arc-jet values to define the uncertainty of the correlated environment. The results show that for a given flight surface heat flux and a fully-catalytic TPS, the flight relevant arc-jet heat flux increases with the arc-jet bulk enthalpy while for a non-catalytic TPS the arc-jet heat flux decreases with the bulk enthalpy.

show abstract

Heating Augmentation for Short Hypersonic Protuberances

Cited by 2 publications

References 3 publications

Computational Predictions of the Hypersonic Material Environmental Test System Arcjet Facility

Computational Predictions of the Hypersonic Material Environmental Test System Arcjet Facility

Methodology for Flight-Relevant Arc-Jet Testing of Flexible Thermal Protection Systems

Contact Info

Product

Resources

About