Drag Values Research Articles

Influence mechanism of magnetic field direction on magnetic drag of reentry vehicle and better magnetic field direction

The magnetic field condition has a great influence on the magnetic control drag of reentry vehicle, so it is an important research topic to select appropriate magnetic field condition to control the drag force of vehicle. This paper analyzes the magnetic control drag by solving the hypersonic magnetohydrodynamic equations and combining the magnetic field working conditions, studies the influence of the axisymmetric magnetic field direction on the drag, supplements the mechanism of Lorentz force, pressure and conductivity on the axisymmetric magnetic control drag, and compares the drag value and drag composition ratio under different magnetic field directions. The problem is solved numerically for a particular model of a dipole magnetic field. Under different dipole magnetic fields, the magnitude and distribution shape of Lorentz force are different. There are several dividing lines where the Lorentz force is 0, and the Lorentz force directions on both sides are opposite, and this line divides the Lorentz force field into multiple parts. In addition, it is found that the change of the angle between the axis of the aircraft and the direction of the magnetic field will cause the change of the aircraft resistance, which will reduce or increase it.

Effects of physical properties of supercritical water on coarse graining of particle cluster

The coarse graining of particle cluster is of great significance to the study of a fluidized bed. The effects of variations in the physical properties of supercritical water on the coarse graining of particle cluster are investigated in this work. The drag coefficient distributions of the particle cluster are not influenced by the physical properties. However, the physical properties have effects on the values of drag coefficient. The effects of physical properties are weaker in the case of large particle concentrations. Furthermore, the physical properties lead to that the effect of particle cluster wake on the drag of downstream particles being significantly different from that of constant property flow. The variation trend of drag of coarse graining particle is consistent with that of isolated particle. The physical properties lead to significant differences in the values of drag. In this paper, the dominance of the effects of physical properties in a variety of cases is confirmed. Finally, a physical properties effect model is developed accordingly.

Characterization of the Unsteady Wake Aerodynamics for an Industry Relevant Road Vehicle Geometry Using LES

A wall-resolved large eddy simulation (WRLES) study of the flow around a 15% scale model of the Nissan NDP, an electric concept vehicle developed by Nissan, at Re_H=100{,}000 is presented. First, wake asymmetries and the associated possibility of wake bimodality occurring are investigated by comparing the flow fields around “squareback” and cavity variants of the Nissan NDP. It is highlighted that there is no noteworthy long-term wake asymmetry in the spanwise direction for both configurations and that there is, instead, symmetric spanwise vortex shedding, as highlighted through the use of proper orthogonal decomposition (POD) post-processing. One can, therefore, exclude the existence of classical wake bimodality in the spanwise direction that has been observed for the Ahmed body. However, the wake does explore the vehicle’s rear space in the spanwise direction rapidly over non-dimensional time intervals of {mathcal {O}}(10). Meanwhile, there is a strong wake tilt in the vertical direction due to the presence of a ground, the vehicle geometry’s vertical asymmetry, and the detachment of a powerful hairpin vortex from the vehicle’s roof. When looking at POD of the flow field in a vertical plane, asymmetric vortex shedding, similar to that observed for the Ahmed body by Hesse and Morgans (2021) in the spanwise plane, is found. This suggests that wake bimodality in the vertical direction could occur for the Nissan NDP—the presented results are not conclusive, as the provided non-dimensional simulation duration of t^* sim 60 is insufficient for the bimodal phenomenon that occurs at t^* sim 1000. Additionally, the discernible impact of having a cavity at the rear of the NDP is to allow the wake to explore a larger vehicle base space (i.e. the wake is able to move more freely). This, coupled to a 5% reduction in rear base area, translates to a drag reduction compared to the “squareback” variant of 13.6%. Second, in a more qualitative analysis of simulation results, the effect of using a moving ground in simulation as compared to a stationary ground is assessed. This is only done for the cavity variant of the Nissan NDP. It is found that, for this vehicle geometry, a stationary ground is associated with the occurrence of low pressure clockwise rotating (when looking into the page of the vertical plane) vortices near the ground caused by the flow deceleration just aft of the vehicle base, where the flow moves from the vehicle under-body toward the wake’s far-field region. The consequence of this flow phenomenon is to simulate a 3.3% higher drag value with the stationary ground simulation as compared to the moving ground simulation. Thus, although the moving ground should be more representative of the real-world, the stationary ground simulation is more conservative in aerodynamic terms and should be used if developing the NDP vehicle completely digitally using a virtual twin. By over-design, the stationary ground variant namely ensures that the drag key performance indicator (KPI) is met.

