Aerodynamic Analysis Over Double Wedge Airfoil

Frontiers in Automobile and Mechanical Engineering

Prasad, U.S.^1 ; Ajay, V.S.^2 ; Rajat, R.H.^2 ; Samanyu, S.^2

Institute of Aeronautical Engineering, Hyderabad, India^1

Aeronautical Engineering, MIT, Manipal University, Manipal, India^2

关键词: Aerodynamic analysis;    Angles of attack;    Computational tools;    Physical parameters;    Specific heat ratio;    Standard conditions;    Supersonic flights;    Supersonic speed;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/197/1/012076/pdf
DOI  :  10.1088/1757-899X/197/1/012076

来源: IOP

【 摘 要 】

Aeronautical studies are being focused more towards supersonic flights and methods to attain a better and safer flight with highest possible performance. Aerodynamic analysis is part of the whole procedure, which includes focusing on airfoil shapes which will permit sustained flight of aircraft at these speeds. Airfoil shapes differ based on the applications, hence the airfoil shapes considered for supersonic speeds are different from the ones considered for Subsonic. The present work is based on the effects of change in physical parameter for the Double wedge airfoil. Mach number range taken is for transonic and supersonic. Physical parameters considered for the Double wedge case with wedge angle (ranging from 5 degree to 15 degree. Available Computational tools are utilized for analysis. Double wedge airfoil is analysed at different Angles of attack (AOA) based on the wedge angle. Analysis is carried out using fluent at standard conditions with specific heat ratio taken as 1.4. Manual calculations for oblique shock properties are calculated with the help of Microsoft excel. MATLAB is used to form a code for obtaining shock angle with Mach number and wedge angle at the given parameters. Results obtained from manual calculations and fluent analysis are cross checked.