Pitching Model with Control Surface in Hypersonic Flow: Short Duration Ground Tests and Simulations

2020 ◽  
Author(s):  
Nathan Stern ◽  
David R. Buttsworth
Keyword(s):  
Hypersonic Flow ◽  
Short Duration ◽  
Control Surface

Temperature- and Pressure-Sensitive Paint Measurements in Short-Duration Hypersonic Flow

AIAA Journal ◽  
2001 ◽  
Vol 39 (4) ◽  
pp. 654-659 ◽  
Author(s):  
J. P. Hubner ◽  
B. F. Carroll ◽  
K. S. Schanze ◽  
H. F. Ji ◽  
M. S. Holden
Keyword(s):  
Hypersonic Flow ◽  
Short Duration ◽  
Pressure Sensitive Paint ◽  
Pressure Sensitive ◽  
Temperature And Pressure

Numerical analysis of exhaust jet secondary combustion in hypersonic flow field

2018 ◽  
Vol 32 (12n13) ◽  
pp. 1840045
Author(s):  
Tian-Peng Yang ◽  
Jiang-Feng Wang ◽  
Fa-Ming Zhao ◽  
Xiao-Feng Fan ◽  
Yu-Han Wang
Keyword(s):  
Flow Field ◽  
Hypersonic Flow ◽  
Flight Control ◽  
Stokes Equations ◽  
Field Structure ◽  
Control Surface ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Secondary Combustion ◽  
Exhaust Jet

The interaction effect between jet and control surface in supersonic and hypersonic flow is one of the key problems for advanced flight control system. The flow properties of exhaust jet secondary combustion in a hypersonic compression ramp flow field were studied numerically by solving the Navier–Stokes equations with multi-species and combustion reaction effects. The analysis was focused on the flow field structure and the force amplification factor under different jet conditions. Numerical results show that a series of different secondary combustion makes the flow field structure change regularly, and the temperature increases rapidly near the jet exit.

Heat alleviation studies on hypersonic re-entry vehicles

2018 ◽  
Vol 122 (1257) ◽  
pp. 1673-1696 ◽  
Author(s):  
M. Khalid ◽  
K. A. Juhany
Keyword(s):  
Numerical Simulation ◽  
Boundary Condition ◽  
Flow Field ◽  
Hypersonic Flow ◽  
Flow Rate ◽  
Leading Edge ◽  
Control Surface ◽  
Solid Boundary ◽  
Simulation Techniques ◽  
Hypersonic Speeds

ABSTRACTA numerical simulation has been carried out to investigate the effects of leading edge blowing upon heat alleviation on the surface of hypersonic vehicles. The initial phase of this work deals with the ability of the present CFD-based techniques to solve hypersonic flow field past blunt-nosed vehicles at hypersonic speeds. Towards this end, the authors selected three re-entry vehicles with published flow field data against which the present computed results could be measured. With increasing confidence on the numerical simulation techniques to accurately resolve the hypersonic flow, the boundary condition at the solid blunt surface was then equipped with the ability to blow the flow out of the solid boundary at a rate of at least 0.01–0.1 times the free stream (ρ∞u∞) mass flow rate. The numerical iterative procedure was then progressed until the flow at the surface matched this new ‘inviscid like’ boundary condition. The actual matching of the flow field at the ejection control surface was achieved by iterating the flow on the adjacent cells until the flow conformed to the conditions prescribed at the control surface. The conditions at the surface could be submitted as a ρ∞u∞at the surface or could be equipped as a simple static pressure condition providing the desired flow rate. The comparison between the present engineering approach and the experimental data presented in this study demonstrate its ability to solve complex problems in hypersonic.

Temperature- and pressure-sensitive paint measurements in short-duration hypersonic flow

AIAA Journal ◽  
2001 ◽  
Vol 39 ◽  
pp. 654-659 ◽  
Author(s):  
J. P. Hubner ◽  
B. F. Carroll ◽  
K. S. Schanze ◽  
M. S. Holden
Keyword(s):  
Hypersonic Flow ◽  
Short Duration ◽  
Pressure Sensitive Paint ◽  
Pressure Sensitive ◽  
Temperature And Pressure

An Experimental and Computational Correlation Study for Fluid-Thermal-Structural Interaction of a Control Surface in Hypersonic Flow

2022 ◽  
Author(s):  
Aravinth Sadagopan ◽  
Daning Huang ◽  
Adam Jirasek ◽  
Jürgen Seidel ◽  
Anshuman Pandey ◽  
...  
Keyword(s):  
Hypersonic Flow ◽  
Correlation Study ◽  
Control Surface ◽  
Structural Interaction

A study of cometary eruptions through OH radio-lines

1999 ◽  
Vol 173 ◽  
pp. 249-254
Author(s):  
A.M. Silva ◽  
R.D. Miró
Keyword(s):  
Short Duration ◽  
Growth Curves ◽  
The Other ◽  
Initial Mass ◽  
Radio Lines ◽  
Other Hand ◽  
Sudden Rise

AbstractWe have developed a model for theH2OandOHevolution in a comet outburst, assuming that together with the gas, a distribution of icy grains is ejected. With an initial mass of icy grains of 108kg released, theH2OandOHproductions are increased up to a factor two, and the growth curves change drastically in the first two days. The model is applied to eruptions detected in theOHradio monitorings and fits well with the slow variations in the flux. On the other hand, several events of short duration appear, consisting of a sudden rise ofOHflux, followed by a sudden decay on the second day. These apparent short bursts are frequently found as precursors of a more durable eruption. We suggest that both of them are part of a unique eruption, and that the sudden decay is due to collisions that de-excite theOHmaser, when it reaches the Cometopause region located at 1.35 × 105kmfrom the nucleus.

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