Passive Flow Control around Two Side‐by‐Side Square Cylinders Using a Control Plate

This article is concerned with the numerical analysis of reduction of fluid forces (drag and lift) and suppression of vortex shedding around two side‐by‐side square cylinders using the lattice Boltzmann method. For this purpose, a passive flow control methodology is adopted in which a flat plate (termed as the control plate) is placed at the upstream position of cylinders. The gap ratio (g) between the cylinders and the plate is varied from 0 to 4 while the height of the control plate is varied from 0.2 to 0.8 at fixed Reynolds number of 150. Different flow patterns are found in this study depending on the gap ratios and different heights of the control plate. These flow patterns are single bluff body flow, flip‐flopping flow, and antiphase vortex shedding flow patterns. The narrow gap ratio (g = 0.5) is found to have more impact in terms of force reduction and flow control as compared to larger gap ratios. This article also shows that the fluid flow parameters such as the mean drag coefficient, the Strouhal number, and rms values of drag and lift coefficients of both cylinders reduce considerably due to the control plate as compared to without the control plate. In this regard, it is found that the mean drag coefficient of upper cylinder reduces upto 45.94%, the Strouhal number of both cylinders reduces upto 18.66%, while a maximum reduction of 83.47% and 95.39% is observed in root‐mean‐square values of drag and lift coefficients of upper cylinder, respectively. Another important finding of this article is that the control plate does not suppress forces and control flow at all gap ratios and heights of control plate considered in this article. In some cases, the flow‐induced forces were found to be increasing as compared to without the control plate, and this generally happened at higher gap ratios.

Parabolic transport measurement of hydrodynamic forces for flow around circular/triangular distance dependent obstructions: Finite element analysis

<abstract><p>The present effort is the low Reynolds finite element hybrid meshed solution to apprehend the flow field properties in a convergent-divergent (CD) domain having engineering standpoints applications. To be more specific, we have considered the CD domain rooted with two types of obstructions in three various arrangements namely triangular/triangular, circular/triangular, and triangular/circular in CD throat. The viscous fluid is introduced from the inlet and interacts with installed obstacles. The moving stream in the channel is modelled mathematically in terms of the two-dimensional time-independent equations. The finite element approach is used to disclose numerical solutions by means of a hybrid meshing scheme. Optimized drag and lift force values encountered by an obstruction are offered through line integration across the external obstruction surfaces. In comparison to obstruction in left vicinity, the lift force faced by the triangle obstacle on the right side of the CD throat is larger. Furthermore, as compared to the drag force faced by the triangular obstruction in the same proximity, the circular obstacle experienced greater values as a drag. The lifting force sensed by the triangular cylinder is larger than circular cylinders. The assessment of marine hydrodynamic forces and stability individualities for fully or partially submerged objects in ocean engineering will benefit from the results of this study.</p></abstract>

Investigation on the Influence of Vortex Generators on Aerofoil

Boundary layer separation is a major cause of concern in the wind turbine and aerospace industries as it adversely affects the performance of aircraft wings and wind turbine blades. The immediate result of flow separation over an aerofoil causes decrease in lift and an increase in drag within the stall range, both of which have a negative impact on the overall performance of aerofoils in the wind turbines. To overcome this problem, vortex generators (VGs) are used for increasing lift force and thus increasing the rotational speed of the blade. They act like small protrusions on wing surfaces which helps in energizing the boundary layers thereby delaying the separation and providing a wide range of attached flow over aerofoil surface. The present research illustrates the comparative analysis on the various shapes of VGs such as rectangular, triangular and gothic by varying the angle of attacks (AoA) from 0-15. The analysis is performed on NACA0012 aerofoil, which is developed using SOLIDWORKS and analysed on ANSYS 2020 R2 software. The values of lift (Cl) and drag (Cd) coefficients with and without VGs are determined using ANSYS fluent and the contours for velocity and pressure are further mapped using CFD Post. The stall angle is evaluated for each of the VG shapes representing the maximum lift that an aerofoil can achieve. Pressure coefficient plots are studied in order to investigate the amount of pressure difference created and its influence AoA at the leading edge of the aerofoil. An overall comparison is made to determine the best VG shape that delivers maximum lift to the aerofoil. The optimum configuration found for VG is gothic shape which illustrates the maximum lift coefficient value, which is highest amongst all the three shapes.

