Determination of Shock Standoff Distance for Wedge at Supersonic Flow
Authors
Abstract:
An experimental investigation is conducted to calculate the shock standoff (SSO) distance in front of an acute-angled wedge. For this experimentation, simple water flows channel analysis is carried out. The flow velocity is varied from 13.2 cm/s to 25.5 cm/s increasing in steps of 1 cm/s. A velocity of 13.2 cm/s corresponds to Froude number 1.13 and velocity of 25.5 cm/s to Froude number 1.41. The Froude number ranged from 1.13 to 1.41 in steps of 0.04. The study is conducted on 5 mm thick acrylic sheets and of wedge angles 50°, 60°, and 75° to obtain a relation for calculating the SSO distance concerning the Froude number. It is found that the pressure uphill strongly depends upon the Fr and wedge angle. The SSO distance determined experimentally and using the proposed correlation are found to be in good agreement.
similar resources
Supersonic flow onto a solid wedge
We consider the problem of 2D supersonic flow onto a solid wedge, or equivalently in a concave corner formed by two solid walls. For mild corners, there are two possible steady state solutions, one with a strong and one with a weak shock emanating from the corner. The weak shock is observed in supersonic flights. A long-standing natural conjecture is that the strong shock is unstable in some se...
full textControl of Nozzle Flow Using Microjets at Supersonic Mach Regime
This article reports the active control of base flows using the experimental procedure. Active control of base pressure helps in reducing the base drag in aerodynamic devices having suddenly expanded flows. Active control in the form of microjets having 0.5 mm radius placed at forty-five degrees apart is employed to control the base pressure. The Mach numbers of the present analysis are 1.7, 2....
full textShock Motion and Flow Instabilities in Supersonic Nozzle Flow Separation
This study evaluates the role of shock wave motion on the instability of the plume exiting an over-expanded, convergent-divergent nozzle. An array of wall pressure transducers was used to track the position of the shock in time, and a Pitot probe was used to obtain simultaneous measurement of the total pressure fluctuations at various points in the jet that emerges from the separation shock. An...
full textSupersonic Combustion Flow Visualization at Hypersonic Flow
Currently, a new generation of scientific aerospace vehicles, using advanced hypersonic airbreathing propulsion based on supersonic combustion technology, is in development at several research centers [1]. The 14-X Brazilian Hypersonic Aerospace Vehicle, Figure 1, designed by Rolim et al. [2], at the Prof. Henry T. Nagamatsu Laboratory of Aerothermodynamics and Hypersonics, Figure 2, at the Ins...
full textHigh Incidence Supersonic Similitude For Planar Wedge
A similitude has been obtained for a planar wedge with attached bow shock at high incidence in supersonic flow. A strip theory in which flow at a span wise location is two dimensional developed by Ghosh is been used. This combines with the similitude to lead to a piston theory which gives closed form of solutions for unsteady derivatives in pitch. Substantially the same results as the theory of...
full textGas Jet–Workpiece Interactions in Laser Machining
Laser machining efficiency and quality are closely related to gas pressure, nozzle geometry, and standoff distance. Modeling studies of laser machining rarely incorporate gas effects in part because of the complex structure and turbulent nature of jet flow. In this paper, the interaction of a supersonic, turbulent axisymmetric jet with the workpiece is studied. Numerical simulations are carried...
full textMy Resources
Journal title
volume 32 issue 7
pages 1049- 1056
publication date 2019-07-01
By following a journal you will be notified via email when a new issue of this journal is published.
Keywords
Hosted on Doprax cloud platform doprax.com
copyright © 2015-2023