Jet Momentum Research Articles

Conformal collider physics meets LHC data

The remarkably high energies of the Large Hadron Collider (LHC) have allowed for the first measurements of the shapes and scalings of multipoint correlators of energy flow operators, ⟨Ψ|E(n→1)E(n→2)⋯E(n→k)|Ψ⟩, providing new insights into the Lorentzian dynamics of quantum chromodynamics (QCD). In this letter, we use recent advances in effective field theory to derive a rigorous factorization theorem for the light-ray density matrix, ρ=|Ψ⟩⟨Ψ|, inside high transverse momentum jets at the LHC. Using the light-ray operator product expansion, the scaling behavior of multipoint correlators can be computed from the expectation value of the twist-2 spin-J light-ray operators, O[J], in this state, Tr[ρO[J]]. We compute the light-ray density matrix at next-to-leading order, and combine this with results for the next-to-leading logarithmic scaling behavior of the correlators up to six-points, comparing with CMS open data. This theoretical accuracy allows us to resolve the quantum scaling dimensions of QCD light-ray operators inside jets at the LHC. Our factorization theorem for the light-ray density matrix at the LHC completes the link between recent developments in the study of energy correlators and LHC phenomenology, opening the door to a wide variety of precision jet substructure studies. Published by the American Physical Society 2025

Multijet event shape variables for Mueller-Navelet jet topologies

This paper presents a new set of multijet event shape variables introduced to further understand the Mueller-Navelet jet topology. This topology consists of having at least one pair of jets with a very large rapidity separation between them, treating additional jet activity inclusively. This multijet topology is expected to shed light on the radiation pattern that is expected in the high-energy limit of the strong interaction. The paper relies on a Monte Carlo event generator analysis. One set of predictions uses the ex event generator, which is based on Balitsky-Fadin-Kuraev-Lipatov (BFKL) perturbative quantum chromodynamics (pQCD) evolution with a resummation of large logarithms of energy at leading-logarithmic accuracy. The ex predictions are compared with a fixed-order next-to-leading order pQCD calculation using matched to the parton shower of ythia8 (NLO+PS), which is the standard for NLO generator predictions at the LHC. We find that both approaches lead to compatible results at current LHC energies, assuming the current experimental constraints for the reconstruction of low transverse momentum jets in ATLAS and CMS. This shows the reliability of the BFKL approach at describing the behavior of the strong interaction in the preasymptotic limit of high center-of-mass energies. Differences between the NLO+PS and the BFKL-based approaches are found when the jet multiplicity is increased or when the minimum transverse momentum of the jets is decreased. Published by the American Physical Society 2024

Flow characterization of a submerged inclined impinging pulse jet

This study investigated flow characteristics associated with a circular pulse-impinging jet on an inclined surface using dye visualization and particle image velocimetry techniques. The experiments are carried out for various pulse frequencies (0.1 < St < 0.9) of the jet, a constant angle of surface inclination (θ = 26°), and fixed surface spacing. The primary objective is to explore the flow dynamics aspect of pulse-inclined impinging jets with respect to the pulse frequency and Reynolds number. The present observation shows that at a certain degree of surface inclination (θ ≈ 28°), the jet momentum drives the entire flow in the downhill direction, which represents the critical angle of inclination. Furthermore, the critical angle of the inclination remains unchanged for both steady and pulse jets. The interaction of the inner and outer shear layers of the jet in the downhill direction highly depends on the pulse frequency, which is indeed triggered by the free jet vortices. In a free jet, the vortex formation and their growth depend on the jet shear layer response (convective acceleration) and the time available for vortex formation (local acceleration). Moreover, the instantaneous jet information reveals that the presence of the growing vortices increases the jet entrainment, and its movement along the surface enhances the mixing (shear stress) between the surrounding and boundary layer fluid. The results show that pulsation at Strouhal Number (St) = 0.44 help develop more coherent and durable vortices impinging on the surface, which is identical to the critical St for free and normal impinging jets. Pulsation near the critical St increases the jet entrainment and mixing between the inner and outer jet shear layers and is responsible for enhancement in the heat transfer rate. The results improve our understanding of heat transfer from pulse-inclined impinging jet and reinforce the existence of a critical St (= 0.44) with an inclined pulsing jet, providing the criteria for maximizing the heat transfer rate.

Automated Approach to Accurate, Precise, and Fast Detector Simulation and Reconstruction.