Aerodynamic Drag Reduction of Commercial Ground Vehicles Using Numerical Techniques

Automobiles of today warrants improved aerodynamic behaviour that results in low drag producing vehicles. Such optimally designed vehicles offer advantages such as better overall performance, desirable driveability, rapid response, improved stability and added fuel economy. In this paper, an attempt is made to accomplish lower drag coefficient by incorporating the dimples shape on the vehicle roof surface. Aerodynamic flow analysis was conducted with and without dimple shape effect on a bus truck trailer and commercial vehicles, using ANSYS Fluent software tool. Effect of different sized and shaped dimples on aerodynamic performance was analysed as well. Results obtained were validated with available literature and it is found that coefficient of drag obtained showed less than 10 % error. It was found that drag values were significantly reduced with dimple effect on both the commercial vehicles. Both models demonstrated that the fluid flowing on the surface did not separate from the vehicle roof, and the vortex size at the back was reduced. Further paper gives a detailed study of various parameters like turbulence model effect, pressure distribution on the vehicles, temperature and mach number variations. This study is proposed to enhance energy efficiency of the automobiles as better aerodynamics improves their mileage and fuel economy.

Supersonic flow investigation of a drag reducing conical spike on a hemispherically blunted nose body

Experiments and computations were made at a Mach number of 2.0 on a hemispherical blunt nose body with a conical spike of L/D ratio = 1.0. Attempts were made to alter the axisymmetric cavity formation between the spike tip head and the blunt base body. Qualitative measurements and quantitative details indicate the changes which support the drag reduction beyond the conventional sharp spike. Additional drops in drag values were observed by the techniques used in the present investigation. A linear trend of drag reduction is obtained with conical spikes which lead to the drag of a pure conical body.

Flow characteristics comparison of PIV and numerical prediction results for an unmanned underwater vehicle positioned close to the free surface

In the present paper, flow characteristics of an Unmanned Underwater Vehicle (UUV) with a commonly used Myring profile were investigated numerically and experimentally using Computational Fluid Dynamics (CFD) and the Particle Image Velocimetry (PIV) technique under the influence of free surface. The 3-D and two-phase flow simulation generated using the Volume of Fluid (VOF) were carried out using the Large Eddy Simulation (LES) turbulence model for high accuracy in both near free-surface and almost uniform flow conditions. Due to the presence of the free-surface effect, dynamics and unsteady instantaneous flow characteristics such as force and moment coefficients, streamlines topology, and pressure values on the body surface along with vorticity structures were found to be very chaotic and have irregular motion in the wake while the followable variation trend of the time-averaged properties was obtained to show critical immersion ratio. The immersion ratios of 0.75≤ h/D≤3.50 were examined at Reynolds numbers Re = 2.0 × 104 and 4.0 × 104. Jet-like flow between the UUV body and the free surface of the water was detected at the immersion ratio of h/D = 0.75, which caused a substantial asymmetry in flow structures, resulting in highest drag and lift values. Increased surface disturbance at Re = 4.0 × 104 caused air introduction into via jet-like flow in h/D = 0.75, which caused positive lift. Hydrodynamic coefficients and isosurfaces shown that the free-surface effect decreased significantly up to h/D = 1.50 at constant Reynolds numbers. Further investigation of time-averaged velocity components, streamlines, vorticity and turbulence statistics revealed that h/D = 1.50 acted as a transitional immersion ratio as the flow structure changed significantly with Reynolds numbers. The utilized CFD approach yielded especially excellent agreement with the PIV measurements with the discrepancy which varies from 1% to 15% in near wake for streamwise velocity components to simulate the essential unmeasured flow features needed in the research and development process of UUVs when they move below the free surface.

