Pressure coefficient, drag Coefficient and other important plots are considered for the study. Analysis was carried out in Fluent Software, Standard Flow conditions was used with change in Mach number and wedge AOA. Modelling of Double wedge airfoil was carried out using CAD Software. These angles are used for further calculation of flow properties after oblique shock and expansion wave are found. Using coding software MAT lab shock angles for corresponding Mach number and Wedge angle is found. Also another model with 10 degree half wedge angle was analysed at 0 degree AOA. Published under licence by Ltd 1ģ done at 0, 5, 10, 15degree angle of attack (AOA) for a 5deg half wedge angle. Any further distribution of this work must maintain attribution to the author(s) and the title of the work, journal citation and DOI. This was Content from this work may be used under the terms of the Creative Commons Attribution 3.0 licence. Oblique shock and expansion waves for Double wedge airfoil were manually calculated for different wedge angles and the same was carried using ANSYS Fluent software. Manual and Fluent analyses over Double wedge airfoil was done to minimize this drag. Supersonic characteristics for a Double wedge airfoil are associated with shocks and expansion waves. Detailed analysis of change in flow properties over airfoils is done with the aid of CAD Modelling and Fluent for analysis. Since any disturbance (either physical or shock related) takes up great deal of importance in supersonic flow, it becomes a necessity to analyse flow over different contours to get higher and efficient performance. Supersonic flow over different contours is a leading study in today s aeronautical field. DWA have different types of shocks at higher speeds which make studies interesting to analyse the flow parameters along the body. Introduction Double wedge airfoils (DWA) are very rarely used in physical applications because of its complex geometrical parameter variations. Results obtained from manual calculations and fluent analysis are cross checked. MATLAB is used to form a code for obtaining shock angle with Mach number and wedge angle at the given parameters. Manual calculations for oblique shock properties are calculated with the help of Microsoft excel. Analysis is carried out using fluent at standard conditions with specific heat ratio taken as 1.4. Double wedge airfoil is analysed at different Angles of attack (AOA) based on the wedge angle. Available Computational tools are utilized for analysis. Physical parameters considered for the Double wedge case with wedge angle (ranging from 5 degree to 15 degree. Mach number range taken is for transonic and supersonic. The present work is based on the effects of change in physical parameter for the Double wedge airfoil. Airfoil shapes differ based on the applications, hence the airfoil shapes considered for supersonic speeds are different from the ones considered for Subsonic. Aerodynamic analysis is part of the whole procedure, which includes focusing on airfoil shapes which will permit sustained flight of aircraft at these speeds. Aeronautical studies are being focused more towards supersonic flights and methods to attain a better and safer flight with highest possible performance. Assistant Professor, Institute of Aeronautical Engineering, Hyderabad, India UG scholar of Aeronautical Engineering, MIT, Manipal, Manipal University, India. Numerical simulations of the NREL S826 airfoil KF Sagmo, J Bartl and L Sætran This content was downloaded from IP address on at 21:16Ģ Aerodynamic Analysis Over Double Wedge Airfoil U S Prasad 1, Ajay V S 2, Rajat R H 3, Samanyu S 4 1 Sr. Related content - Theoretical Fluid Mechanics: Incompressible aerodynamics R Fitzpatrick - Application of CAD/CAE class systems to aerodynamic analysis of electric race cars L Grabowski, A Baier, A Buchacz et al. Eng View the article online for updates and enhancements. 1 IOP Conference Series: Materials Science and Engineering PAPER OPEN ACCESS Aerodynamic Analysis Over Double Wedge Airfoil To cite this article: U S Prasad et al 2017 IOP Conf.
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