Study of the Aerodynamic Characteristic and Flight Trajectories in a Tail Fin-stabilized Projectile with Different Shapes

Li, Chun-Chi; Tai, C. H.; Lai, Cheng-Chyuan; Fu, Shang-Min; Tsai, Yen-Chun

doi:10.1016/j.proeng.2014.06.317

Cited by 5 publications

(3 citation statements)

References 1 publication

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“…The code that predicts aerodynamic coefficients was used to decide rolling moment effects at subsonic and supersonic speeds. Li et al [10] carried out wind tunnel test, the CFD simulation and MATLAB/Simulink to solve aerodynamics of the tailfin projectile. Karman-Tsien rule was utilized to convert air compressibility into 0.6 Mach data.…”

Section: Introductionmentioning

confidence: 99%

The effects of different wing configurations on missile aerodynamics

ŞUMNU,

GÜZELBEY

2023

Journal of Thermal Engineering

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In the present study, missile aerodynamic analysis is performed using different wing config-urations at subsonic and transonic speeds. The wing is critical component in point of aero-dynamic efficiency for a missile that speed is especially closer to transonic level because of flow separation. Flow on the wings may adversely effect tailfins of missile at high speed since it may cause vortex generation and flow disturbances. There are few studies that investigate the missile wing using different configurations at critical speeds when examined the previ-ous studies. Therefore, in this study, three different wing configurations are investigated and aerodynamic performance is compared with each other at 0.7 and 0.9 Mach numbers and 5° angle of attack (AoA). In beginning of this study, missile model with only tailfins is selected from previous study that contains experimental data. Because the experimental data for the selected missile model are available at supersonic speeds, the aerodynamic analysis to verify the solutions is carried out at supersonic speeds. After wing is mounted to the selected missile, aerodynamic analysis is carried out using three different wing configurations that are Tapered Leading Edge, Tapered Trailing Edge, and Double Tapered wings. Lift to drag ratio (CL/CD) is calculated to compare wing configurations and it is concluded that Tapered Leading Edge wing configuration shows higher performance then other wing configurations. CL/CD values are 2.327, 2.306, 2.303 at 0.7 Mach number and 2.45, 2.429, 2.423 at 0.9 Mach number for Tapered Leading Edge, Tapered Trailing Edge, and Double Tapered, respectively. When the results are compared each other, CL/CD values at 0.9 Mach number is higher about % 5.28, %5.33 and %5.21 than the CL/CD values at 0.7 Mach number for missile with Tapered Leading Edge, Tapered Trailing Edge, and Double Tapered, respectively.

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Section: Introductionmentioning

confidence: 99%

The effects of different wing configurations on missile aerodynamics

ŞUMNU,

GÜZELBEY

2023

Journal of Thermal Engineering

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“…Intensity of negative pressure area at the rear end of car is also evident which could be minimized for subsequent drag reduction. Lia et al, analyzed a tail fin-stabilized projectile with two different shapes under four degree of freedom, angle of attack -8 to 8 degrees and Mach 0.6 using CFD, MATLAB/Simulink and low speed wind tunnel testing [10]. Both the design shows an excellent aerodynamics while the improved design had an increased range of 26.83% to that of original prototype.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamics Analysis and Range Enhancement Study of 81mm Mortar Shell (French Design)

Kalvin

Taweekun

Mustafa

et al. 2021

ARFMTS

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The aim of this research is performing the Computational Fluid Dynamics (CFD) analysis of 81mm Mortar Shell (French Design). The analysis is performed using ANSYS Fluent Software on three different Mach numbers (0.72, 0.76, and 0.84) and results are compared with existing design of 81mm HE M57D A2 Mortar. The drag coefficient of new modified design is found to be less than the existing model. The range of mortar shell is increased by 271 meters because of low drag coefficient with 5.96% percent increase in range and 15.73% decrease in drag coefficient value. Parabolic type; light weighted material fuze casing applied over the existing fuze will result in increase in aerodynamics, range enhancement and drag coefficient reduction. Weight optimization by using lighter material for mortar components and increasing the muzzle velocity can also increase flight duration of the projectile and increase its range. The analysis on 81mm Mortar Shell is a part of range enhancement study to overcome the short fall in required range of mortar shells.

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“…Compared with the above methods, CFD is the kind of simulation method by which we can intuitively get the distribution of the flow field, and for the reasons that the process is simple and the results reliable and accurate, it is widely used for aerodynamic parameter calculations of guided projectiles, resulting in it becoming a hot area of aerodynamic research. For example, the CFD simulation has been used for the aerodynamic characteristic study of the spin-stabilized artillery shell by Hamel and Gagnon, 1 Je et al, 2 Fu et al, 3 and Yin et al, 4 used for the aerodynamic characteristic study of the fin-stabilized rocket by Afzal et al, 5 Sahu,6 Zhimin et al, 7 Sahu et al, 8 Zhang et al, 9 and López et al, 10 and used for the aerodynamic characteristic study of the mortar projectile by Su et al, 11 Li et al, 12 and Chengen et al 13 Most of the CFD simulations that are used for aerodynamic characteristic studies on projectiles, are focused on the effect of geometry on the aerodynamic parameter. The contrastive analysis of the CFD simulation method is relatively less.…”

Section: Introductionmentioning

confidence: 99%

Investigation of the aerodynamic parameters simulation method of a guided rocket

Chen

Gao

2017

SIMULATION

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Orthogonal design method is adopted to investigate the aerodynamic parameters simulation method of a canard guided rocket, in order to obtain one simulation method which can calculate the aerodynamic parameters quickly, reliably, and accurately. The turbulence model, mesh size, y + value and flow field size, which are regarded as the main factors in computational fluid dynamics (CFD) simulation, are divided into three levels for comparative analysis. Nine simulation combination schemes, which are representative and comprehensive, are singled out based on orthogonal table. The axial force coefficient and normal force coefficient in subsonic, transonic, and supersonic conditions are respectively calculated with these nine simulation combination schemes. The best simulation combination schemes in subsonic, transonic, and supersonic conditions are respectively picked out by intuitive analysis and synthesis balance analysis. The aerodynamic parameters in different velocities and attack angles, which were obtained by corresponding best simulation combination schemes, prove that the best simulation combination schemes are accurate. The results provide basis for the aerodynamic characteristic study of the canard guided rocket, and this research method can be used for the investigation on aerodynamic parameters simulation method of projectiles with different configurations.

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Study of the Aerodynamic Characteristic and Flight Trajectories in a Tail Fin-stabilized Projectile with Different Shapes

Cited by 5 publications

References 1 publication

The effects of different wing configurations on missile aerodynamics

The effects of different wing configurations on missile aerodynamics

Aerodynamics Analysis and Range Enhancement Study of 81mm Mortar Shell (French Design)

Investigation of the aerodynamic parameters simulation method of a guided rocket

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