Design of top mounted supersonic inlets for a cylindrical fuselage

Saheby, Eiman B.; Gouping, Huang; Hays, Anthony P.

doi:10.1177/0954410018790173

Cited by 5 publications

(6 citation statements)

References 20 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The final grid for forebody-inlet simulations contains about four million cells. The accuracy of the grid structure can also be compared with similar studies in the study by Saheby et al 23 The grid domains are interrelated to each other. It means that the grid blocks in Figure 8 are generated by splitting and mirroring the grid blocks in Figure 7, so the grid study of both cases follows a similar cell increment approach.…”

Section: Grid Studymentioning

confidence: 97%

“…By extending the wetted area in front of the bump, it is possible to estimate the effects of BL thickness on the performance of the DSI with a simpler computational domain, 23 but when installed on an aircraft, its forebody affects the flow pattern and thickness of the BL, especially at maneuver conditions. A simple planar extension of the wetted area does not accurately provide simulation of the airflow upstream of the bump.…”

Section: Inlet Model For Cfd Simulationsmentioning

confidence: 99%

“…The three-dimensional Navier-Stokes equations, coupled with an SST (shear stress transport) turbulence model, 23 are solved by the steady-state upwind algorithm in the domains. The solution starts with the first-order discretization scheme and when the residuals reach 10 À4 , the solver changes to second-order scheme and continues the iterations with double precision approach.…”

Section: Governing Equations and Solver Adjustmentmentioning

confidence: 99%

“…Previous researchers have proven the accuracy of double equation turbulent models for supersonic flow analysis. 23…”

Section: Governing Equations and Solver Adjustmentmentioning

confidence: 99%

See 3 more Smart Citations

Design and performance study of a parametric diverterless supersonic inlet

Saheby

Shen

Hays³

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

Self Cite

View full text Add to dashboard Cite

Diverterless supersonic inlet integration for a flight vehicle requires a three-dimensional compression surface (bump) design with an acceptable shock structure and boundary layer diversion; this results in a low drag induction system with acceptable propulsive efficiency. In this investigation, a computational fluid dynamics-based-generated bump is used to design an integrated diverterless supersonic inlet without any bleed mechanism on a forebody with a large wetted area. Numerical solution of the Navier–Stokes equations simulates the flow pattern of the configuration. The forebody design analysis includes simulating the effects of angle of attack and sideslip by dependent computational domains. Results demonstrate the ability of the bump surface to keep the shock structures in an operational mode even at high supersonic angles of attack. Analysis of shock structures and shock wave boundary layer interactions at supersonic maneuver conditions indicate that the aerodynamic efficiency of the diverterless supersonic inlet in conditions with a thick boundary layer and high angles of attack is sufficient to ensure operation throughout the supersonic flight envelope.

show abstract

Section: Grid Studymentioning

confidence: 97%

Section: Inlet Model For Cfd Simulationsmentioning

confidence: 99%

Section: Governing Equations and Solver Adjustmentmentioning

confidence: 99%

“…Previous researchers have proven the accuracy of double equation turbulent models for supersonic flow analysis. 23…”

Section: Governing Equations and Solver Adjustmentmentioning

confidence: 99%

See 2 more Smart Citations

Design and performance study of a parametric diverterless supersonic inlet

Saheby

Shen

Hays³

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

Self Cite

View full text Add to dashboard Cite

show abstract

“…By closing the M n to (or equal to) unity, the total pressure loss of the normal shock is minimized, but the shock stability at the entrance needs stronger pressure jumps. 27,28 Therefore, the range 1.2 < M t < 1.3 is selected for compression surface design because it is widely used for throat Mach numbers of practical external compression induction systems to keep a stable terminal shock at the entrance. 29 Generally, the total pressure recovery of the supersonic compression should be maximized by selecting an adequate number of ramps (or turning angles) to reduce freestream Mach number to the desired M n .…”

Section: Design Of Forebody-inlet Configurationmentioning

confidence: 99%

The inlet flow structure of a conceptual open-nose supersonic drone

Saheby

Shen

Hays

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

Self Cite

View full text Add to dashboard Cite

This study describes the aerodynamic efficiency of a forebody–inlet configuration and computational investigation of a drone system, capable of sustainable supersonic cruising at Mach 1.60. Because the whole drone configuration is formed around the induction system and the design is highly interrelated to the flow structure of forebody and inlet efficiency, analysis of this section and understanding its flow pattern is necessary before any progress in design phases. The compression surface is designed analytically using oblique shock patterns, which results in a low drag forebody. To study the concept, two inlet–forebody geometries are considered for Computational Fluid Dynamic simulation using ANSYS Fluent code. The supersonic and subsonic performance, effects of angle of attack, sideslip, and duct geometries on the propulsive efficiency of the concept are studied by solving the three-dimensional Navier–Stokes equations in structured cell domains. Comparing the results with the available data from other sources indicates that the aerodynamic efficiency of the concept is acceptable at supersonic and transonic regimes.

show abstract