scholarly journals Prediction and Analysis of the Aerodynamic Characteristics of a Spinning Projectile Based on Computational Fluid Dynamics

2020 ◽  
Vol 2020 ◽  
pp. 1-12
Author(s):  
Arim Ko ◽  
Kyoungsik Chang ◽  
Dong-Jin Sheen ◽  
Chi-Hoon Lee ◽  
Yongin Park ◽  
...  
Keyword(s):  
Mach Number ◽  
Nonlinear Behavior ◽  
Semiempirical Method ◽  
Aerodynamic Coefficients ◽  
Magnus Force ◽  
Force Coefficient ◽  
Moment Coefficient ◽  
Quadratic Drag ◽  
Spinning Projectile ◽  
Simulation Results

Numerical simulations of a spinning projectile with a diameter of 120 mm were conducted to predict the aerodynamic coefficients, and the CFD results were compared with the semiempirical method, PRODAS. Six coefficients or coefficient derivatives, including zero and the quadratic drag coefficient, lift force coefficient derivative, Magnus force coefficient derivative, overturning moment coefficient, and spinning damping moment coefficient, which are important parameters for solving the equations of motion of the spinning projectile, were investigated. Additionally, the nonlinear behavior of these coefficients and coefficient derivatives were analyzed through the predicted flow fields. The considered Mach number ranges from 0.14 to 1.2, and the nondimensional spinning rate (PD/2V) is set to 0.186. To calculate the coefficient derivative of the corresponding force or moment, additional simulations were conducted at the angle of attack of 2.5 degrees. The simulation results were able to predict nonlinear behavior, the especially abrupt change of the predicted coefficients and derivatives at the transonic Mach number, 0.95. The simulation results, including the skin friction, pressure, and velocity field, allow the characterization of the nonlinear behavior of the aerodynamic coefficients, thus, enabling better predictions of projectile trajectories.

Lateral-Directional Aerodynamics of a Canard Guided Spin Stabilized Projectile at Supersonic Velocity

2011 ◽  
Vol 110-116 ◽  
pp. 4343-4350 ◽  
Author(s):  
Xiu Ling Ji ◽  
Hai Peng Wang ◽  
Shi Ming Zeng ◽  
Chen Yang Jia
Keyword(s):  
Computational Study ◽  
Cfd Modeling ◽  
Aerodynamic Coefficients ◽  
Force Coefficient ◽  
Modeling And Analysis ◽  
Moment Coefficient ◽  
Computational Fluid Dynamics Cfd ◽  
Spinning Projectile ◽  
Yaw Moment ◽  
Side Force Coefficient

A computational study performed for a canard guided spin stabilized projectile using finite volume TVD schemes is described in this paper. Computational Fluid Dynamics (CFD) modeling and analysis of the spinning projectile with fixed canard are conducted to determine the lateral-directional aerodynamic coefficients at three supersonic speeds and various angles of attack. The analyses provide a detailed understanding of the effects of canard with different circumferential position on lateral-directional aerodynamic coefficients, and the results show that side force coefficient and yaw moment coefficient vary periodically with the circumferential position angles of canard.

scholarly journals Calculation of aerodynamic characteristics of flying objects using Prodas and Fluent environments

Mechanik ◽  
2017 ◽  
Vol 90 (7) ◽  
pp. 591-593
Author(s):  
Leszek Baranowski ◽  
Michał Frant
Keyword(s):  
Mach Number ◽  
Experimental Method ◽  
Drag Force ◽  
Lift Force ◽  
Incidence Angle ◽  
Theoretical Method ◽  
Aerodynamic Characteristics ◽  
Pitching Moment ◽  
Force Coefficient ◽  
Moment Coefficient

The article presents the methodology of determining the basic aerodynamic characteristics using the Fluent theoretical method and the theoretical and experimental method using the Prodas program. Presented calculations were made for a 122 mm non-guided missile. In order to compare both methods, the results of calculations of coefficient of drag force, lift force coefficient and pitching moment coefficient as a function of incidence angle of attack and Mach number are shown in graphs.

New Methodology for the Calculation of Aerodynamic Coefficients on ATR-42 Scaled Model With Neural Network – EGD Method

2014 ◽  
Author(s):  
A. B. Mosbah ◽  
R. Botez ◽  
T. M. Dao
Keyword(s):  
Control System ◽  
Mach Number ◽  
Experimental Tests ◽  
Aerodynamic Performance ◽  
Aerodynamic Coefficients ◽  
Scaled Model ◽  
Moment Coefficient ◽  
Pressure Distributions ◽  
Flight Parameters

The determination of aerodynamic coefficients such as pressure distributions and aerodynamic coefficients (lift, drag and moment) from the known parameters (angle of attack, Mach number …) in real time is still not achievable easily by methods of numerical analysis in aerodynamics and aeroelasticity domains. For this reason, we propose a flight parameters control system. This approach is based on new optimization methodologies with neural networks (NN) and extended great deluge (EGD). The validation of this new method is realized by experimental tests using a model installed in the wind tunnel to determine the pressure distribution. For lift, drag and moment coefficient, the results of our approach are compared to the XFoil results for different angles of attack and Mach number. The main purpose of this control system is to improve the aircraft aerodynamic performance.