Velocity Dissipation Approach on Drag Analysis using CFD for Shoreline Defense

Coastal forest protects the shoreline from erosion and extreme events by attenuating wave and velocity by obstructing the flow of water through the forest. Lack of understanding on tree drag coefficients vary with tree morphology density and arrangement is a major source of uncertainty that close related to the shoreline belt span. This study evaluates the behavior of velocity flow through the mangrove aerial root system. The analysis process starts with the drag value analysis of stilt roots model and continues by analyzing the dissipation behavior of velocity on the analysis path. Both analyses were carried out using Computational Fluid Dynamics (CFD) by ANSYS Fluent program. Root zone of the stilt root model is observed contributes higher velocity dissipation than stem zone. The highest drag value is observed at the average of 32.75% of the stilt root height. Higher density of forest stands contribute to higher dissipation of velocity. The study recommends the minimum span 200 m of shoreline forest belt to allow the ecosystem to be shoreline protector naturally. Therefore this study recommend for artificial protector for mangrove seedlings in the early growth. The results are useful for forest managers to restore mangroves and support the establishment of mangrove seedlings for coastal risk reduction strategies.

Study of flow through and around a pair of porous cylinders covering steady and unsteady regimes

The present article focuses on the incompressible flow around two identical porous cylinders for a side-by-side configuration in a closed channel. The formation of various flow patterns behind permeable cylinders is more intriguing and further compelling to assimilate the underlying flow physics. The effects of three critical parameters, gap ratio (s/d), Reynolds number (Re), and the Darcy number (Da), on the flow behavior are investigated for the ranges of s/d = 1.5–6, Re = 5–100, and Da = 10−6–10−2. Both attached standing and detached vortices are observed in a steady flow regime. One secondary wake structure is also observed for s/d = 1.5, whose size gradually reduces with increased permeability. In an unsteady flow regime, the jet-like flow in the gap section mainly governs the unsteady wake patterns. In the low range of Darcy numbers (10−6–10−3), asymmetric flip-flopping patterns are observed for s/d = 1.5 and 2; and synchronized wake patterns either in anti-phase or in-phase mode are observed for higher gap ratios. The velocity profiles in the gap and free sides of the cylinders and pressure distribution along the porous surface are also discussed to facilitate the understanding of different wake patterns. Surprisingly, a case of pattern shifting from anti-phase to in-phase mode is observed when permeability is altered for the same flow-time. Symmetric and clustered strands of vorticity near the centerline are observed for all cases of s/d at Da = 10−2. The effects of Re, s/d, and Da on the drag coefficient and critical Reynolds number are also discussed. A jump in the drag values, a maximum of 13.9% for s/d = 3.5, is witnessed for the mid-range of Da at higher Re.

Streamline Effect Improvement of Additive Manufactured Airfoil Utilizing Dynamic Stream Control Procedure

In the era of fast transport, to create inventive stream flow management solutions that are capable of diminishing the aerodynamic drag of the vehicles, there is a need to modify the flow characteristics over the vehicle by deferring or expelling the position of the flow partition. The objective of this study involves the parameterized design of an airfoil utilizing the Bezier curve technique with the assistance of the simulation program. For flow regulations, synthetic jet modules are ingrained at different percentages of the chord to manage the stall characteristics. The parametrization system, combined with the stream control method, can give a much better insight into flow re-energization and pave some way for the reduction of the wake. Digital fabrication technique (3d printing or Rapid Prototyping method) is used to fabricate the end product for aerodynamic testing. The comparative outcome showed a reduction in drag at certain angles of attack due to the surface finish obtained. By comparing the results, the aerodynamic efficiency showed a significant rise of 13.05% at lower angles of attack when compressed gas was used in the synthetic jet closer to the frontier edge of the airfoil. Near the stall angle of attack, the coefficient of lift (Cl) and coefficient of drag (Cd) values showed no progress.

Analysis of effects of aerodynamic interference on dynamic response of suspended monorail wind–vehicle–bridge system using joint simulation approach

A dynamic simulation model of a suspended monorail vehicle–bridge system was developed using a joint simulation approach based on ANSYS and SIMPACK. Moreover, the aerodynamic coefficients of the vehicle–bridge system were measured through a wind-tunnel test, in which a wind load was applied as an external excitation. The variation law of the dynamic response of a double-line suspended monorail vehicle–bridge system with respect to the line spacing under aerodynamic interference was systematically studied, and the following results were obtained. (1) The effect of the vehicle–bridge combination on the aerodynamic coefficient was significant. In the case of one vehicle, the vehicle on the downstream line was slightly less affected by the crosswind than that on the upstream line. For these two vehicles, the three-component force coefficient of the downstream vehicle was far smaller than that of the upstream vehicle. (2) In the case of two vehicles, an increase in the spacing ratio reduced the drag of the vehicles. When the spacing ratio exceeded 4.5, the change in the three-component force of the upstream vehicle was no longer obvious, but the drag value for the downstream vehicle changed from negative to positive. (3) With an increase in the spacing ratio, the vehicle acceleration generally increased, but the changes in the acceleration and displacement of the bridge were insignificant. (4) During the meeting of two vehicles, the vehicle running on the upstream side is easy to be affected by winds than on the downstream side, which leads to the result that the dynamic response of the upstream vehicle and bridge are larger than that of the downstream side.