Detector simulation and reconstruction are a significant computational bottleneck in particle physics. We develop particle-flow neural-assisted simulations (parnassus) to address this challenge. Our deep learning model takes as input a point cloud (particles impinging on a detector) and produces a point cloud (reconstructed particles). By combining detector simulations and reconstruction into one step, we aim to minimize resource utilization and enable fast surrogate models suitable for application both inside and outside large collaborations. We demonstrate this approach using a publicly available dataset of jets passed through the full simulation and reconstruction pipeline of the Compact Muon Solenoid (CMS) experiment. We show that parnassus accurately mimics the CMS particle flow algorithm on the (statistically) same events it was trained on and can generalize to jet momentum and type outside of the training distribution.

Deep learning-based prediction of initiation jet momentum ratio in jet-induced oblique detonations

Oblique detonation, with its attributes of self-ignition, rapid heat release, and high thermal cycle efficiency, has garnered significant attention. It is crucial to explore methods that actively control the detonation at a shorter distance under less compressive conditions, and wall jets for active control stands out. However, when the jet momentum ratio excessively exceeds the critical value, it not only leads to resource wastage but may also compromise the outlet thrust performance. Thus, this paper presents a novel deep learning-based method for predicting the jet momentum ratio to ensure detonation with a sufficient margin while minimizing its value across various flight conditions. Firstly, the proposed methodology utilizes a deep neural network (DNN) to classify detonation status under different operating conditions. Building upon the concept of incremental learning, knowledge acquired by the classification network is repurposed to identify the transition point between detonation initiation failure and success. To address potential initiation failure issues in practical applications when seeking the critical jet momentum ratio, we elevate the threshold for the probability of successful initiation, defining such the ratio as the "robust jet momentum ratio". The framework developed in this study enables rapid identification of the robust jet momentum ratio within 0.07 s. To improve the model's inadequate learning of the discontinuous features associated with initiation/initiation failure transitions, data augmentation techniques are employed. The improved model demonstrates efficient determination under two-dimensional variables of flight altitude and Mach number. This study addresses a key challenge in jet prediction by devising an adaptive strategy for tuning jet momentum ratios according to varying flight conditions. This work bears significant engineering application value in the realm of hypersonic propulsion technology.

Algorithms for optimizing systems with multiple extremum functionals

The problem of minimizing (maximizing) multiple extremum functionals (infinite-dimensional optimization) is considered. This problem cannot be solved by conventional gradient methods. New gradient methods with adaptive relaxation of steps in the vicinity of local extrema are proposed. The efficiency of the proposed methods is demonstrated by the example of optimizing the shape of a hydraulic gun nozzle with respect to the objective functional, which is the average force of the hydraulic pulse jet momentum acting on an obstacle. Two local maxima are found, the second of which is global; in the second maximum, the average force of the jet momentum is three times higher than in the first maximum. The corresponding nozzle shape is optimal. Conventional gradient methods have not found any maximum; i.e., they were unable to solve the problem.

Experimental study on the radiation characteristic of downward turbulent diffusion jet flame

Gaseous fuels are typical clean energy and transported through gas pipelines to household and factories. A downward jet flame occurs when the fuel gas leaks from the bottom of the pipelines, which causes severe damage to the surroundings due to the complicated interaction between flame buoyancy and jet momentum. In order to investigate the combustion characteristics of downward jet flame, a series experiments were carried out to analyze the flame morphology and radiation systematically. The results show that the flame width increased from the upper tip along the centerline to a maximum value, and then decreased till the flame lowest point. The maximum flame width appears at the position of 3/4 flame length near the flame lowest point. A weighted-multi-point source radiation model was employed for prediction of flame radiation of downward jets based on the flame actual shape. The flame radiant fraction was found to be in the range of 0.28–0.32, which is larger than that of the corresponding upward jets because the luminous downward jet flame generated relatively more soot than upward jet flame. The derived radiant fraction was used to predict radiative heat flux compared with the experimental data, which showed good agreement.

