Wedge Shock and Nozzle Exhaust Plume Interaction in a Supersonic Jet Flow

Castner, Raymond S.; Zaman, K. B. M. Q.; Fagan, A. L.; Heath, Christopher M.

doi:10.2514/1.c033623

Cited by 7 publications

(3 citation statements)

References 27 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The propulsion system for this study includes an external compression inlet, VCE, and CD variable geometry nozzle. Note that FUN3D has been used previously to model inlet and nozzle components [20][21][22][23][24]. The new feature in this work is the inclusion of the dynamic effects of the propulsion system turbomachinery, a schematic of which is shown in Fig.…”

Section: Propulsion System Modelmentioning

confidence: 99%

Aero-Propulso-Elastic Analysis of a Supersonic Transport

Connolly¹,

Kopasakis²,

Chwalowski³

et al. 2020

Journal of Aircraft

View full text Add to dashboard Cite

An aeroelastic modeling capability of a flexible aircraft with gas turbine engines is developed using a computational fluid dynamics tool as an integration platform. The new modeling capability allows for the typical aeroelastic analysis to include a nonlinear dynamic model of the turbomachinery that is capable of capturing relevant gas dynamics. An example case of the aero-propulso-elastic (APE) modeling capability is explored for a supersonic transport vehicle with turbofan engines. An overview of the methodology for integrating the propulsion system and elastic vehicle is provided. This is followed by a study to explore coupling sensitivities compared against typical aeroelastic analysis. Dynamic and static vehicle responses are considered across key flight conditions and vehicle-level angles of attack, where the inclusion of the propulsion system has a 10% increase in vehicle wing tip deformations. It is found that the propulsion system is stable at various operating conditions, with structural oscillations having little impact on propulsion system performance. Perceived loudness, a key performance metric for a supersonic transport, is investigated using the APE model. Results lead to an approximately 4 dB increase in noise over a rigid body analysis that neglects the propulsion system. The greatest impacts are shown during off-nominal conditions.

show abstract

Section: Propulsion System Modelmentioning

confidence: 99%

Aero-Propulso-Elastic Analysis of a Supersonic Transport

Connolly¹,

Kopasakis²,

Chwalowski³

et al. 2020

Journal of Aircraft

View full text Add to dashboard Cite

show abstract

“…For example, simulations with active inlets and exhaust plumes are required to accurately capture the complex near-body shock system of low-boom supersonic aircraft to predict both aerodynamic performance and ground noise carpets. [1][2][3] Similarly, computational studies of high-bypass fanjet installations must accurately resolve the propulsive stream-tube to capture the changes in the induced drag due to the non-planar lifting system and the interference effects of transonic wave drag. 4,5 Another important example is efficient simulation of helicopters and multi-rotor vehicles, where capturing the rotor interference effects is essential to predicting aerodynamic performance.…”

Section: Introductionmentioning

confidence: 99%

Adjoint-Based Mesh Adaptation and Shape Optimization for Simulations with Propulsion

Nemec

Rodriguez²,

Aftosmis

2019

AIAA Aviation 2019 Forum

View full text Add to dashboard Cite

We demonstrate a well-posed formulation of permeable boundary conditions and massflow-rate functionals for adjoint-based mesh refinement and shape optimization governed by the steady Euler equations. The boundary conditions are used to model propulsionsystem effects of inlets and nozzles. A two-shock diffuser with an analytic solution is used to verify the implementation. Numerical examples show that the adjoint solution is smooth at the boundary, indicating that the discretization is adjoint consistent when exit pressure is specified at subsonic outflow, and stagnation temperature and pressure at subsonic inflow. The results focus on improving simulation techniques for low-boom aircraft analysis and design. By including mass-flow-rate outputs, we obtain reliable estimates of engine flow rates concurrently with nearfield pressure signatures without increasing simulation cost. We also demonstrate the importance of mass-flow-rate constraints in shape optimization by examining trade-offs between maximizing performance of a shrouded supersonic nozzle and minimizing shocks in its nearfield.

show abstract

“…Two recent CFD and experimental studies 11,12 have studied the interaction of an exhaust nozzle plume and a shock wave generated by simple wedge-shaped shock generators. The shock location from the wedge moved upstream due to the interaction with the plume and the plume path was deflected by the pressure disturbance from the wedge.…”

Section: Introductionmentioning

confidence: 99%

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

Castner

Elmiligui

Cliff

et al. 2015

53rd AIAA Aerospace Sciences Meeting

View full text Add to dashboard Cite

The desire to reduce or eliminate the operational restrictions of supersonic aircraft over populated areas has led to extensive research at NASA. Restrictions are due to the disturbance of the sonic boom, caused by the coalescence of shock waves formed by the aircraft. A study has been performed focused on reducing the magnitude of the sonic boom N-wave generated by airplane components with a focus on shock waves caused by the exhaust nozzle plume. Testing was completed in the 1-foot by 1-foot supersonic wind tunnel to study the effects of an exhaust nozzle plume and shock wave interaction. The plume and shock interaction study was developed to collect data for computational fluid dynamics (CFD) validation of a nozzle plume passing through the shock generated from the wing or tail of a supersonic vehicle. The wing or tail was simulated with a wedgeshaped shock generator. This test entry was the first of two phases to collect schlieren images and off-body static pressure profiles. Three wedge configurations were tested consisting of strut-mounted wedges of 2.5degrees and 5-degrees. Three propulsion configurations were tested simulating the propulsion pod and aft deck from a low boom vehicle concept, which also provided a trailing edge shock and plume interaction. Findings include how the interaction of the jet plume caused a thickening of the shock generated by the wedge (or aft deck) and demonstrate how the shock location moved with increasing nozzle pressure ratio. Nomenclature D= test nozzle outer diameter, inches NPR = nozzle pressure ratio, Pt / P∞ P = local static pressure, psia Pt = total pressure in nozzle, psia P∞ = free stream static pressure, psia ΔP/P = normalized static pressure, (P -P∞)/ P∞ x = axial distance from jet simulator nozzle exit plane, inches y = vertical distance from nozzle centerline, inches

show abstract

Wedge Shock and Nozzle Exhaust Plume Interaction in a Supersonic Jet Flow

Cited by 7 publications

References 27 publications

Aero-Propulso-Elastic Analysis of a Supersonic Transport

Aero-Propulso-Elastic Analysis of a Supersonic Transport

Adjoint-Based Mesh Adaptation and Shape Optimization for Simulations with Propulsion

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

Contact Info

Product

Resources

About