ANALYSIS OF HYPERSONIC FLOW OVER BLUNTED NOSE GEOMETRY FOR A DIFFERENT FINENESS RATIO AT DIFFERENT ANGLE OF ATTACK

This study analyses hypersonic flow over spherically blunted nose cones using CFD in ANSYS FLUENT. The focus is on fineness ratios (1.0, 3.6, and 4.7) with a constant nose radius of 2. Simulations assess static pressure, temperature, and velocity distributions at angles of 0°, 15°, and 30°. Results highlight geometric influences on flow behaviour and drag coefficients. Comparative graphs show aerodynamic impacts across configurations, emphasizing the need for drag minimization. The findings guide optimized nose cone designs for high-speed vehicles, balancing aerodynamic efficiency and thermal management under hypersonic conditions. These insights contribute to future hypersonic vehicle advancements, aiding in achieving stability and efficiency under extreme conditions.