Aerodynamic investigation of an S-shaped intake employing sweeping jet actuators based on proper orthogonal decomposition

The central curvature change of the S-shaped intake exacerbates the three-dimensional flow separation, resulting in total pressure and swirl distortions at the outlet. In this paper, an efficient active flow control technique, the sweeping jet actuator, was applied to control flow separation. The instantaneous characteristics of the flow field inside and outside the actuator were revealed by using validated numerical simulation methods. In addition, the effect of the sweeping jet on the aerodynamic performance of the S-shaped intake was investigated. Proper orthogonal decomposition (POD), an analysis method used to extract the main feature components of data, was applied to decompose the flow field structure at the S-shaped intake outlet in this study. The results highlight the external flow field characteristics of the actuator, with a jet sweeping range of up to ±40° and a sweeping frequency of 1 500 Hz, corresponding to a Strouhal number of 0.018. When the jet momentum coefficient is only 0.116%, the total pressure loss coefficient and pressure distortion index are reduced by 5.6% and 24.76%, respectively. This study demonstrates the critical role of momentum injection and discretization in inhibiting flow separation in the channel. The POD-based analysis indicates that a sweeping jet with high momentum can significantly enhance the energy in the flow passage and reduce the vorticity intensity of the first three modes. The stable mode structures exist near the outlet, exhibiting excitation frequency and frequency-doubling properties. The findings of this research provide essential input conditions for subsequent distortion studies.

High-Lift Enhancement of an Airfoil Using Arrays of Discrete Wall Jets

The circulation of a high-lift airfoil is enhanced using a spanwise array of fluidically oscillating wall jets to engender a Coanda-like effect on the suction surface near the cove between the flap and the main element. The actuation jets manipulate the interaction between the main element boundary layer and the cove jet to overcome flow separation over the flap and yield high-lift performance that is comparable to or better than conventional high-lift airfoils. The fluidic actuation enables effective operation at larger flap deflections while diminishing the sensitivity to cove characteristics. The performance of the actuator array varies with both the jet momentum coefficient and the spanwise periodic jet spacing. It is shown that the lift increment per jet, which for a sufficiently sparse jet array is invariant with jet spacing, diminishes as jet spacing is reduced due to spanwise jet interactions. Accordingly, the overall lift increment scales with the number of active jets and jet density, and a characteristic spanwise jet spacing is identified for optimal performance.

Research on circulation control mechanisms based on Lagrangian dynamics

Circulation control technology greatly improves an aircraft's aerodynamic efficiency by employing high-speed jets at the wing's trailing edge, which generates the Coanda effect. This paper analyzes and reveals the mechanism of circulation control from the perspective of Lagrangian dynamics. First, simulate the circulation control airfoil using the shear stress transport turbulence model to obtain instantaneous flow field data under various jet momentum coefficients (Cμ) and angles of attack. Subsequently, from the perspective of Lagrangian dynamics, the mixing, material transport, and momentum transfer processes between the jet and the trailing-edge separation zone are analyzed using attracting Lagrangian Coherent Structures (aLCSs) under different jet momentum coefficients. Next, through the perspective of particle motion in the Lagrangian framework, the study reveals the accelerating effect of the Coanda jet on the low-speed fluid over the upper wing surface. Additionally, repelling Lagrangian Coherent Structures are used to characterize the downward movement of the leading-edge stagnation point after applying circulation control, and the impact of this movement on the flow state is analyzed. Finally, the analysis using aLCSs assesses the flow control effectiveness of Coanda jets as “virtual aerodynamic flaps.” This analysis helps to further understand the advantages of the “virtual rudder surface” formed by Coanda jet.

Enhancing hydraulic efficiency in jet impingement sprinklers: Comparative analysis of aperture ratios compared with non-impingement sprinklers

A jet impingement sprinkler was designed based on asymmetric collision between the primary and secondary jets to replace traditional rotating sprinklers that require additional water distribution devices to provide suitable water distribution at low pressures. The study focuses on the ratio of apertures between primary and secondary nozzles, deriving a theoretical relationship based on jet momentum. The factors contributing to the variation in hydraulic performance between jet-impingement and non-impinging sprinklers are elucidated by combining hydraulic performance experiments with experiments using high-speed photography (HSP). The results show that the developed jet impingement sprinkler achieved a smoother water distribution trend. The wetted radius and Christiansen's uniformity coefficient of the jet impingement sprinkler were evaluated using the Criteria Importance via the Intercriteria Correlation (CRITIC) method. A comparison of the average scores shows that an aperture ratio of 1.66 performs best under full pressure. By contrast, an aperture ratio of 1.33 exhibited superior performance at low pressure. Jet deflection angle and jet breakup length were obtained through HSP experiments. The relative error between the measured and theoretical jet deflection angles was less than 5%, demonstrating the reliability of the proposed theoretical calculation method. A non-linear curve was used to establish the relationship among the aperture ratio, diameter of the primary nozzle exit, jet breakup length, average measured jet deflection angle, working pressure, and wetted radius. The relative error between the calculated and measured values was within 4%, indicating the suitability of the new formula for calculating the wetted radius of jet impingement sprinklers.

