Optimization of air-ejected rocket/missile geometries under validated supersonic flow field simulations

2014 ◽  
Author(s):  
D. López ◽  
D. Domínguez ◽  
J. Gonzalo
Keyword(s):  
Supersonic Flow ◽  
Flow Field

The Supersonic Flow Field Associated with a Conical Flame Sheet

1970 ◽  
Vol 21 (4) ◽  
pp. 368-378 ◽  
Author(s):  
J. F. Clarke ◽  
D. G. Petty
Keyword(s):  
Supersonic Flow ◽  
Flow Field ◽  
Base Flow ◽  
Slender Body ◽  
Conical Flow ◽  
Slender Body Theory ◽  
Deflagration Wave ◽  
Flame Sheet ◽  
Base Drag ◽  
Body Theory

SummaryIt is shown that a pair of supersonic inviscid conical flow fields can exist on either side of a conical deflagration wave. The configuration is relevant to the base flow question and indicates how base drag may be alleviated by burning. Results of exact computations are presented as well as those derived from a slender-body theory.

Correction: Computational Simulation of Axis Symmetric Aft Wall Angle Cavity in Supersonic Flow Field

2020 ◽  
Author(s):  
Naresh Relangi ◽  
Divyasri Garimella ◽  
K Jayaraman ◽  
Jayakumar Venkatesan ◽  
S Jeyakumar ◽  
...  
Keyword(s):  
Supersonic Flow ◽  
Flow Field ◽  
Computational Simulation ◽  
Wall Angle

On the flow field of a rapidly oscillating airfoil in a supersonic flow

1974 ◽  
Vol 62 (4) ◽  
pp. 811-827 ◽  
Author(s):  
M. Kurosaka
Keyword(s):  
Supersonic Flow ◽  
Flow Field ◽  
Leading Edge ◽  
Flow Region ◽  
Relative Magnitude ◽  
Frequency Parameter ◽  
Unsteady Supersonic Flow ◽  
Long Time ◽  
Intimate Knowledge ◽  
Repeated Use

This paper examines the features of the flow field off the surface of an oscillating flat-plate airfoil immersed in a two-dimensional supersonic flow Although the exact linearized solution for a supersonic unsteady airfoil has been known for a long time, its expression in the form of an integral is not convenient for a physical interpretation. In the present paper, the quintessential features of the flow field are extracted from the exact solution by obtaining an asymptotic expansion in descending powers of a frequency parameter through the repeated use of the stationary-phase and steepest descent methods. It is found that the flow field consists of two dominant and competing signals: one is the acoustic ray or that component arising from Lighthill's ‘convecting slab’ and the other is the leading-edge disturbance propagating as a convecting wavelet. The flow field is found to be divided into several identifiable regions defined by the relative magnitude of the signals, and the asymptotic expansions appropriate for each flow region are derived along with their parametric restrictions. Such intimate knowledge of the flow field in unsteady, supersonic flow is of interest for interference aerodynamics and related acoustic problems.

scholarly journals Reverse flow and supersonic interference

1959 ◽  
Vol 6 (2) ◽  
pp. 272-288 ◽  
Author(s):  
Joseph H. Clarke
Keyword(s):  
Spatial Distribution ◽  
Supersonic Flow ◽  
Flow Field ◽  
Reverse Flow ◽  
Flow Reversal ◽  
Analytic Proof ◽  
Perturbation Velocity ◽  
Horseshoe Vortices ◽  
Linearized Theory ◽  
Drag And Lift

First, from a volumetric formulation of the momentum theorem of linearized theory, a general analytic proof is presented of the invariance of the drag of an arbitrary spatial distribution of horseshoe vortices and sources under reversal of the undisturbed flow. By consideration of the interference drag of two such singularity distributions, a reverse-flow relation for steady subsonic or supersonic flow is then obtained. This relation, a generalization of the Ursell-Ward theorem, may be applied to configurations with bodies whose surfaces are not quasi-cylindrical and whose surface pressures are quadratically related to the perturbation velocity.The relation is used to discuss several interfering two-body arrangements in supersonic flow. It is shown that, in certain cases, the drag and lift may be determined without knowledge of the interference flow field associated with the arbitrarily prescribed body geometry. The simplicity of the results permits the formulation of optimum problems. The invariance of the drag under flow reversal with unchanged geometry is also established.

Effect of Finite Diaphragm Rupture Process on Microshock Tube Flows

2013 ◽  
Vol 135 (8) ◽  
Author(s):  
Arun K. R ◽  
H. D. Kim ◽  
T. Setoguchi
Keyword(s):  
Supersonic Flow ◽  
Flow Field ◽  
Shock Front ◽  
Supersonic Nozzle ◽  
Propagation Speed ◽  
Propagation Distance ◽  
Rupture Process ◽  
Shock Propagation ◽  
Diaphragm Rupture ◽  
Contact Distance

The study of flow physics in microshock tubes is of growing importance with the recent development of microscale technology. The flow characteristics in a microshock tube is considerably different from that of the conventional macroshock tube due to the boundary layer effects and high Knudsen number effects. In the present study an axisymmetric computational fluid dynamics (CFD) method was employed to simulate the microshock tube flow field with Maxwell's slip velocity and temperature jump boundary conditions, to accommodate the rarefaction effects. The effects of finite diaphragm rupture process and partial diaphragm rupture on the flow field and the wave propagations were investigated, in detail. The results show that the shock propagation distance attenuates rapidly for a microshock tube compared to a macroshock tube. For microshock tubes, the contact surface comes closer to the shock front compared to the analytical macroshock tube case. Due to the finite diaphragm rupture process the moving shock front will be generated after a certain distance ahead of the diaphragm and get attenuated rapidly as it propagates compared to the sudden rupture case. The shock-contact distance reduces considerably for the finite diaphragm rupture case compared to the sudden diaphragm rupture process. A partially burst diaphragm within a microshock tube initiates a supersonic flow in the vicinity of the diaphragm similar to that of a supersonic nozzle flow. The supersonic flow expansion leads to the formation of oblique shock cells ahead of the diaphragm and significantly attenuates the moving shock propagation speed.

The Simulation of Turbomachinery Blade Rows in Asymmetric Flow Using Actuator Disks

1997 ◽  
Vol 119 (4) ◽  
pp. 723-732 ◽  
Author(s):  
W. G. Joo ◽  
T. P. Hynes
Keyword(s):  
Supersonic Flow ◽  
Flow Field ◽  
Boundary Conditions ◽  
High Speed ◽  
Axial Position ◽  
Numerical Implementation ◽  
Asymmetric Flow ◽  
Actuator Disk ◽  
Blade Row ◽  
Flow Through

This paper describes the development of actuator disk models to simulate the asymmetric flow through high-speed low hub-to-tip ratio blade rows. The actuator disks represent boundaries between regions of the flow in which the flow field is solved by numerical computation. The appropriate boundary conditions and their numerical implementation are described, and particular attention is paid to the problem of simulating the effect of blade row blockage near choking conditions. Guidelines on choice of axial position of the disk are reported. In addition, semi-actuator disk models are briefly described and the limitations in the application of the model to supersonic flow are discussed.

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