Plume and Shock Interaction Effects on Sonic Boom in the 1-foot by 1-foot Supersonic Wind Tunnel

Castner, Raymond S.; Elmiligui, Alaa A.; Cliff, Susan E.; Winski, Courtney S.

doi:10.2514/6.2015-1046

Cited by 7 publications

(8 citation statements)

References 8 publications

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“…The plume and shock interaction study was developed to collect data for CFD validation where a nozzle plume passed through the shock generated from the wing or tail of a supersonic vehicle. Major findings of the study demonstrated how the interaction of the jet plume caused a thickening, or widening [6], of the shock generated by the wedge or aft deck, and movement of the shock location with increasing nozzle pressure ratio. There were, however, some concerns with the data.…”

Section: Introductionmentioning

confidence: 95%

“…The double wedge shock generator was a scaled-up version (1.5 times) of the shock generator used in the Glenn Research Center (GRC) 1x1 test [6], to allow for a similar test case between the two tests. The double wedge generated a strong shock, but it is not representative of a modern day horizontal tail design.…”

Section: B Modelmentioning

confidence: 99%

“…Castner [5] later performed a CFD analysis that showed the impact that either an overexpanded or an underexpanded nozzle flow had on the shape of the N-wave. Testing was then conducted at the NASA Glenn Research Center in the 1x1 Supersonic Wind Tunnel to understand the effects of a shock passing through a nozzle flow [6]. The plume and shock interaction study was developed to collect data for CFD validation where a nozzle plume passed through the shock generated from the wing or tail of a supersonic vehicle.…”

Section: Introductionmentioning

confidence: 99%

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Computational and Experimental Study of Plume and Shock Interaction Effects on Sonic Boom in the NASA Ames 9x7 Supersonic Wind Tunnel

Winski

Carter

Elmiligui

et al. 2018

2018 AIAA Aerospace Sciences Meeting

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A wind tunnel test was performed in the NASA Ames 9x7 Supersonic Wind Tunnel focusing on the shock waves traveling through and interacting with an exhaust nozzle plume. This experimental study was conducted to develop and validate the CFD capability required to accurately include nozzle flow with impinging shock effects on near field and ground-propagated sonic boom signatures. The model was made to be generic, and included a simple nozzle shape, two different aft decks, and a few generic horizontal tails. High pressure air was pumped through a nozzle at various nozzle pressure ratios (NPR) to represent the engine plume in flight. The three different aft body representations each created a different shock wave signature that passed through the plume. An aft deck configuration, where part of the aircraft shields the nozzle plume, was also tested. Retroreflective Background-Oriented Schlieren (RBOS) was used to obtain schlieren images of the flow field around the model and behind the model. This study compares wind tunnel data and numerical simulations conducted by the NASA Tetrahedral Unstructured Software System CFD code, USM3D.

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Section: Introductionmentioning

confidence: 95%

Section: B Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Computational and Experimental Study of Plume and Shock Interaction Effects on Sonic Boom in the NASA Ames 9x7 Supersonic Wind Tunnel

Winski

Carter

Elmiligui

et al. 2018

2018 AIAA Aerospace Sciences Meeting

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“…Since this tunnel's capability to test small-scale models was developed to validate results obtained for supersonic nozzle concepts 4 , it was chosen as the facility to obtain fundamental data on nozzle plume and shock interaction effects. The testing conducted used a simple jet flow and simulated tail shock generated by a wedge shaped shock generator.…”

Section: Introductionmentioning

confidence: 99%

Computational and Experimental Study of Supersonic Nozzle Flow and Shock Interactions

Carter

Elmiligui

Nayani

et al. 2015

53rd AIAA Aerospace Sciences Meeting

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This study focused on the capability of NASA Tetrahedral Unstructured Software System's CFD code USM3D capability to predict the interaction between a shock and supersonic plume flow. Previous studies, published in 2004, 2009 and 2013, investigated USM3D's supersonic plume flow results versus historical experimental data. This current study builds on that research by utilizing the best practices from the early papers for properly capturing the plume flow and then adding a wedge acting as a shock generator. This computational study is in conjunction with experimental tests conducted at the Glenn Research Center 1'x1' Supersonic Wind Tunnel. The comparison of the computational and experimental data shows good agreement for location and strength of the shocks although there are vertical shifts between the data sets that may be do to the measurement technique.

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“…The capability to test small-scale models in NASA GRC's 1-foot by 1-foot supersonic wind tunnel (1x1 SWT) was developed to validate results obtained for supersonic nozzle concepts. This capability was utilized for a fundamental study of the nozzle plume and shock interaction effects 11 . Analysis was performed on the experimental configuration using the Cart3D CFD code.…”

Section: Introductionmentioning

confidence: 99%

Cart3D Analysis of Plume and Shock Interaction Effects on Sonic Boom

Castner

2015

33rd AIAA Applied Aerodynamics Conference

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A plume and shock interaction study was developed to collect data and perform CFD on a configuration where a nozzle plume passed through the shock generated from the wing or tail of a supersonic vehicle. The wing or tail was simulated with a wedge-shaped shock generator. Three configurations were analyzed consisting of two strut mounted wedges and one propulsion pod with an aft deck from a low boom vehicle concept. Research efforts at NASA were intended to enable future supersonic flight over land in the United States. Two of these efforts provided data for regulatory change and enabled design of low boom aircraft. Research has determined that sonic boom is a function of aircraft lift and volume distribution. Through careful tailoring of these variables, the sonic boom of concept vehicles has been reduced. One aspect of vehicle tailoring involved how the aircraft engine exhaust interacted with aft surfaces on a supersonic aircraft, such as the tail and wing trailing edges. In this work, results from Euler CFD simulations are compared to experimental data collected on sub-scale components in a wind tunnel. Three configurations are studied to simulate the nozzle plume interaction with representative wing and tail surfaces. Results demonstrate how the plume and tail shock structure moves with increasing nozzle pressure ratio. The CFD captures the main features of the plume and shock interaction. Differences are observed in the plume and deck shock structure that warrant further research and investigation. Nomenclature

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Plume and Shock Interaction Effects on Sonic Boom in the 1-foot by 1-foot Supersonic Wind Tunnel

Cited by 7 publications

References 8 publications

Computational and Experimental Study of Plume and Shock Interaction Effects on Sonic Boom in the NASA Ames 9x7 Supersonic Wind Tunnel

Computational and Experimental Study of Plume and Shock Interaction Effects on Sonic Boom in the NASA Ames 9x7 Supersonic Wind Tunnel

Computational and Experimental Study of Supersonic Nozzle Flow and Shock Interactions

Cart3D Analysis of Plume and Shock Interaction Effects on Sonic Boom

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