Influence of hole blockage caused by thermal barrier coatings on the turbine vane endwall film cooling performance

Thermal barrier coating (TBC) is extensively employed to protect hot components in modern gas turbines due to its high thermal resistance. Laser spraying is used to apply ceramic coating powder onto the target surface. However, when coating the junction region between the endwall and vane, the angle of the sprayer cannot face the surface directly. As a result, excessive spraying in a specific direction will result in hole blockages. Such blockages can disrupt cooling jet outflow, impacting downstream film cooling performance. This study investigated the adiabatic effectiveness of turbine nozzle guide vane endwalls, considering hole blockages. The experiments utilizing pressure sensitive paint (PSP) technique and simulations were both conducted, and the numerical turbulence model was validated. For a turbine cascade vane endwall, the blockage mainly occurred on the film holes near the boundary. These blockages significantly altered film flow direction, and increased the cooling jet momentum. For the endwall with cylindrical holes, the impact of blockages on the endwall cooling performance varied with blowing ratios. For the endwall with fan-shaped holes, blockages enhanced the cooling performance. In contrast, blockages reduced the cooling performance of endwall with converging slot holes.

Hard jet substructure in a multistage approach

We present predictions and postdictions for a wide variety of hard jet-substructure observables using a multistage model within the framework. The details of the multistage model and the various parameter choices are described in []. A novel feature of this model is the presence of two stages of jet modification: a high-virtuality phase [modeled using the modular all twist transverse-scattering elastic-drag and radiation model ()], where modified coherence effects diminish medium-induced radiation, and a lower virtuality phase [modeled using the linear Boltzmann transport model ()], where parton splits are fully resolved by the medium as they endure multiple scattering induced energy loss. Energy-loss calculations are carried out on event-by-event viscous fluid dynamic backgrounds constrained by experimental data. The uniform and consistent descriptions of multiple experimental observables demonstrate the essential role of modified coherence effects and the multistage modeling of jet evolution. Using the best choice of parameters from [], and with no further tuning, we present calculations for the medium modified jet fragmentation function, the groomed jet momentum fraction zg and angular separation rg distributions, as well as the nuclear modification factor of groomed jets. These calculations provide accurate descriptions of published data from experiments at the Large Hadron Collider. Furthermore, we provide predictions from the multistage model for future measurements at the BNL Relativistic Heavy Ion Collider. Published by the American Physical Society 2024

Optimal Selection of Active Jet Parameters for a Ducted Tail Wing Aimed at Improving Aerodynamic Performance

The foldable tail of the box-type launch vehicle poses a risk of mechanical jamming during the launch process, which is not conducive to the smooth completion of the flight mission. The integrated nonfolding ducted tail proposed in this article can solve the problem of storing the tail in the launch box. Moreover, traditional mechanical control surfaces have been eliminated, and active jet control has been adopted to control the pitch direction of the flight attitude, which can improve the structural reliability of the tail wing. By studying the effects of parameters such as momentum coefficient, jet hole position, jet hole height, and jet angle on improving the aerodynamic performance of ducted tail wing, relatively good jet parameters are selected. Research has found that compared with jet hole height and jet angle, momentum coefficient and jet hole position are more effective in improving the aerodynamic performance of ducted tail wings. Under a trailing edge jet, a relatively good jet condition occurs when the jet hole height is equal to0.25% of the aerodynamic chord length, and the jet angle is equal to 0°. At this time, with the increase of the jet momentum coefficient, the effect of increasing the lift of the ducted tail wing is the best. Finally, a comparative analysis is conducted on the lift and drag characteristics between the ducted tail wing and traditional tail wing, and it is found that the ducted tail wing can generate lift at a 0° attack angle and will not stall in the high attack angle range of 12°~22°, with broad application prospects.