Comparative study of hatchback vehicles through modelling and computational tools

The purpose of this research is to explore the world of Computer-Aided Modelling and then apply its tools to benefit the automotive sector. Three commercially available economical vehicles in Pakistan, namely (i) Daihatsu Mira X, (ii) Honda N-One and (iii) Suzuki Wagon R, have been virtually modelled in Computer-Aided Design (CAD) software by using CATIA-V5R19. This research focuses on providing all the steps that are needed to transform an existing real vehicle body to a virtual vehicle body. Detailed comparisons of all the three hatchback vehicles have performed which determined the most crucial factors of the body that affect the performance of the vehicle. Computational fluid dynamics (CFD) analysis is also performed using SolidWorks flow simulation tool. The base drag and lift coefficients of selected vehicles are computed and compared. Furthermore, the influence of different diffuser angles on the aerodynamics characteristics of vehicle is also investigated. The drag and lift coefficients are computed at different diffuser angles to find out the optimum angle of diffuser. With the increase in diffuser angle, it is found that the total lift coefficient decreases but there is not much effect on drag coefficient for all hatchback vehicles. In addition, this study revealed that Daihatsu Mira X is the most stable and fuel economic vehicle among all three considered vehicles because of its lower centre of gravity co-ordinates and smaller coefficient of drag values at all diffuser angles.

Numerical simulation of the aerodynamic characteristics of the NACA 0018 airfoil at medium range Reynolds number

In the present work, simulations of the flow around the NACA 0018 airfoil operating at Reynolds number 7 × 105 are performed using the EasyCFD software package. The influence of the advection scheme and turbulence model on the computed lift, drag and momentum coefficients is presented and an evaluation of the obtained results is made by comparison with published experimental data. It is concluded that predictions agree very well with experimental data up to 18° angle of attack, when using the SST turbulence model with the second order advection scheme. Limitations of simulations are shown when the airfoil operates at larger angles of attack, where unsteady periodic flow is verified. The turbulence model and the advection scheme affects both lift and drag values, but to a larger extent for drag. Predictions at high angles of attack overestimate both lift and drag coefficients, but underestimate the momentum coefficient.

Computational fluid dynamics (CFD) based propeller design improvement for high altitude long endurance (HALE) UAV

PurposeHigh Altitude Long Endurance Unmanned Aerial Vehicle (HALE UAV) driven by a hybrid power between battery and solar panel have attracted many researchers. The HALE UAV which develops at Bandung Institute of Technology has design requirements of a 63 kg MTOW with a cruise velocity of 22.1 m/s at an altitude of 60,000 ft propelled by two propellers. The main problems that arise with the propellers gained from the market are these propellers cannot operate properly at the cruise phase due to inadequate thrust and high drag value. This paper aims to design a propeller that solves those problems.Design/methodology/approachThe Larrabee method is used to design this propeller geometry with an output in the form of a chord and twist distribution. The CFD approach method is used to improve the design resulting from the Larrabee method.FindingsThis study shows that the inputted thrust value of the propeller designed using the Larrabee method is always higher than the thrust value resulting from the CFD simulation with a difference of around 20% so a design improvement process using CFD is required.Originality/valueThe analysis of propeller implementation in various mission profiles shows that this propeller can operate fully from climbing at sea level to cruising flight at an altitude of 60,000 ft. The same procedure can be applied in other HALE UAV cases to generate a propeller design with different objectives.

