scholarly journals Base Pressure Control using Micro-jets in Supersonic Flow Regimes

2018 ◽  
Author(s):  
Vigneshvaran Sethuraman ◽  
Sher Afghan Khan
Keyword(s):  
Supersonic Flow ◽  
Flow Regimes ◽  
Pressure Control ◽  
Base Pressure

Base Pressure Control with Annular Ribs

2014 ◽  
Vol 31 (2) ◽  
Author(s):  
K. Vijayaraja ◽  
C. Senthilkumar ◽  
S. Elangovan ◽  
E. Rathakrishnan
Keyword(s):  
Pressure Control ◽  
Base Pressure

The Effect of Sting Diameter and Length on Base Pressure at M = 3·88

1968 ◽  
Vol 19 (4) ◽  
pp. 368-374 ◽  
Author(s):  
Walter R. Sieling
Keyword(s):  
Supersonic Flow ◽  
Axisymmetric Body ◽  
Base Pressure ◽  
Base Diameter ◽  
Apparent Change

SummaryThe effects of sting diameter and cylindrical protuberance length on the base pressure of an axisymmetric body in a turbulent supersonic flow are experimentally determined. It is found that the change in base pressure due to the presence of the sting is greater than 4 per cent when the ratio of sting diameter to base diameter is 0·150 or greater. When the ratio of cylindrical protuberance length to base diameter is greater than 1·3 there is no apparent change in base pressure with a change in length. However, when this ratio is less than 1·3, the base pressure varies greatly with length.

Flow Around a Conical Nose with Rounded Tail Projectile for Subsonic, Transonic, and Supersonic Flow Regimes : A Numerical Study

2014 ◽  
Vol 64 (6) ◽  
pp. 509-516
Author(s):  
Amitesh Kumar ◽  
◽  
H.S. Panda ◽  
T.K. Biswal ◽  
R. Appavuraj ◽  
...  
Keyword(s):  
Supersonic Flow ◽  
Numerical Study ◽  
Flow Regimes

An Euler-Based Throughflow Approach for an Axial Turbine at Supersonic Flow Regimes

2021 ◽  
Author(s):  
Sebastian Föllner ◽  
Dieter Brillert ◽  
FriedrichKarl Benra
Keyword(s):  
Supersonic Flow ◽  
Flow Regimes ◽  
Axial Turbine

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.

Review and development of base pressure and base heating correlations in supersonic flow

1995 ◽  
Vol 32 (1) ◽  
pp. 8-23 ◽  
Author(s):  
J. Parker Lamb ◽  
William L. Oberkampf
Keyword(s):  
Supersonic Flow ◽  
Base Pressure
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