Incoherent diffractive production of jets in electron DIS off nuclei at high energy

We study incoherent diffractive production of two and three jets in electron-nucleus deep inelastic scattering (DIS) at small xBj using the color dipole picture and the effective theory of the color glass condensate (CGC). We consider color fluctuations in the CGC weight-function as the source of the nuclear break-up and the associated momentum transfer |t|. We focus on the regime in which the two jets are almost back-to-back in transverse space and have transverse momenta P⊥ much larger than both the momentum transfer and the saturation scale Qs. The cross section for producing such a hard dijet is parametrically dominated by large size fluctuations in the projectile wave-function that scatter strongly and for which a third, semihard, jet appears in the final state. The 2+1 jets cross section can be written in a factorized form in terms of incoherent quark and gluon diffractive transverse momentum distributions (DTMDs) when the third jet is explicit, or incoherent diffractive parton distribution functions (DPDFs) when the third jet is integrated over. We find that the DPDFs and the corresponding cross section saturate logarithmically when |t|≪Qs2, while they fall like 1/|t|2 in the regime Qs2≪|t|≪P⊥2. We further show that there is no angular correlation between the hard jet momentum and the momentum transfer. For typical EIC kinematics the 2 jets and 2+1 jets cross sections are of the same order. Published by the American Physical Society 2024

Numerical study on enhanced-diffusion characteristics of kerosene jet in supersonic crossflow

The enhanced-diffusion characteristics of kerosene jet in supersonic crossflow under different supersonic mainstream and kerosene injection conditions were discussed in this paper. Numerous numerical simulations were conducted under varying shock wave intensities, injection momentum flux ratio conditions based on Euler-Lagrangian method. The influence of low-enthalpy (Tt=300 K) and high-enthalpy (Tt=1680 K) supersonic inflow conditions on kerosene diffusion was also involved. The results indicate that the momentum flux ratio caused by injection and evaporation jointly determines the diffusion ability of kerosene. The increase of injection momentum flux ratio and shock wave intensity promotes both the penetration ability and evaporation gain. However, the relative growth rate of penetration depth decreases, and the relative growth rate of evaporation penetration gain increases. As the jet momentum flow ratio decreases and the shock wave intensity increases, the mixing efficiency and relative growth rate of kerosene increase. A judicious design of injection measures proves to be an effective approach for enhancing the diffusion and mixing of kerosene, which holds significant importance in further enhancing the performance of supersonic combustors.

Impact of Blowing Location on the Aerodynamic Characteristics Over the Delta Wing

The performance of an aircraft can be enhanced by altering the flow field favourably by adopting flow control techniques. The present study deals with the application of the active flow control methods on a sharp-edged delta wing with a wing sweep of 65°. The concept of blowing was employed as an active flow control technique. The blowing technique is applied on the suction surface of the delta wing by varying its location. The various identified locations of the blowing holes are 1.62 %, 3.24 % and 4.86 % of root chord from the leading edge to the centre of the blowing holes. The computation is performed using the commercial software ANSYS Fluent. An unsteady, incompressible Reynolds-averaged Navier–Stokes equation and the shear-stress transport k-ω turbulence model are employed. The angles of attack varied in the range of 0°<α<35° and Reynolds number is 2.64×106 and the jet momentum coefficient is fixed at 0.05. The blowing of air from the injection region enhances the strength of the leading-edge vortices, resulting in a delay in the vortex breakdown. The performance of the delta wing is greatly improved while using the blowing method specifically for the blowing holes located at 3.24 % of root chord from the leading edge compared to without the blowing method.

Learning active flow control strategies of a swept wing by intelligent wind tunnel

An intelligent wind tunnel using an active learning approach automates flow control experiments to discover the aerodynamic impact of sweeping jets on a swept wing. A Gaussian process regression model is established to study the jet actuator’s performance at various attack and flap deflection angles. By selectively focusing on the most informative experiments, the proposed framework was able to predict 3,721 wing conditions from just 55 experiments, significantly reducing the number of experiments required and leading to faster and cost-effective predictions. The results show that the angle of attack and flap deflection angle are coupled to affect the effectiveness of the sweeping jet. Meanwhile, increasing the jet momentum coefficient can contribute to lift enhancement; a momentum coefficient of 3% can increase the lift coefficient by at most 0.28. Additionally, the improvement effects are more pronounced when actuators are placed closer to the wing root.

