Aerodynamic Analysis of Anti-Armor Missile in Different Flight Modes

• Main Authors: Wu,ChungTa, 吳俊達
• Other Authors: Tai, ChangSheng
• Format: Others
• Language: zh-TW
• Published: 2012
• Online Access: http://ndltd.ncl.edu.tw/handle/75695839754962489449

碩士 === 國防大學理工學院 === 機械工程碩士班 === 100 === In this research, Computational Fluid Dynamics(CFD) was employed to study the aerodynamic characteristic of lift, drag and stall angle of attack of Javelin missile in different fly modes with Mach number M=0.3~0.5, angle of attack α=0°~5°, the deflection angle of vertical fin δv =0°~10°, and the deflection angle of horizational fin δh=-10°~10°. For the drag, when flight at zero angle of attack with M and δv constants and δh varies from -10° to 10° with the change in 5° interval, the drags coefficient shows the phenomenon of symmetry with the center line, however the symmetry disappear when the fly with angle of attacks, and the higher the value of α, δv, and negative δh, the greater the drag coefficient. For the lift, only about 0.5% of the total lift is affected by the changes of δv. A higher lift is obtained with δh<0° at all angle of attack, and a negative value is observed when δh>0° with zero angle of attack. Lift coefficient increases with the increase in α, and it appears as a linear function of α and δh. ie. CL=Φ(α,δh). For the stall angle, since (dFL/dα) decreases with the increase in α, and become to zero when α is increased to 40° —a maximum value of lift is achieved— and (dFL/dα) found to be negative results in the lift to decrease when α >40°. Therefore, the critical α is 40° and the stall angle of attack is 40° for the Javelin missile in free flight. Solving the relevant aerodynamic data, MATLAB-Simulink program was employed to solve the six degrees of freedom of the missile trajectory.