Hypersonic flow past nose cones of different geometries: a comparative study

Abstract

The present work provides a detailed comparative study of the hypersonic flow past spherically blunted and parabolic nose cones at a Mach number of 5.8, numerically. The main focus of the paper is to determine the geometry and parameters of the nose cones that provide minimum aerodynamic drag and heating. Studies on spherically blunted and parabolic nose cones are performed for different fineness ratios at zero angle of attack. It is observed that for fineness ratio \1.2, blunted cones provide minimum drag, whereas at higher values of fineness ratios .1.2, parabolic nose cones provide superior drag reduction. Detailed comparison of the flow/shock features in the vicinity of the blunted and parabolic nose cones for different fineness ratios is also shown in order to determine its influence on aerodynamic drag. An empirical correlation developed for the total drag coefficient based on regression analysis for a parabolic nose cone reveals that it is mainly a function of the maximum pressure coefficient and fineness ratio. In general, the present study reveals that parabolic nose cones at higher fineness ratios are preferred over spherically blunted ones for achieving higher drag reductions and lower heating in hypervelocity vehicles.

Aerodynamic Optimization of the Von Karman Nose Cone for a Supersonic Sounding Rocket

“…Given that the rocket velocity will range up to Mach 3, the Von Karman geometry is selected as the candidate for optimization. [1][4][5] [6] 3 Design…”

Numerical Analysis of Semi-Tangential Ogive Bullet

“…But the research does not discuss the flow parameters of the bullet shapes. In the research works of Narayan [2].flow past over various nose geometry gives us a detailed view of flow over different nose geometry & gives a clear vision of the shock generated by the nose shapes. in the research thesis of Wilcox [3] Formulation of the k-w Turbulence Model, explains about the k-omega turbulence model uses an approximation for the Reynolds-averaged Navier-Stokes equations in computational fluid dynamics (RANS equations).…”

“…The flow past different geometry forms of the nose has been completed, according to the study of Narayan [2]. The Mach number contours of a spherically blunted nose and a parabolic nose have been obtained as a result of the testing.…”

Influence of Spike-Nosed Length on Aerodynamic Drag of a Wing-Projectile Model

“…Previously, the effects of spike on flow structure around the nose and drag reduction were studied widely by both experimental and numerical approaches [2][3][4][5][6][7][8][9]. Stalder and Nielsen [1], who conducted measurements with spikes at high Mach number, indicated that aerodynamic drag of the model decreases with increasing length up to two times of diameter.…”