The Overall Design And Aerodynamic Analysis Of A Blended Wing Body UAV

The technology of unmanned aerial vehicle(UAV)is developing vigorously all around the world.Different performance,advanced technology and a wide range of unmanned aerial vehicle constantly emerge.Blended Wing Body UAV layout let the traditional fuselage and the wing structure together.Compared with the traditional barrel-shaped fuselage and wing-mounted aircraft,it has the advantages of light weight,high aerodynamic efficiency,low radar reflector,economical and high utilization rate of aircraft interior space,etc.Blended Wing Body UAV get more and more attention of the countries,both in the field of military and civilian fields.This paper design a Blended Wing Body UAV and demonstrates its overall layout.The aerodynamic analysis of the Blended Wing Body UAV model was carried out through the wind tunnel experiment.The specific contents of the study include the following:1.This paper designed a Blended Wing Body UAV.The S3010 airfoil which has obvious advantages was selected by Profili software.The geometry of the wing and the geometrical shape of the Blended Wing Body UAV were determined,and the overall design of the Blended Wing Body UAV was completed.This paper also produced the model of this Blended Wing Body UAV,by the use of aircraft model materials.2.The theory of aerodynamic analysis and the wind tunnel experiment system for aerodynamic analysis of the Blended Wing Body UAV were studied.Firstly,the working principle of the wind tunnel and the similarity criterion of the wind tunnel were studied.The influence of the twelve similar quasi-sides on the wind tunnel test was described.The main similarity criteria under different conditions were discussed.Then,The experimental system of low speed wind tunnel was studied.The composition of low speed wind tunnel,the main similarity parameters and the airflow quality of the test section were described.The composition and function of the control cabinet,the hole structure,the angle control system,the measurement control system and the data acquisition system were studied.3.Through the wind tunnel experiment,the aerodynamic analysis of this Blended Wing Body UAV model was carried out.This Blended Wing Body UAV model was simulated by wind tunnel,and a series of aerodynamic parameter values under different angle of attack,yaw angle and wind speed were obtained,including the liftcoefficient,the resistance coefficient,the pole curve,the lift resistance ratio and the pitch moment coefficient under different angle of attack and wind speed.And a series of aerodynamic parameter values under different yaw angle and wind speed were also obtained,including the lift coefficient,the resistance coefficient,the side force coefficient,and the yaw moment coefficient.The parameters of the aerodynamic parameters are plotted as graphs.The test results are analyzed.Then through three layers of flat tail,a layer of flat tail and eddy current detector way for local change Blended Wing Body UAV.The same aerodynamic analysis of local changed Blended Wing Body UAV was also carried out.