Supersonic inlet study using the Navier-Stokes equations

1986 ◽  
Vol 2 (2) ◽  
pp. 181-187 ◽  
Author(s):  
Louis G. Hunter ◽  
John M. Tripp ◽  
Douglas G. Howlett
Keyword(s):  
Stokes Equations ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Supersonic Inlet

Computation of Off-Design Flows in a Transonic Compressor Rotor

1986 ◽  
Vol 108 (1) ◽  
pp. 144-150 ◽  
Author(s):  
W. N. Dawes
Keyword(s):  
Stokes Equations ◽  
Current Paper ◽  
Navier Stokes ◽  
Experimental Measurements ◽  
Navier Stokes Equations ◽  
Interactive Method ◽  
Transonic Compressor ◽  
Compressor Rotor ◽  
Supersonic Inlet ◽  
Maximum Benefit

Recent years have seen increasing efforts to develop efficient solvers for the compressible Navier–Stokes equations. For maximum benefit to be derived from this effort, these Navier–Stokes solvers must be capable of dealing with off-design flows as readily and accurately as the on-design cases. The current paper outlines an efficient implicit algorithm developed recently by the author for solving the compressible Navier–Stokes equations in turbomachinery blade-blade flows. The Navier–Stokes solver is applied to the study of a transonic compressor rotor with supersonic inlet velocities for three cases, one on-design and two off-design. The results are compared with experimental measurements and with the predictions of a viscous-inviscid interactive method.

Accuracy Issues in the Prediction of Supersonic Inlet Flows

1992 ◽  
Author(s):  
G. C. Paynter ◽  
E. Tjonneland
Keyword(s):  
Stokes Equations ◽  
Navier Stokes ◽  
Zonal Method ◽  
Inlet Flow ◽  
Navier Stokes Equations ◽  
Supersonic Inlet ◽  
Flow Phenomena ◽  
Accurate Performance ◽  
Primary Advantage ◽  
Computational Resources

Numerical and modeling accuracy issues are examined for two types of inlet flow analyses through a discussion of how numerical and modeling errors can influence the predicted inlet performance. For supersonic inlets, two types of procedures are in use at Boeing. The first is a zonal method that has been in use and under development for two decades. The second is based on solution of the Reynolds averaged NS (Navier-Stokes) equations; NS methods have been applied to the prediction of supersonic inlet flows for only about the last five years. The primary advantage of the zonal procedure is that accurate performance predictions are obtained on a computer workstation for only modest computational resources. The primary advantages of the NS procedures are the almost unlimited geometries and flows that can be considered. The accuracy (or lack thereof) achievable by either type of procedure is determined by the errors introduced by both the numerical procedures and by the modeling. At present, NS analysis is at about the same level of accuracy as the more mature zonal procedure. NS analysis offers, however, a wider range of flows and geometries that can be analyzed and less reliance on a sophisticated understanding of inlet flow phenomena necessary for modeling. Continuing advances in computing technology foretell a bright future for the use of CFD (Computational Fluid Dynamics) for supersonic inlet design when accuracy issues that constrain the usefulness are addressed.

Design and performance study of a parametric diverterless supersonic inlet

2019 ◽  
Vol 234 (2) ◽  
pp. 470-489
Author(s):  
Eiman B Saheby ◽  
Xing Shen ◽  
Anthony P Hays
Keyword(s):  
Boundary Layer ◽  
Stokes Equations ◽  
Three Dimensional ◽  
Navier Stokes ◽  
Operational Mode ◽  
Performance Study ◽  
Navier Stokes Equations ◽  
Supersonic Inlet ◽  
Wetted Area ◽  
And Performance

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.

A quasi one-dimensional bleed flow rate model for terminal normal shock stability in mixed compression supersonic inlet

2014 ◽  
Vol 228 (14) ◽  
pp. 2569-2583 ◽  
Author(s):  
Li Qiushi ◽  
Lv Yongzhao ◽  
Li Shaobin
Keyword(s):  
Flow Rate ◽  
Stokes Equations ◽  
Flow Characteristics ◽  
Normal Shock ◽  
Navier Stokes ◽  
Rate Model ◽  
Navier Stokes Equations ◽  
One Dimensional ◽  
Supersonic Inlet ◽  
The Stability

Ninety-degree (normal) bleed slots have been used to stabilize the terminal normal shock in the throat of a mixed compression supersonic inlet. In this study, a quasi-one-dimensional bleed flow rate model, consisting of a constant-area channel with a pair of normal slots symmetrically located along the upper and lower endwalls, is developed. The bleed flow rate is shown to be a function of the terminal normal shock position within the slot. Some key factors, such as the bleed discharge coefficient, taken from the Bragg model, were derived from the basic laws of conservation for a one-dimensional simplification. Furthermore, numerical simulations based on Reynolds-averaged Navier–Stokes equations were performed to analyze the flow characteristics around the bleed slots. The predictions of the bleed flow rate model agree well with computational fluid dynamics results. This method may be helpful to predict the stability of the terminal normal shock in mixed compression supersonic inlets.

Effects of stator splitter blades on aerodynamic performance of a single-stage transonic axial compressor

2020 ◽  
Vol 14 (4) ◽  
pp. 7369-7378
Author(s):  
Ky-Quang Pham ◽  
Xuan-Truong Le ◽  
Cong-Truong Dinh
Keyword(s):  
Stokes Equations ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Aerodynamic Performance ◽  
Numerical Results ◽  
Single Stage ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Operating Stability ◽  
Length Coverage

Splitter blades located between stator blades in a single-stage axial compressor were proposed and investigated in this work to find their effects on aerodynamic performance and operating stability. Aerodynamic performance of the compressor was evaluated using three-dimensional Reynolds-averaged Navier-Stokes equations using the k-e turbulence model with a scalable wall function. The numerical results for the typical performance parameters without stator splitter blades were validated in comparison with experimental data. The numerical results of a parametric study using four geometric parameters (chord length, coverage angle, height and position) of the stator splitter blades showed that the operational stability of the single-stage axial compressor enhances remarkably using the stator splitter blades. The splitters were effective in suppressing flow separation in the stator domain of the compressor at near-stall condition which affects considerably the aerodynamic performance of the compressor.

Sensitivity analysis for Navier-Stokes equations on unstructured meshes using complex variables

AIAA Journal ◽  
2001 ◽  
Vol 39 ◽  
pp. 56-63
Author(s):  
W. Kyle Anderson ◽  
James C. Newman ◽  
David L. Whitfield ◽  
Eric J. Nielsen
Keyword(s):  
Sensitivity Analysis ◽  
Stokes Equations ◽  
Unstructured Meshes ◽  
Complex Variables ◽  
Navier Stokes ◽  
Navier Stokes Equations
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