Outcome of Varied Mach Number and AOA on Convex Blunt Nose with Spike Angle Zero Degree

Mahesh, Srikanth, Channaveerayya; Srikanth; Channaveerayya

Outcome of Varied Mach Number and AOA on Convex Blunt Nose with Spike Angle Zero Degree

Authors: Mahesh, Srikanth, Channaveerayya, Srikanth, Channaveerayya

Unique Paper ID: 175022
Volume: 6
Issue: 12
PageNo: 953-960

Keywords: Convex Blunt Nose Spike angle CFD Lift force Mach number drag force.

Abstract:
Wave drag is an important parameter to be considered in designing high speed vehicles. It is well known that drag can be alleviated by modifying the flow field in front of the body. There are several techniques to the flow field ahead of a supersonic/hypersonic body and the use of retractable nose spike appears to be simplest and at an efficient means of reducing drag on the vehicle by bringing about flow separation and altering the shock structure around the body. The present work involves study of high-speed flow around the blunt nose of an aero vehicle. Three different types of spikes have been considered for the purpose of drag reduction studies. These computational studies suggest that suitable aero to reduce the drag and lift forces. The numerical results have been validated with literature data. Modify the blunt nose and spikes to increase aerodynamics, lower drag, or accomplish other design goals in light of the simulation results. The information presented states that thermal protection can be achieved by blunting the front surface of an aircraft. The nose still undergoes high levels of heat activity despite this blunting, thus it needs a lot more thermal protection than the remainder of the car. A modification to the flow field in front of the vehicle is necessary to alleviate the problem of wave drag, which is often brought on by the blunt nose shape. Using a retractable nose spike is one method to implement this modification. The flow field may be changed by deploying a retractable spike, which may lessen wave drag and enhance aerodynamic efficiency.

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ISSN: 2349-6002
Volume: 6
Issue: 12
PageNo: 953-960

Outcome of Varied Mach Number and AOA on Convex Blunt Nose with Spike Angle Zero Degree

Available:https://ijirt.org/Article?manuscript=175022

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