scholarly journals A review and development of correlations for base pressure and base heating in supersonic flow

1993 ◽  
Author(s):  
J.P. Lamb ◽  
W.L. Oberkampf
Keyword(s):  
Supersonic Flow ◽  
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.

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

Two Different Theoretical Approaches to the Base Pressure Problem in Two-Dimensional Supersonic Flow

1978 ◽  
Vol 29 (2) ◽  
pp. 114-130 ◽  
Author(s):  
M. Tanner
Keyword(s):  
Supersonic Flow ◽  
Flow Model ◽  
The Body ◽  
Experimental Results ◽  
Base Pressure ◽  
Two Dimensional ◽  
Reattachment Point ◽  
Fundamental Idea ◽  
Entropy Increase ◽  
Theoretical Approaches

SummaryThe basic physical idea underlying the theories based on the flow model of CHAPMAN and KORST is that the base pressure can be predicted if the pressure at the reattachment point is known. In the new theory of TANNER the fundamental idea is the connection between the drag of the body and the entropy increase in the flow. This paper presents the essence of both theories together with theoretical and experimental results.

Two-Dimensional Boat-Tailed Bases in Supersonic Flow

1974 ◽  
Vol 25 (3) ◽  
pp. 210-224 ◽  
Author(s):  
P R Viswanath ◽  
R Narasimha
Keyword(s):  
Boundary Layer ◽  
Supersonic Flow ◽  
Free Stream ◽  
The Body ◽  
Base Pressure ◽  
Two Dimensional ◽  
Sharp Corner ◽  
Boundary Layer Effect ◽  
Pressure Distributions ◽  
Layer Effect

SummaryBoat-tailing of aft bodies may affect the base pressure through two mechanisms: firstly by changing the angle between the approaching flow at separation and the reattachment surface, and secondly by distorting the boundary layer through the favourable pressure gradient (which can be particularly severe in the presence of a sharp corner on the body). The first effect is isolated here by tests on inclined backward-facing steps with a fully developed turbulent boundary layer at separation, at free-stream Mach numbers of 1.75 and 2.4. It is found that the base pressure increases significantly with boat-tail angle; the data have been correlated taking explicit account of the boundary layer effect, modifying and extending the approach adopted by Nash. Charts are provided for quick estimation of base pressure in engineering calculations. Some of the earlier data on boat-tailed bases, on re-examination in the light of the present correlation, suggest that strongly distorted boundary layers at separation affect the base pressure appreciably. Several features of the measured reattachment pressure distributions, including their internal similarity, are also discussed.

Study of base pressure fluctuations behind a cone in supersonic flow

1970 ◽  
Vol 1 (6) ◽  
pp. 84-86 ◽  
Author(s):  
Yu. A. Panov ◽  
A. I. Shvets ◽  
A. M. Khazen
Keyword(s):  
Supersonic Flow ◽  
Pressure Fluctuations ◽  
Base Pressure

Base Pressure Measurements on Elliptic Cones in Supersonic Flow

1967 ◽  
Vol 18 (3) ◽  
pp. 298-307 ◽  
Author(s):  
W. Stahl ◽  
H. Grauer-Carstensen
Keyword(s):  
Boundary Layer ◽  
Supersonic Flow ◽  
Reasonable Agreement ◽  
Flow Theory ◽  
Reynolds Numbers ◽  
Base Flow ◽  
Base Pressure ◽  
Pressure Measurements ◽  
Pressure Coefficients ◽  
Mach Numbers

SummaryAt the Aerodynamische Versuchsanstalt Gottingen (AVA), base pressure measurements were made on five elliptic cones. The ratios of the axes of the ellipses were: 1:12, 1:3, 1:1, 3:1, and 12:1. All the cones had the same volume and the same length. The investigations were carried out for Mach numbers M∞=1·50, 1·73, and 1·98 at angles of incidence between about —2 degrees and about 8 degrees. Reynolds numbers, based on a mean length, lm, varied from 2·5×106 to 3·0×106; the boundary layer approaching the base was turbulent. The base pressure coefficients are given as a function of geometry. Some of the results were compared with the base-flow theory of Korst and reasonable agreement was found.

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