Stagnation Point Probes in Hypersonic Flow

2017 ◽  
pp. 117-127
Author(s):  
Syed Raza Christopher Ali ◽  
Rafael Zárate Cárdenas ◽  
Rolf Radespiel ◽  
Thomas Schilden ◽  
Wolfgang Schröder
Keyword(s):  
Hypersonic Flow ◽  
Stagnation Point

Stagnation-point velocity gradients for spherical segments in hypersonic flow

AIAA Journal ◽  
1969 ◽  
Vol 7 (10) ◽  
pp. 2040-2041 ◽  
Author(s):  
LARRY L. TRIMMER ◽  
EDWARD L. CLARK
Keyword(s):  
Hypersonic Flow ◽  
Stagnation Point ◽  
Velocity Gradients ◽  
Point Velocity

Contours for stagnation-point mass injection in hypersonic flow

AIAA Journal ◽  
1964 ◽  
Vol 2 (1) ◽  
pp. 178-179 ◽  
Author(s):  
CHANG-YI WANG
Keyword(s):  
Hypersonic Flow ◽  
Stagnation Point ◽  
Point Mass ◽  
Mass Injection

scholarly journals Experimental characterization of the hypersonic flow around a cuboid

2020 ◽  
Vol 61 (7) ◽  
Author(s):  
Thomas W. Rees ◽  
Tom B. Fisher ◽  
Paul J. K. Bruce ◽  
Jim A. Merrifield ◽  
Mark K. Quinn
Keyword(s):  
Heat Flux ◽  
Hypersonic Flow ◽  
Stagnation Point ◽  
Separation Bubble ◽  
Reynolds Numbers ◽  
High Heat ◽  
Heat Fluxes ◽  
High Heat Flux ◽  
Simple Method ◽  
High Reynolds

Abstract Understanding the hypersonic flow around faceted shapes is important in the context of the fragmentation and demise of satellites undergoing uncontrolled atmospheric entry. To better understand the physics of such flows, as well as the satellite demise process, we perform an experimental study of the Mach 5 flow around a cuboid geometry in the University of Manchester High SuperSonic Tunnel. Heat fluxes are measured using infrared thermography and a 3D inverse heat conduction solution, and flow features are imaged using schlieren photography. Measurements are taken at a range of Reynolds numbers from $${40.0 \times 10^3}$$ 40.0 × 10 3 to $${549 \times 10^3}$$ 549 × 10 3 . The schlieren results suggest the presence of a separation bubble at the windward edge of the cube at high Reynolds numbers. High heat fluxes are observed near corners and edges, which are caused by boundary-layer thinning. Additionally, on the side (off-stagnation) faces of the cube, we observe wedge-shaped regions of high heat flux emanating from the windward corners of the cube. We attribute these to vortical structures being generated by the strong expansion around the cube’s corners. We also observe that the stagnation point of the cube is off-centre of the windward face, which we propose is due to sting flex under aerodynamic loading. Finally, we propose a simple method of calculating the stagnation point heat flux to a cube, as well as relations which can be used to predict hypersonic heat fluxes to cuboid geometries such as satellites during atmospheric re-entry. Graphic abstract

HEAT TRANSFER TO THE STAGNATION POINT OF THE BLUNT BODY IN HYPERSONIC FLOW

1970 ◽  
Author(s):  
L. M. Biberman ◽  
S. Ya. Bronin ◽  
A.N. Lagar'kov
Keyword(s):  
Heat Transfer ◽  
Hypersonic Flow ◽  
Stagnation Point ◽  
Blunt Body
Sign in / Sign up

Export Citation Format

Share Document