Experimental study of rotating direction for dual-axial swirlers on the flow field and combustion characteristics of aero-engine combustor

The flow field structure for aero-engine combustor is one of the most important factors for combustion performance. To investigate how the rotating direction of dual-axial swirlers affects the flow field and combustion characteristics, particle image velocimetry (PIV) experiments were conducted in the primary combustion and intermediate zones. Additionally, planar laser induced fluorescence (PLIF) was used to map the distribution of kerosene and OH in the primary combustion zone. The results show that the swirling jets in co-swirl exhibit greater jet momentum, resulting in a longer primary recirculation zone and a larger deflection angle of the primary jets. This ultimately leads to a higher recirculation rate compared to counter-swirl. The primary jets define the boundary of the flow field structure. The rotating direction primarily affects the flow field structure upstream of the primary jets, exerts a relatively weaker influence on the intermediate zone, which is mainly affected by the deflection direction of the primary jets, and essentially has no impact on the dilution jets. Co-swirl has a relatively stable flow field than counter-swirl, whereas the flow field in counter-swirl is more chaotic, featuring a greater number of vortex cores in the primary recirculation zone. The coupling between the primary and swirling jets affects the mass transfer direction in the intermediate zone, which is reflected in the fact that the mass transfer is from top-left to bottom-right in co-swirl, while it is in the opposite direction in counter-swirl. OH is predominantly found in the swirling shear layers, the primary and secondary combustion zones, whereas kerosene is mainly concentrated in the shear layers of swirling jets. The kerosene distribution in co-swirl shows a larger and more concentrated expansion angle compared to counter-swirl. In contrast, the OH distribution downstream of counter-swirl is broader, with more intense combustion due to enhanced kerosene decomposition and fuel-air mixing. The smaller primary recirculation zone in counter-swirl forces the primary combustion zone to extend downstream, leading to a more intense reaction in the secondary recirculation zone.

Quantifying the jet energy loss in Pb+Pb collisions at LHC

In this work, we give a method to study the energy loss of jets in the medium using a variety of jet energy loss observables such as nuclear modification factor and transverse momentum asymmetry in dijets and γ\\documentclass[12pt]{minimal} \\usepackage{amsmath} \\usepackage{wasysym} \\usepackage{amsfonts} \\usepackage{amssymb} \\usepackage{amsbsy} \\usepackage{mathrsfs} \\usepackage{upgreek} \\setlength{\\oddsidemargin}{-69pt} \\begin{document}$$\\gamma $$\\end{document}-jets in heavy ion collisions. The energy loss of jets in the medium depends mainly on the size and the properties of medium viz. temperature and is a function of energy of the jets as predicted by various models. A Monte Carlo (MC) method is employed to generate the transverse momentum and path-lengths of the initial jets that undergo energy loss. Using different scenarios of energy loss, the transverse momentum and system size dependence of nuclear modification factors and different measures of dijet momentum imbalance at energies sNN\\documentclass[12pt]{minimal} \\usepackage{amsmath} \\usepackage{wasysym} \\usepackage{amsfonts} \\usepackage{amssymb} \\usepackage{amsbsy} \\usepackage{mathrsfs} \\usepackage{upgreek} \\setlength{\\oddsidemargin}{-69pt} \\begin{document}$$\\sqrt{s_{\ extrm{NN}}}$$\\end{document} = 2.76 TeV and 5.02 TeV and γ\\documentclass[12pt]{minimal} \\usepackage{amsmath} \\usepackage{wasysym} \\usepackage{amsfonts} \\usepackage{amssymb} \\usepackage{amsbsy} \\usepackage{mathrsfs} \\usepackage{upgreek} \\setlength{\\oddsidemargin}{-69pt} \\begin{document}$$\\gamma $$\\end{document}-jet asymmetry at sNN\\documentclass[12pt]{minimal} \\usepackage{amsmath} \\usepackage{wasysym} \\usepackage{amsfonts} \\usepackage{amssymb} \\usepackage{amsbsy} \\usepackage{mathrsfs} \\usepackage{upgreek} \\setlength{\\oddsidemargin}{-69pt} \\begin{document}$$\\sqrt{s_{\ extrm{NN}}}$$\\end{document} =2.76 TeV in Pb+Pb collisions are simulated. The results are compared with the measurements by ATLAS and CMS experiments as a function of transverse momentum and centrality. The study demonstrates how the system size and energy dependence of jet energy loss can be quantified using various experimental observables.