Supersonic Retropropulsion Experimental Results from NASA Ames 9×7 Foot Supersonic Wind Tunnel

Berry, Scott A.; Rhode, Matthew N.; Edquist, Karl T.

doi:10.2514/1.a32650

Cited by 20 publications

(8 citation statements)

References 17 publications

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“…The data surveyed inform the effects of variations in nozzles, nozzle configurations, and aerodynamics parameters, primarily sourced from NASA wind tunnel testing conducted in the era of the Viking Mars lander development [1,[7][8][9][10]. A pair of NASA wind tunnel tests in 2010 and 2011 expanded upon legacy efforts through parametric investigation of single and multiple nozzle configurations across a range of supersonic Mach numbers and thrust coefficients [4,5]. This most recent testing incorporated modern pressure instrumentation and examined a number of multiple nozzle arrangements and a range of flow conditions.…”

Section: Evaluation Of Srp Ai Scaling Parametersmentioning

confidence: 99%

“…However, several of the tests incorporated variations in nozzle and/or model geometry. In contrast, the recent NASA testing was specifically designed to provide experimental data to be used for validation of computational fluid dynamics (CFD) codes and to re-establish the capability to investigate these interference effects through ground testing [4,5]. This testing also incorporated variations in nozzle (and therefore plume) configuration without replication of the historical references for multiple nozzle data.…”

Section: Evaluation Of Srp Ai Scaling Parametersmentioning

confidence: 99%

“…Retropropulsion, or the firing of rocket engines or motors into the direction of flight, is a method of spacecraft deceleration and soft landing that dates back to the early 1960s [1]. Use of retropropulsion during atmospheric flight has reemerged as a technology development objective over the past decade [1][2][3][4][5][6]. Two candidate applications have driven this resurgent interest:…”

Section: Introductionmentioning

confidence: 99%

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Scaling and Similitude in Single Nozzle Supersonic Retropropulsion Aerodynamics Interference

Korzun

Cassel

2020

AIAA Scitech 2020 Forum

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Retropropulsion, or the firing of rocket engines or motors into the direction of flight, is a method of spacecraft deceleration and soft landing that dates back to the early 1960s. Current conceptual designs for landing humans on the surface of Mars require supersonic retropropulsion, or initiation of retropropulsion at supersonic freestream conditions, as part of an extended powered descent phase of flight. The objective of this work is to identify the design parameters and flow condition bounds for self-similar behavior of powered descent aerodynamic interference in relevant flight environments. In applications of sub-scale test data, an "unknown" uncertainty lies in scaling to and from full-scale environments and systems. The issue of scaling for the opposing flows characteristic of powered descent is the focus of the following analysis, using data from wind tunnel testing of configurations with a single, central nozzle as a point of departure.

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Section: Evaluation Of Srp Ai Scaling Parametersmentioning

confidence: 99%

Section: Evaluation Of Srp Ai Scaling Parametersmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Scaling and Similitude in Single Nozzle Supersonic Retropropulsion Aerodynamics Interference

Korzun

Cassel

2020

AIAA Scitech 2020 Forum

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“…The first cell off the vehicle has the same height as the adjacent cell at the nozzle exit. The parameters stretch, N k,2 and N k, 3 in Table 2 may be used to control the position of the elliptical inflow boundary to accommodate large penetrations of the jet into the free stream. The resulting grid for configuration C1 is shown in Figs.…”

Section: A Single Axisymmetric Conical Nozzlementioning

confidence: 99%

Tapping the Brake for Entry, Descent, and Landing

Gnoffo

Thompson

Korzun

2016

46th AIAA Fluid Dynamics Conference

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A matrix of simulations of hypersonic flow over blunt entry vehicles with steady and pulsing retropropulsion jets is presented. Retropropulsion in the supersonic domain is primarily designed to reduce vehicle velocity directly with thrust. Retropropulsion in the hypersonic domain may enable significant pressure recovery through unsteady, oblique shocks while providing a buffer of reactant gases with relatively low total temperature. Improved pressure recovery, a function of Mach number squared and oblique shock angle, could potentially serve to increase aerodynamic drag in this domain. Pulsing jets are studied to include an additional degree of freedom to search for resonances in an already unsteady flow domain with an objective to maximize the time-averaged drag coefficient. In this paradigm, small jets with minimal footprints of the nozzle exit on the vehicle forebody may be capable of delivering the requisite perturbations to the flow. Simulations are executed assuming inviscid, symmetric flow of a perfect gas to enable a rapid assessment of the parameter space (nozzle geometry, plenum conditions, jet pulse frequency). The pulsedjet configuration produces moderately larger drag than the constant jet configuration but smaller drag than the jet-off case in this preliminary examination of a single design point. The fundamentals of a new algorithm for this challenging application with time dependent, interacting discontinuities using the feature detection capabilities of Walsh functions are introduced.

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“…In addition to the UPWT test at high supersonic Mach number conditions, data were also obtained in a LaRC-led test at lower supersonic Mach numbers in the Ames Research Center (ARC) 9x7-Foot Supersonic Wind Tunnel (Ref. 67). The model used in the prior LaRC UPWT test was also used in this study.…”

Section: B Supersonic Retropropulsionmentioning

confidence: 99%

Entry, Descent and Landing Aerothermodynamics: NASA Langley Experimental Capabilities and Contributions

Hollis

Berger

Berry

et al. 2014

52nd Aerospace Sciences Meeting

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A review is presented of recent research, development, testing and evaluation activities related to entry, descent and landing that have been conducted at the NASA Langley Research Center. An overview of the test facilities, model development and fabrication capabilities, and instrumentation and measurement techniques employed in this work is provided. Contributions to hypersonic/supersonic flight and planetary exploration programs are detailed, as are fundamental research and development activities.

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Supersonic Retropropulsion Experimental Results from NASA Ames 9×7 Foot Supersonic Wind Tunnel

Cited by 20 publications

References 17 publications

Scaling and Similitude in Single Nozzle Supersonic Retropropulsion Aerodynamics Interference

Scaling and Similitude in Single Nozzle Supersonic Retropropulsion Aerodynamics Interference

Tapping the Brake for Entry, Descent, and Landing

Entry, Descent and Landing Aerothermodynamics: NASA Langley Experimental Capabilities and Contributions

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