Apollo afterbody heat transfer and pressure with and without ablation at M infinity of 5.8 to 8.3
Apollo afterbody heat transfer and pressure with and without ablation at Mach numbers 5.8 - 8.3
AFTERBODY↗
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Results for “ABLATION”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Determination of temperature and material effects on high-velocity impact craters in ablative heat-shield materials
Temperature and material effects on high-velocity impact craters in phenolic-nylon and elastomeric ablative heat-shield materials
ABLATING MATERIAL↗
Ablative and insulating properties of outgassed boron nitride and boron nitride composite
Ablative and insulating properties of outgassed boron nitride and boron nitride-phenolic resin composite
ABLATION↗
An experimental evaluation of 100-lb-thrust ablatively cooled rocket engines
Test firing of 100-lb thrust ablatively cooled rocket chambers
ROCKET CHAMBER↗
Development of sensors to obtain in-flight ablation measurements of thermal-protection materials
Design and development of sensors for measuring ablative changes in space vehicle heat shield during reentry phase
ABLATION↗
Thermochemical ablation.
Thermochemical interaction between ablation material and environment during manned reentry, using mainly graphite and composite materials
REENTRY EFFECT↗
Melting ablation about decelerating spherical bodies.
Heat transfer and melting ablation about decelerating spherical bodies during planetary atmosphere entry
REENTRY PHYSICS↗
Evidence of surface waves and spreading of turbulence on ablating models.
Surface modifications of recovered small-scale plastic models after high speed flight used to estimate extent of laminar and turbulent flow over surface related to ablation studies
ABLATING NOSE CONE↗
Experimental investigation of a charring ablative material exposed to combined convective and radiative heating.
Charring ablative materials effectiveness in combined convective and radiative heating as reentry shield
MATERIAL TESTING↗
Development of ablation sensors for advanced reentry vehicles.
Make wire, light pipe and spring wire ablation sensors development for measuring parameters of heat shield materials for reentry vehicles
MEASURING APPARATUS↗
Boundary-layer transition on ablating cones at speeds up to 7 km/sec.
Laminar and turbulent boundary layer flow in ablating cones in hypervelocity flight
HIGH SPEED FLYING↗
Free-flight aerodynamics of a blunt-faced reentry shape with and without ablation.
Hypersonic aerodynamic stability and drag of ablating and nonablating models of blunt-faced reentry shape
BLUNT BODY↗
Analysis of the effects of environmental conditions on the performance of charring ablators.
Effectiveness of charring ablators strongly influenced by stream enthalpy level and heating rate
REENTRY SHIELD↗
Ablation of reinforced plastic for heat protection.
Approximate solution of ablation of reinforced plastic for heat protection
ABLATION↗
Laminar convective heating and ablation in the Mars atmosphere.
Mars atmospheric composition and laminar convective heating and ablation studied to predict performance of heat protection systems during entry
MARS ATMOSPHERE↗
Boundary-layer transition on ablating cones at speeds up to 7 km/sec.
Laminar and turbulent boundary layer flow in ablating cones in hypervelocity flight
TURBULENT BOUNDARY LAYER↗
Calculation of approximate thermophysical properties for ablating specimens exposed to high radiant heat fluxes.
Calculating specific heat and conductivity of ablating specimens exposed to radiant heat fluxes
SPECIFIC HEAT↗
A study of artificial meteors as ablators.
Simulated meteor ablation tests using artificial meteors of gabbro, basalt and steel in ultrahigh enthalpy plasma jet
METEOR↗