Comparison of SLS Sectional Loads from Pressure-Sensitive Paint and CFD

Meeroff, Jamie G.; Lee, Henry; Dalle, Derek J.; Rogers, Stuart E.; Roozeboom, Nettie; Baerny, Jennifer

doi:10.2514/6.2019-2127

Cited by 5 publications

(1 citation statement)

References 5 publications

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“…The goal of the current work is to assess PSP by performing direct comparisons with one of the CFD tools that has already been used to produce multiple aero ascent databases on the present Block 1B crew vehicle and other related vehicles. Two related papers will provide detailed comparisons between the wind-tunnel test and CFD simulations focused on force and moment measurements [1] and sectional loads [2].…”

Section: Introductionmentioning

confidence: 99%

Comparison of Space Launch System Aerodynamic Surface Pressure Measurements from Experimental Testing and CFD

McMillin

Shea

Dalle

et al. 2019

AIAA Scitech 2019 Forum

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Section: Introductionmentioning

confidence: 99%

Comparison of Space Launch System Aerodynamic Surface Pressure Measurements from Experimental Testing and CFD

McMillin

Shea

Dalle

et al. 2019

AIAA Scitech 2019 Forum

Self Cite

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Exhaust Gas and Plume Modeling Effects for Space Launch System Abort Scenarios

Boustani,

Applebaum,

Eppard

et al. 2024

Journal of Spacecraft and Rockets

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Viscous computational fluid dynamics simulations depicting Space Launch System post Mode-1 abort scenarios are conducted and analyzed. The purpose of these simulations is to study the effect of attitude control motor and abort motor plume modeling on the drag of the aborted core stage. The simulations are first conducted with a multispecies and chemically reacting thermodynamic model. Following this, equivalent species are created for the exhaust gases. These equivalent species aim to provide results for core stage drag similar to the chemically reacting model at a lower computational cost. Finally, the exhaust gases are modeled as calorically perfect air. Under most scenarios, both simplified models predict the drag on the core stage close to that predicted by the chemically reacting simulations. In these cases, the flow conditions do not induce significant changes in the composition of the exhaust gas via afterburning. For simulations in which this is not the case, the properties of the simplified models deviate from the true mixture, yielding unsatisfactory results. Finally, the chemically reacting model is weighed against the associated increase in computational costs. The simplified models are at least four times less computationally expensive than the reacting model.

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Ascent Aerodynamic Force and Moment Database Development for the Space Launch System

Shea

Pinier

Houlden

et al. 2019

AIAA Aviation 2019 Forum

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The Space Launch System Aerodynamics Task Team is responsible for delivering aerodynamic force and moment databases from liftoff through ascent until the rocket leaves the Earth's atmosphere. The process for developing the ascent portion of this database is described in the current paper. The data used to develop the database were generated using a combination of wind tunnel testing and CFD simulations. The details of the wind tunnel testing performed at the NASA Ames Unitary Plan Wind Tunnel and CFD simulations performed using FUN3D at wind tunnel and flight conditions are discussed, and comparisons of these data sets are provided. The methods used for converting the source data into the final database response surfaces with corresponding uncertainty are also detailed.

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Comparison of SLS Sectional Loads from Pressure-Sensitive Paint and CFD

Cited by 5 publications

References 5 publications

Comparison of Space Launch System Aerodynamic Surface Pressure Measurements from Experimental Testing and CFD

Comparison of Space Launch System Aerodynamic Surface Pressure Measurements from Experimental Testing and CFD

Exhaust Gas and Plume Modeling Effects for Space Launch System Abort Scenarios

Ascent Aerodynamic Force and Moment Database Development for the Space Launch System

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