Effects of counterflow jet on the performance of a generic rocket

Ölçmen, Semih; Cheng, Gary; Branam, Richard; Baker, John

doi:10.1016/j.actaastro.2021.01.060

Cited by 11 publications

(2 citation statements)

References 22 publications

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“…The main reason for limiting its use is the complexity. At present, how to solve the severe aerodynamic resistance and heating problems of future hypersonic vehicles is one of the research focuses (Ölçmen et al , 2021; Meng et al , 2021), and the advantages and importance of transpiration have been re-recognized, as it is a promising method. More and more scholars are studying the optimization of transpiration with the aim of reducing the aerodynamic resistance and the surface heat flux efficaciously.…”

Section: Introductionmentioning

confidence: 99%

Numerical study on heat and drag reduction by transpiration in hypersonic flow

Zhao

Huang

et al. 2023

HFF

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Purpose The transpiration has been recognized as one of the most effective thermal protection methods for future hypersonic vehicles. To improve efficiency and safety, it is urgent to optimize the design of the transpiration system for heat and drag reduction. The purpose of this paper is to investigate the effects of transpiration on heat and drag reduction. Design/methodology/approach A chemical nonequilibrium flow model with the transpiration is established by using Navier–Stokes equations, the shear-stress transport turbulence model, thermodynamic properties and the Gupta chemical kinetics model. The solver programmed for this model is verified by comparing with experimental results in the literature. Effects of air injection on the flow field, the aerodynamic resistance and the surface heat flux are calculated with the hypersonic flow past a blunt body. Furthermore, a modified blocking coefficient formula is proposed. Findings Numerical results show that the transpiration can reduce the aerodynamic resistance and the surface heat flux observably and increase the shock wave standoff distance slightly. It is also manifested that the modified formula is in better agreement with the wind tunnel test results than the original formula. Originality/value The modified formula can expand the application range of the engineering method for the blocking coefficient. This study will be beneficial to carry out the optimal design of the transpiration system.

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Section: Introductionmentioning

confidence: 99%

Numerical study on heat and drag reduction by transpiration in hypersonic flow

Zhao

Huang

et al. 2023

HFF

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“…e parameters of the counterflow jet have been analyzed experimentally, numerically, and even analytically. Studies [16][17][18][19][20][21] depict that the jet-to-body diameter ratio, jet orifice shape [22], and pressure ratio [23] affect the jet performance. e alteration in pressure ratio between the free-stream and counterflow jet generates two operating modes, short penetration mode (SPM) (Figure 1(a)) and long penetration mode (LPM) (Figure 1(b)), determined by the penetration length of the free-stream flow [24,25].…”

Section: Introductionmentioning

confidence: 99%

Modeling and Analysis of Shock Reduction through Counterflow Plasma Jets

Rashid

Nawaz

Maqsood

et al. 2021

Mathematical Problems in Engineering

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The study presents a numerical investigation of aerodynamic drag reduction by implementing a counterflow plasma jet, emanating from the stagnation point of an aerodynamic surface in a supersonic regime with a constant pressure ratio PR = 3 , and compares findings with a conventional opposing jet. The computational study is carried out by solving three-dimensional and axisymmetric Navier–Stokes equations for counterflow plasma-jet interaction. The calculations are performed at free-stream Mach ( M ∞ = 1.4) with sea level stagnation conditions. The weakly ionized argon plasma jet generated by a plasma torch has constant stagnation pressure and temperature of 303,975 Pa and 3000 K . The effect of the Mach number and the angle of attack variation on plasma-jet effectiveness is also analyzed. The results indicate that the counterflow plasma jet reduces more drag (in twice) compared to the conventional jet (nonplasma). The gravitational, magnetic field effect and chemical processes in the plasma formation are considered negligible. It is inferred that the effectiveness of the counterflow plasma jet strongly depends upon the jet stagnation temperature.

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