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Design and Analysis of Hypersonic Aircraft with Transonic and Supersonic Fluid Flow analysis


Pichika S V V S Narayana , Godavari Institute of Engineering and Technology; Dr. T Jayananda Kumar, Godavari Institute of Engineering and Technology


Coefficient of Drag, Coefficient of Lift, CFD, FVM, Hypersonic Aircraft


This paper aims to design new geometry for hypersonic aircraft along with a study of transonic and supersonic fluid flows over Northrop B-2, Lockheed F-22 respectively. The hypersonic aircraft uses the Waverider concept in its design. Specific parameters (like drag coefficient, lift coefficient, pressure, and velocity variation) that effect aerodynamic efficiency are studied. Finite volume methods (FVM) of computational fluid dynamics (CFD) with the help of cartesian based meshes are used in determining these parameters. The structured cartesian immersed – body mesh with rectangular cells (cuboids) are used. The geometry of aircraft is created using Solidworks and CFD analysis is carried out using Solidworks Flow Simulation. The stated parameters for different aircraft are compared.

Other Details

Paper ID: IJSRDV5I30076
Published in: Volume : 5, Issue : 3
Publication Date: 01/06/2017
Page(s): 112-116

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