Heat Transfer and Boundary-layer Transition on Two Blunt Bodies at Mach Number 3.12
Variation of Boundary-layer Transition with Heat Transfer on Two Bodies of Revolution at a Mach Number of 3.12
Heat-transfer Measurements on Two Bodies of Revolution at a Mach Number of 3.12
Boundary-layer Transition at Mach 3.12 as Affected by Cooling and Nose Blunting
The Ablation of Graphite in Dissociated Air
Laminar Incompressible Leading and Trailing Edge Flows and the Near Wake Rear Stagnation Point
The Performance of Ablation Materials as Heat Protection for Re-entering Satellites
Effects of Extreme Surface Cooling on Boundary-layer Transition
Results from Aerodynamic Studies of Blunt Bodies in Hypersonic Flows of Partially Dissociated Air
The Heat Protection Potential of Several Ablation Materials for Satellite and Ballistic Re-entry Into the Earth's Atmosphere
Performance of Several Ablation Materials in Simulated Planetary Atmospheres