Scale effect of applying Tauti's law in model experiment: CFD models for flow across planar netting

Tauti's similarity criterion is the core problem in physical experiments and is associated with the accuracy of the final estimation of physical system results. In this study, a computational fluid dynamics (CFD) simulation study related to the steady fluid hydrodynamic forces acting on netting was performed by solving Reynolds-averaged Navier–Stokes equations. First, the prediction accuracy of the netting hydrodynamic forces in a flume tank was investigated. Subsequently, the basic characteristics of CFD simulations to reproduce the flow field and the hydrodynamics of a prototype net were studied. The flow field around the netting was analysed using five different schemes. When a same scale ratio was adopted (λ = λ′ = λ″, where λ is the large-scale ratio, and λ′ and λ″, are the small-scale ratios of the mesh length and twine diameter, respectively), the results demonstrate that as the scale ratio increases, the drag coefficient of the netting increases, and the relative error between the drag restored by the Tauti criterion and the original netting drag force also increases. When adopting a double different scale ratio (λ,λ′=λ″) in the schemes of the prototype netting, the drag coefficient of the netting decreased with an increase in the scale ratio, and the drag value gradually deviated from the standard value. When thress different scale ratios (λ,λ′,λ″) were adopted under various mesh sizes and twine diameters, the flow velocity reduction trend downstream of the netting was opposite to that upstream, verifying that the same small-scale ratio is accurate for the reduction result. Finally, we confirmed the improvement in the selection of the scale ratio of the Tauti criterion and the correction suggestions after adopting the scale ratio. The aforementioned findings can provide a theoretical guidance for the physical testing and design of fishing gear.

Unsteady MHD Tangent Hyperbolic Nanofluid Past a Wedge Filled with Gyrotactic Micro-Organism

In this numerical investigation, tangent hyperbolic nanofluid past a wedge-shaped surface filled with gyrotactic micro-organisms has been examined. The simulations have been performed in the presence of Ohmic heating and linear thermal radiation effect. After using similarity transformation to convert modeled PDEs into ODEs, the system of ODEs is tackled with the aid of shooting technique. For the authenticity of the code, the present numerical data have been compared with the already existing results in the literature. The impact of important governing parameters on velocity, concentration, temperature, and motile density distribution is examined graphically. Furthermore, the numerical values of the surface drag, heat transfer rate, mass transfer rate, and motile density number are computed and represented in the tabular form. Our simulations indicate that the Nusselt number is enhanced for the growing values of unsteadiness and the velocity ratio parameters. Moreover, a significant raise in nanofluid velocity is observed as magnetic number gets bigger whereas the temperature profile is depressed. For the above proposed model, it can be concluded that heat and mass can be enhanced by using gyrotactic micro-organism.

Numerical study of drag force on the UAV tilt and fixed wing model during vertical take off landing

A hybrid vertical take-off landing (VTOL) UAV combines the concepts of fixed-wing and rotary-wing UAV aircraft in one platform while performing in both conventional and vertical take-off landings. This aircraft has a drawback of significant drag force generated due to fixed-wing. Therefore, a Tilt-Wing often utilized to overcome this obstacle whereby it could be adjusted to the vertical and horizontal directions. To enhance the understanding of generated drag force on both wing model, this study was performed by examine the drag characteristic of the VTOL UAV. The simulations were carried out in the wind speed range by 1.4 m/s, 4.17 m/s, and 6.94 m/s. Simulation results showed that the drag of the UAV Hybrid Tilt-Wing and Fixed-Wing increased at the speed of 1.4 m/s to 6.94 m/s while the highest drag value was 177.51 N on a Fixed-Wing UAV aircraft and 1.97 N on a Tilt-Wing UAV aircraft. The result concluded that Tilt-Wing UAV has less drag which was more efficient than fixed-wing.

Shape optimization of a hyperloop pod’s head and tail using a multi-resolution morphing method

In the current study, the 3D shape optimization of a hyperloop pod’s head and tail is carried out to improve the pod’s aerodynamic performance. For shape exploration, a new shape design method called multi-resolution morphing is applied with three baseline hyperloop models, where each has its own aerodynamic characteristics. As a result, an optimal hyperloop pod with a drag value that is 7.5% smaller with respect to the baseline model and optimal pods with well-balanced drag and lift values are obtained. From further investigations, several meaningful results are also discovered. First, the shape of the tail has a greater impact on the drag and lift of the hyperloop pod than the shape of the head, and this difference is more remarkable in the drag than the lift. Second, changing the shape of the head does not elicit a large effect on the aerodynamic performance of the tail and vice versa. Accordingly, the optimization of a hyperloop pod’s head and tail can be implemented independently. A high correlation between the strength of the turbulent kinetic energy around the tail and drag is also found from a flow comparison between the optimal models. Finally, the local flow characteristics are similar for the models that are constructed with the same coefficients of the high-degree spherical harmonics. This indicates that it is possible to transfer the local flow characteristics of one model to the other via the multi-resolution morphing method.