Soham SINHA, Mohammed Ibrahim SUGARNO
DOI Number: XXX-YYY-ZZZ
Conference number: HiSST2024-00227
The conical nose shape has long been a focal point of high-speed aerodynamic research. It serves as the foundation from which a multitude of general forebody designs, including waveriders, draw their inspiration. This study aims in investing the change in flow physics over a sharp cone as the angle of attack (AoA) is changed. This entails the presence of an attached conical shockwave in conjunction with the development of an attached boundary layer on the surface. Also due to this alteration, the heat transfer rate to the conical surface from the windward side to the leeward side will also get affected. The model used here is a 200mm slender cone with 8° semi-apex angle having a sharp leading edge. The notable flow features are change in shock angle, heat flux to the conical surface and the recirculation zone at the base of the cone with variation of AoA. Flow over the cone will be Laminar throughout its length. So, it will give an idea about the heat flux if the entire flow over the conical body can be maintained laminar. In this extended abstract, glimpse of work done on 8° angle of attack is presented showing the variation of heat flux in the axial and circumferential axis. Analysis of the boundary heat flux contour leads to the following observations: 1. The highest heat flux is concentrated near the tip of the cone, gradually diminishing in intensity as we move along the axial direction. 2. In the circumferential aspect, the maximum heat flux is situated at the base of the cone, gradually diminishing as we progress towards the upper surface. Work is still in progress and numerical results will be presented.