Numerical Simulation of Surface Pressure and Temperature Distribution along a Cone at Supersonic Mach Numbers using CFD
DOI:
https://doi.org/10.37934/arnht.28.1.126Keywords:
Mach number, Supersonic flow, semi-cone angle, CFDAbstract
The primary focus of this study is to use numerical simulations to analyze the static temperature and surface pressure distribution along the slant length of a cone at different Mach numbers and a range of semi-cone angles. Computational fluid dynamics (CFD) analysis numerically simulates temperature and surface pressure distribution. This research considers parameters such as supersonic Mach numbers, semi-cone angles, and different locations along the slant length of a cone. The study examines Mach numbers of 1.5, 2.0, 2.5, 3.0, 3.5, 4.0, 4.5, and 5.0, along with cone angles ranging from 3° to 21°. The static temperature and pressure (P/Pa) results are measured at different locations (x/L) along the slant length of the cone, ranging from 0.1 to 1. The results for static temperature and pressure distribution obtained by CFD analysis are compared with results obtained by regression model at various Mach numbers and constant semi-cone angle (θ) = 12°. The results from the CFD analysis and the findings of the regression methodology are in agreement. This study found that the Mach number, semi-cone angle, and the various locations along the cone's slant length significantly impact the variation of static temperature and surface pressure distribution. As the Mach number and the semi-cone angle increase, the temperature and pressure distribution along the slant length of the cone also increase.
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