Experimentally Determined Stability Parameters of a Subsonic Cascade Oscillating Near Stall

1978 ◽  
Vol 100 (1) ◽  
pp. 111-120 ◽  
Author(s):  
F. O. Carta ◽  
A. O. St. Hilaire
Keyword(s):  
Phase Angle ◽  
Incidence Angle ◽  
Minor Effect ◽  
Significant Finding ◽  
Force Coefficient ◽  
Stability Parameters ◽  
Free System ◽  
Pressure Transducers ◽  
Moment Coefficient ◽  
The Stability

Tests were performed on a linear cascade of airfoils oscillating in pitch about their midchords at frequencies up to 17 cps, at free-stream velocities up to 200 ft/s, and at interblade phase angles of 0 deg and 45 deg, under conditions of high aerodynamic loading. The measured data included unsteady time histories from chordwise pressure transducers and from chordwise hot films. Unsteady normal force coefficient, moment coefficient, and aerodynamic work per cycle of oscillation were obtained from integrals of the pressure data, and indications of the nature and extent of the separation phenomenon were obtained from an analysis of the hot-film response data. The most significant finding of this investigation is that a change in interblade phase angle from 0 deg to 45 deg radically alters the character of the unsteady blade loading (which governs its motion in a free system) from stable to unstable. Furthermore, the stability or instability is governed primarily by the phase angle of the pressure distribution (relative to the blade motion) over the forward 10–15 percent of the blade chord. Reduced frequency and mean incidence angle changes were found to have a relatively minor effect on stability for the range of parameters tested.

Computational drag and magnus force reduction for a transonic spinning projectile using passive porosity

2001 ◽  
Vol 190 (46-47) ◽  
pp. 6125-6139 ◽  
Author(s):  
Shing-Chung Onn ◽  
Ay Su ◽  
Chieng-Kuo Wei ◽  
Chung-Chuan Sun
Keyword(s):  
Magnus Force ◽  
Spinning Projectile ◽  
Force Reduction

Longitudinal Aerodynamics of a Canard Guided Spin Stabilized Projectile

2012 ◽  
Vol 443-444 ◽  
pp. 719-723
Author(s):  
Xiu Ling Ji ◽  
Hai Peng Wang ◽  
Shi Ming Zeng ◽  
Chen Yang Jia
Keyword(s):  
Normal Force ◽  
Navier Stokes ◽  
Test Case ◽  
Aerodynamic Coefficients ◽  
Number Range ◽  
Detailed Understanding ◽  
Pitch Moment ◽  
Spinning Projectile ◽  
Mach 3 ◽  
Viable Approach

Navier–Stokes simulation is performed on a canard guided spinning projectile for different attack angles and circumferential position angles of canard over the Mach number range of 1.8–2.2. The computational Magnus moment coefficients of test case are validated with available experimental data of a Secant-Ogive-Cylinder-Boattail (SOCBT) configuration at Mach 3, demonstrating that the method can provide an accurate and viable approach for this problem. The aim of the present study is to provide a detailed understanding of the effects of canard with different circumferential position angles on longitudinal aerodynamic coefficients at three supersonic speeds and various angles of attack. And the results show that normal force coefficients and pitch moment coefficients vary periodically with the circumferential position angles of canard.

Packet Switching Start-Stop Bits Generation Based on Bifurcation Behavior of Light in a Micro Ring Resonator

2008 ◽  
Vol 55-57 ◽  
pp. 505-508 ◽  
Author(s):  
N. Pornsuwancharoen ◽  
J. Kumbun ◽  
P. Preecha Yupapin
Keyword(s):  
Refractive Index ◽  
Coupling Coefficient ◽  
Packet Switching ◽  
Ring Resonator ◽  
Nonlinear Behavior ◽  
The Other ◽  
Optical Packet Switching ◽  
Ring Radius ◽  
Simulation Results ◽  
Bifurcation Behavior

his paper proposes the interesting nonlinear behavior of light known as bifurcation, where the use of such behavior in a micro ring resonator to form the secure digital codes for optical packet switching application is demonstrated. A new concept of the stop-start bits in an optical packet switching protocol is formed by using the bifurcation codes. The bifurcation is introduced when light is input into a nonlinear micro ring device, where the refractive index of an InGaAsP/InP is one of device parameters. The other parameters of the device are coupling coefficient (K) and the ring radius (R), where the ring radii used are ranged from 5-10 microns. Simulation results obtained have shown that the packet switching data can be secured by using the generated start-stop bits as the secured codes.

