Leading-edge bluntness effects on aerodynamic heating and drag of power law body in low-density hypersonic flow

Abstract

A numerical study is reported on power law shaped leading edges situated in a rarefied hypersonic flow. The sensitivity of the heat flux and drag coefficient to shape variations of such leading edges is calculated by using a Direct Simulation Monte Carlo method. Calculations show that the stagnation point heating on power law leading edges with finite radius of curvature follows the same relation for classical blunt body in continuum flow; it scales inversely with the square root of the curvature radius at the nose. Furthermore, for those leading edges with zero or infinity radii of curvature, the heat transfer behavior is in surprising agreement with that for classical blunt body far from the nose of the leading edge

RETRACTED: Thermal protection mechanism of heat pipe in leading edge under hypersonic conditions

“…[3][4][5] In order to reduce aerodynamic resistance, an extremely sharp wing leading edge is required and a radius with a magnitude of millimeters is commonly employed. [6][7][8] In contrast to traditional subsonic and supersonic conditions, since the speed of hypersonic aircraft has been raised significantly, high temperature becomes one of the vital features, as most of the kinetic energy of the high speed airflow, just outside the sharp local structure, transforms into internal energy. 9 This is the result of a strong action of compression, friction and viscous dissipation, and it makes heat flux transmitted into the leading edge becomes intense.…”

Aerothermal Load and Drag Force Analysis of the Electromagnetically Launched Projectiles Under Rarefied Gas Conditions

“…In the last decade, there has been growing research interest for projectiles flying with hypersonic speeds. Heating and drag effects for different leading edges with power law geometries were investigated using the direct simulation Monte Carlo (DSMC) method [1]. Next, the heating of an EML projectile with different surface coatings was analyzed using continuum-based Euler/Navier-Stokes equations [2].…”

Leading Edge Aerothermal Inverse Design of Hyersonic Vehicle Based on Homotopy Optimization Method

“…The blunt leading edge is widely used to alleviate the aerodynamic heating problem since the heat flux for blunt bodies scales inversely with the square root of the nose radius. Traditionally, curves with analytical expression, such as circular arc shapes [2,3], power law shapes [4] are used as the the profile of then leading edge. Recently, the nose tip ablation method to reduce the severe heating around the nose of a hypersonic vehicle is studied [5].…”