Hypersonic convective heat transfer over 140deg blunt cones in different gases
Abstract
Largeangle blunt cones, with various corner radii, were tested in dissociated air, CO2, and CO2Ar gas mixtures. These experiments were conducted at angles of attack from 0 to 20 deg. The heating distribution data and how shockwaved geometry were obtained during the cone's exposure to the three gases. The data can be used to partially validate twodimensional (2D) axisymmetric and threedimensional NavierStokes solutions of the heating distribution over a 140deg blunt cone in a simulated Martian atmosphere. The predicted heating distribution over the cones and estimated bow shock standoff distances using a 2D axisymmetric NavierStokes code were compared with test data taken at zero angle of attack.
 Publication:

Journal of Spacecraft and Rockets
 Pub Date:
 September 1994
 DOI:
 10.2514/3.26506
 Bibcode:
 1994JSpRo..31..735S
 Keywords:

 Aerodynamic Heating;
 Aerothermodynamics;
 Argon;
 Atmospheric Models;
 Carbon Dioxide;
 Computerized Simulation;
 Convective Heat Transfer;
 Environment Simulation;
 Gas Mixtures;
 Hypersonic Heat Transfer;
 Mathematical Models;
 NavierStokes Equation;
 Computational Fluid Dynamics;
 Exposure;
 Mars Atmosphere;
 Shock Waves;
 Temperature Distribution;
 Thermal Protection;
 Three Dimensional Models;
 Two Dimensional Models;
 Zero Angle Of Attack;
 Fluid Mechanics and Heat Transfer