Study on Numerical Simulation Method of Aerodynamic Performance of High-Speed Train on Bridge

2013 ◽  
Vol 376 ◽  
pp. 312-316 ◽  
Author(s):  
Chao Qun Xiang ◽  
Wen Hua Guo ◽  
Jia Wen Zhang
Keyword(s):  
Static Pressure ◽  
Aerodynamic Performance ◽  
Dynamic Mesh ◽  
Positive Pressure ◽  
Aerodynamic Coefficients ◽  
Force Coefficient ◽  
Rolling Moment ◽  
Velocity Magnitude ◽  
Pressure Distributions ◽  
Mesh Method

The dynamic mesh method that could simulate the actual moving of train was used to calculate the aerodynamic coefficients of train on bridge with wind barriers of various heights, and the static pressure distributions around the train body and velocity magnitude distributions were analyzed, the results computed by dynamic mesh method were compared with that computed by traditional static mesh method. The results show that the aerodynamic coefficients of train and flow field characteristics computed by the two methods agree well under the configuration without wind barriers. However, there is considerable difference between the results computed by the two methods with the installation of wind barriers. It is found that the dynamic mesh method is more reasonable to simulate the aerodynamic coefficients of train with wind barriers by analysis of the contour of static pressure distributions and velocity magnitude distributions. The wind barriers effectively decrease the positive pressure on windward train body and negative pressure on train roof, mainly reduce the side force coefficient, lift force coefficient, rolling moment coefficient. Therefore, the aerodynamic performance of train on bridge under crosswind is improved.

Vehicles Aerodynamics while Crossing each other on Road Based on Computational Fluid Dynamics

2010 ◽  
Vol 29-32 ◽  
pp. 1344-1349 ◽  
Author(s):  
Zhe Zhang ◽  
Ying Chao Zhang ◽  
Jie Li
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Numerical Simulations ◽  
Aerodynamic Force ◽  
The Other ◽  
Moving Mesh ◽  
Aerodynamic Coefficients ◽  
Paper Report ◽  
Vehicle Aerodynamics ◽  
Simulation Results

When vehicles run on road, they will be overtaken, cross by other vehicles or be impacted by crosswind. The other events of overtaking and in crosswind were investigated more deeply. A few of paper report the state of the research on this problem. Until now there are no any wind tunnel and road tests to study on road vehicle aerodynamics while crossing each other. Some numerical simulations were carried out by adopting technology of sliding interface and moving mesh. The method of numerical simulations was narrated in detail. The transient process of vehicles crossing each other was realized. Then the trends of aerodynamic coefficients changing were obtained from the flow field of simulation results. The quantificational changing of vehicles aerodynamic coefficients was obtained when they cross each other. The vehicles are sedan and coach. The simulation results indicated that the all aerodynamic coefficients of two vehicles changed large. The aerodynamic force was important to the vehicles’ handling stability when they cross each other.

The Effect of Canard to the Aerodynamic Behavior of Blended Wing Body Aircraft

2012 ◽  
Vol 225 ◽  
pp. 38-42
Author(s):  
Zurriati Mohd Ali ◽  
Wahyu Kuntjoro ◽  
Wisnoe Wirachman
Keyword(s):  
Mach Number ◽  
Wind Tunnel ◽  
Aerodynamic Characteristic ◽  
Lift Coefficient ◽  
Aerodynamic Characteristics ◽  
Moment Coefficient ◽  
Subsonic Wind Tunnel ◽  
Setting Angle ◽  
Blended Wing Body ◽  
The Moment

This paper presents a study on the effect of canard setting angle on the aerodynamic characteristic of a Blended Wing Body (BWB). Canard effects to BWB aerodynamic characteristics are not widely investigated. Hence the focus of the study is to investigate the variations of lifts, drags and moments when the angles of attack are varied at different canard setting angles. Wind tunnel tests were performed on BWB aircraft with canard setting angles,  ranging from -20˚ to 20˚. Angles of attack,  were varied from -10˚ to 10˚. Aspect ratio and canard planform area were kept fixed. All tests were conducted in the subsonic wind tunnel at Universiti Teknologi MARA, at Mach number of 0.1. The streamlines flow, at the upper surface of the canard was visualized using mini tuft. Result shows that the lift coefficient does not change much with different canard setting angles. As expected, the lift coefficient increases with increasing angles of attack at any canard setting angle. In general, the moment coefficient increases as the canard setting angle is increased. The results obtained in this research will be of importance to the understanding of aerodynamic behavior of BWB employing canard in its configuration.

Sign in / Sign up

Export Citation Format

Share Document