Abstract :
Aerospike installation on the forebody of a hypersonic rocket is one of the most challenging tasks. Small change in the structure may cause a great loss. This paper aims to design and develop an optimized structure of the aerospikes by varying the aerospike's frontal shape in order to reduce the drag acting on the forebody of a blunt nosed high-speed vehicle. The designs were done by using CATIA and the effect of air flowing over the blunt body are simulated numerically with the help of ANSYS Fluent. The simulations were carried out for different aerospike models by varying the aerodynamic structure of the aerospike. The coefficient of drag and its coefficients are estimated at zero-degree angle of attack and at a constant velocity of 1400 m/s by keeping pressure of 425 Pascal. Pressure contours and temperature contours are analyzed to find the pressure distribution and temperature distribution respectively. In addition, density and velocity contours are also studied. It is concluded from the results that the forebody with flat shape and cornered(fillet) edge aerospike model experienced less drag when compared with sharp edged and straight edged aerospike models.
Keyword :
aerospikes; CFD; cornered edge; fillet edge; sharp edge; drag; CATIA; ANSYS.