Numerical Prediction of Surface Heat Flux During Multiple Jets Firing for Missile Control

Saha, S.; Sinha, P. P.; Chakraborty, Debasis

doi:10.1007/s40032-012-0052-y

Cited by 7 publications

(3 citation statements)

References 3 publications

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“…To find out the accuracy and the range of applications, the software has been validated for various internal flow fields in the rectangular duct behind backward facing step [12,13], base flow [14], free jets [15], free stream and jet interaction [16][17][18], dual pulse rocket motor [19], air intakes [20] etc. and good quantitative agreement has been obtained between experimental and computational results.…”

Section: Governing Equations and Modelsmentioning

confidence: 99%

Numerical Simulations of Static Tested Ramjet Dump Combustor

Javed

Chakraborty

2016

J. Inst. Eng. India Ser. C

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The flow field of a Liquid Fuel Ram Jet engine side dump combustor with kerosene fuel is numerically simulated using commercial CFD code CFX-11. Reynolds Averaged 3-D Navier-Stokes equations are solved alongwith SST turbulence model. Single step infinitely fast reaction is assumed for kerosene combustion. The combustion efficiency is evaluated in terms of the unburnt kerosene vapour leaving the combustor. The comparison of measured pressures with computed values show that the computation underpredicts (*5 %) pressures for non reacting cases but overpredicts (9-7 %) for reacting cases.

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Section: Governing Equations and Modelsmentioning

confidence: 99%

Numerical Simulations of Static Tested Ramjet Dump Combustor

Javed

Chakraborty

2016

J. Inst. Eng. India Ser. C

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“…Because of its importance in science and engineering, side jet interaction with free stream is studied extensively for high altitude and high Mach number conditions [10,11] as well as for subsonic Mach numbers [12][13][14][15][16][17][18] at sea level conditions. Detailed experimental flow field analysis using PIV measurements were made by Beresh et al [12][13][14], for study of penetration of a transverse / inclined supersonic jet into a subsonic compressible crossflow.…”

Section: Introductionmentioning

confidence: 99%

Aero-Propulsive Characterization of a Flight Vehicle with Two Side-Jets

Balasubramanian,

Dayal,

Krishnamurthy

et al. 2023

joast

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Numerical simulations were carried out to study the aero-propulsive characteristics of a flight vehicle using in-house developed Reynolds Averaged Navier-Stokes code CERANS. The analyses involved subsonic external flow with inclined supersonic dual sustainer jets at various angles of attack, roll orientations and side slip. The control characteristics of the configuration are evaluated for the flow with and without sustainer jets. Numerical simulations indicated that the jet plume exhausting out of the scarf sustainer nozzle grazed and clung to the airframe for a considerable downstream distance causing serious damage to the airframe. This numerical study led to an important design change of the sustainer nozzle shape from ‘scarf’ to ‘conical’ which alleviated plume interference problem with the airframe.

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“…Therefore, heat load data on the supersonic/hypersonic missile wall is notably absent in the open literature. 2,10 A few researchers 12,13 have performed numerical studies to predict surface heat flux during jet firing; however, studies are limited to continuum regime ( H < 53 km) and nonequilibrium effects due to rarefaction are not considered.…”

Section: Introductionmentioning

confidence: 99%

Modeling of a reaction control jet interacting with high-speed cross-flow in slip flow regime

Bhagat

Gijare

Dongari

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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Numerical investigation of a sonic reaction control jet interacting with the high-speed cross-flow has been carried out over a generic missile body. Simulations are performed in the early-hypersonic slip flow regime for air, CO2, and helium jet gases. An open source computational fluid dynamics tool, OpenFOAM is used to model the steady state, three-dimensional compressible Navier–Stokes equations with k-ω shear stress transport turbulence model. The conventional computational fluid dynamics solver is extended with additional features, such as transport of species, nonequilibrium boundary conditions for velocity slip and temperature jump, and a heat load calculation utility based on the sliding friction effect. The extended solver is validated with the direct simulation Monte Carlo results for the case of a sonic argon jet injected into hypersonic nitrogen cross-flow. The extended solver is able to accurately capture all the qualitative flow features like separation shock, bow shock, and barrel shock, and it also improves heat load predictions in the slip flow regime. The main objective of the present work is to study the effect of rarefaction and change in jet gas species on the complex flow topology, heat load distribution, and spread of jet gas on the missile body. Heat load predictions are found to be strongly dependent on the slip velocity of molecules in addition to the temperature gradient near the wall. The strength of a bow shock and a barrel shock is higher for helium jet, compared to air and CO2 jets, which spread more along the missile body, and weaker shocks and reduced heat load is generated. The current work is significant from the perspective of the thermal design of spacecraft surfaces and positioning of the optical sensors.

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Numerical Prediction of Surface Heat Flux During Multiple Jets Firing for Missile Control

Cited by 7 publications

References 3 publications

Numerical Simulations of Static Tested Ramjet Dump Combustor

Numerical Simulations of Static Tested Ramjet Dump Combustor

Aero-Propulsive Characterization of a Flight Vehicle with Two Side-Jets

Modeling of a reaction control jet interacting with high-speed cross-flow in slip flow regime

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