Supersonic flow around the trailing edge of a thin profile

1981 ◽  
Vol 22 (3) ◽  
pp. 316-321
Author(s):  
A. V. Kazakov
Keyword(s):  
Supersonic Flow ◽  
Trailing Edge ◽  
Thin Profile

High-Speed Visualization of the Oscillatory Supersonic Flow Over a Rectangular Cavity

2011 ◽  
Author(s):  
Taro Handa ◽  
Hiroaki Miyachi ◽  
Hatsuki Kakuno ◽  
Takaya Ozaki
Keyword(s):  
Supersonic Flow ◽  
Pressure Wave ◽  
High Speed ◽  
Pressure Oscillation ◽  
Rectangular Cavity ◽  
Schlieren Method ◽  
Trailing Edge ◽  
The Relationship ◽  
Type Pressure ◽  
Semiconductor Type

A mechanism of cavity-induced pressure oscillation in supersonic flows is not well understood in spite of a lot of former investigations. Especially, the process by which the pressure wave is generated and the path of the pressure wave propagating inside the cavity remain unclear. In order to clarify these, the oscillatory behaviors in the supersonic flow over a rectangular cavity are visualized by the schlieren method with a high-speed camera in the present study. The inlet Mach number of the flow is 1.68. The length and depth of the cavity are 14.0mm and 11.7mm respectively; i.e., the length-to-depth ratio of the cavity is 1.20. The pressure oscillation near the trailing edge of the cavity is also measured by use of the semiconductor-type pressure transducer simultaneously with the visualization. As a result, the pressure waves propagating inside as well as outside the cavity are successfully visualized. In addition, the relationship between the shear layer displacement, pressure wave generation and pressure oscillation at the trailing edge of the cavity are clarified experimentally.

scholarly journals REGARDING CERTAIN AERODYNAMIC SOURCES OF NON-STATIONARY FORCE LOADS ON TURBINE PROFILES

2018 ◽  
Vol 20 ◽  
pp. 73-77
Author(s):  
Tomáš Radnic ◽  
Martin Luxa ◽  
David Šimurda
Keyword(s):  
Supersonic Flow ◽  
Flow Field ◽  
Steam Turbine ◽  
Rotor Blade ◽  
Trailing Edge ◽  
Blade Cascade ◽  
Cascade Flow ◽  
Unsteady Force ◽  
Last Stage ◽  
Large Output

The paper deals with selected phenomena present in a blade cascade flow field. The presented research was performed on prismatic blade cascades composed mostly of the tip and root sections of the last stage rotor blade of a large output steam turbine. The unstarted supersonic flow on the cascade inlet, the separation of the flow and the swirl line behind the trailing edge have been identified as the possible sources of the unsteady force effects.

The effect of base bleed on vortex shedding and base pressure in compressible flow

1981 ◽  
Vol 110 ◽  
pp. 273-292 ◽  
Author(s):  
F. Motallebi ◽  
J. F. Norbury
Keyword(s):  
Supersonic Flow ◽  
Compressible Flow ◽  
Vortex Shedding ◽  
Transonic Flow ◽  
Vortex Formation ◽  
Base Pressure ◽  
Trailing Edge ◽  
Blunt Trailing Edge ◽  
Base Bleed ◽  
The Relationship

Experiments have been carried out to investigate the phenomenon of vortex shedding from the blunt trailing edge of an aerodynamic body in transonic and supersonic flow. The effect of a discharge of bleed air from a slot in the trailing edge has been included and the relationship between the vortex formation and base pressure has been considered.In transonic flow a small amount of bleed air was found to produce a rearward shift in the point of origin of the vortices with a consequent substantial increase in base pressure. The effect was less marked in supersonic flow. At higher rates of bleed two different regimes of vortex shedding were identified and increase in bleed rate caused a reduction in base pressure. For bleed rates giving near-maximum base pressure no vortex shedding occurred.

Separated supersonic flow past a trailing edge at incidence

1986 ◽  
Vol 14 (2) ◽  
pp. 109-116 ◽  
Author(s):  
J.W. Elliott ◽  
F.T. Smith
Keyword(s):  
Supersonic Flow ◽  
Trailing Edge ◽  
Flow Past

The Effects on Wing Lift and Pitching Moment Due to the Fin of an Aircraft Flying at Supersonic Speeds

1967 ◽  
Vol 71 (674) ◽  
pp. 134-136
Author(s):  
L. B. Jones
Keyword(s):  
Supersonic Flow ◽  
Pressure Field ◽  
Free Stream ◽  
Leading Edge ◽  
Simple Expression ◽  
Pitching Moment ◽  
Trailing Edge ◽  
Blunt Trailing Edge ◽  
Sharp Edges

Summary:A simple expression is obtained for the lift induced upon a wing by the pressure field of the fin mounted upon the wing in supersonic flow. This expression holds for all fins with sharp edges provided that the wing trailing edge is normal to the free stream and that the Mach lines from the apex of the fin do not intersect the wing leading edge. If the fin has a blunt trailing edge the further restriction that the wing trailing edge is upstream of that of the fin is also required.Results for the induced lift and pitching moment are presented for a delta fin with variations in size and position of the fin relative to the wing trailing edge.

scholarly journals Effects of Probe Supports on Measurements in Steam Turbines

1986 ◽  
Author(s):  
L. C. Squire
Keyword(s):  
Supersonic Flow ◽  
Mass Flow ◽  
Support Systems ◽  
Steam Turbines ◽  
Interference Effects ◽  
Suction Surface ◽  
Trailing Edge ◽  
Blade Passage ◽  
Flow Reduction ◽  
Flow Through

This paper presents the results of an investigation of the interference effects produced within the blade passages due to the support systems used to position probes downstream of the trailing edge in the interblade regions. The support systems studied consist of simple circular rods and it is shown that the presence of these probe stems can have a very large effect on the flow through the blade passage. In all cases the presence of the probe stem reduces the mass flow through the passage directly upstream of the probe with, in some cases, the flow reduction being so great as to eliminate all regions of supersonic flow on the suction surface of the blade. The paper also describes the results of preliminary tests aimed at reducing these effects; further work on this aspect of the study is continuing.

Aerodynamics of Airfoils with Porous Trailing Edges

1979 ◽  
Vol 30 (2) ◽  
pp. 387-399 ◽  
Author(s):  
C. Samuel Ventres ◽  
Richard Barakat
Keyword(s):  
Supersonic Flow ◽  
Complex Variable ◽  
Closed Form Solution ◽  
Form Solution ◽  
Pressure Loading ◽  
Trailing Edge ◽  
Variable Theory ◽  
Complex Variable Theory ◽  
Trailing Edges ◽  
Special Case

SummaryThe aerodynamics of a thin airfoil of arbitrary camber having a porous trailing edge in steady, subsonic, compressible potential flow is investigated. In the special case of a flat plate airfoil with a porous trailing edge, an exact, closed form solution is obtained using complex variable theory. The pressure loading on the airfoil, the lift and pitching moments are exhibited explicitly along with typical numerical results. The corresponding situation in supersonic flow is also considered.

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