Pneumatic Shape Design And Pneumatic Analysis Of Wing Body Fusion Aircraft

Wing body fusion aircraft is also known as flying wing layout aircraft.It is a new layout of the aircraft,because the wing body fusion in the horizontal ring distribution of the bending moment is smaller than the conventional layout of the aircraft,it can make the structure weight of the aircraft smaller.Fusion aircraft have lighter structural quality,higher lift resistance and higher fuel efficiency than conventional aircraft with the same level.Therefore,Europe,the United States,Russia and other Aviation powers put a lot of resources and energy on the wing fusion aircraft to study.For the military wing fusion aircraft,excellent stealth performance and the Low resistance is also a Another popular reason for the wing fusion aircraft.However,the wing body fusion aircraft to remove the traditional sense of the tail,so the wing body fusion aircraft research is stagnation for a long period of time by it,s Poor handling stability,This article based on the past wing body fusion aircraft design experience Combined with the relevant experimental conditions of the school designed a wing body fusion aircraft,and Study on Initial Model of the wing fusion aircraft with Different wind speed and angle of attack.Using CATIA to Generate the Initial Model of wing fusion aircraft.Taking into account the specific size of the aircraft,the choice of airfoil and for weight,The cruise speed of the aircraft is designed to be 30m/s.Through the wind tunnel experiment And FLUENT computational fluid dynamics software calculations,we can get he Initial Model of wing fusion aircraft,s Speed cloud and pressure cloud and the Distribution of the surrounding flow field,according to FLUENT computational fluid dynamics software and the Distribution of the surrounding flow field,Four improved models based on the initial model were identified:Eddy swirl model,wingtip winglet model,canyon model,flat tail model.Research The aerodynamic performance of the four improved wing-body fusion aircraft models at different angles of attack and wind speed(Including lift coefficient resistance coefficient lift resistance ratio)The idea of the impact is To establish an accurate improved swirl model,to improve the wing winglet model,to improve the duck wing model,to improve the flat tail model.Using wind tunnel experiment and CFD to calculate fluid dynamics software Calculate the aerodynamic characteristics of the airplane at different wind of angles at-4°to 14 °,Analysis The aerodynamic characteristics of the aircraft at different speeds and angles of attack,And provide the theoretical basis for the safe and efficient flight of the aircraft.And compare the aerodynamic characteristics of the improved four models with theinitial model at different speeds and angles of attack.And then according different improved wing body fusion model in different flight condition,s aerodynamic characteristics to Explore the use and development value,Which will provide some theoretical basis for the aerodynamic design and improvement of the Boeing 797 super-large wing fusion body and our similar "sword" wing body fusion UAV.