Re-entry heating experiment to be flown by scout news release no. 64-202
Reentry heating experiment to be flown by scout launch vehicle to test ablating materials for use in apollo project flight
HEATING↗
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Results for “Reentry”
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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A data storage system for obtaining missile re- entry heating data.
Missile data storage system for obtaining reentry heating data, employing ferrite memory and digital and analog circuitry
DATA STORAGE↗
Research on blunt-faced entry configurations at angles of attack between 60 deg and 90 deg
Stability and control of blunt reentry configurations at angles of attack between 60 and 90 degrees
SPACECRAFT CONFIGURATION↗
Heat-transfer measurements in regions of flow separation and reattachment on two axisymmetric models at mach numbers from 2.65 to 4.50
Heat transfer measurements in regions of flow separation and reattachment on two axisymmetric reentry models at Mach 2.65 to 4.50
HEAT-TRANSFER COEFFICIENT↗
Project fire integrated post flight evaluation report, flight no. 1
Fire project flight test of Atlas launch vehicle, Antares velocity package, and reentry vehicle
ANTARES MISSILE↗
On the use of magnetohydrodynamics during high speed re-entry
Magnetic field interaction with hypersonic flow to effect deceleration and heating during reentry
HYPERSONIC FLOW↗
Nasa schedules project fire launch in may
Launching of Project FIRE spacecraft for reentry heating experiments
REENTRY EFFECT↗
Guidance of a low l/d vehicle entering the earth's atmosphere at speeds up to 50,000 feet per second
Guidance of low lift-drag ratio vehicle during earth atmosphere reentry
LIFT-DRAG RATIO↗
Study of the stability and drag at mach numbers from 4.5 to 13.5 of a conical venus- entry body
Static and dynamic stability, and drag characteristics of conical nosed planetary vehicle during atmospheric reentry at escape velocity speeds
DYNAMIC STABILITY↗
Performance evaluation of 'thermo-lag' material for entry heat protection of advanced manned spacecraft. vol. 1- summary of investigations final report, 1 oct. 1962 - 31 jan. 1964
Thermoconductivity and thermal properties of protective coating and structural material for reentry manned spacecraft
STRUCTURAL MATERIAL↗
Analysis of the project fire re-entry package flow field final technical report
Theoretical prediction of state of gas in flow field surrounding Apollo type vehicle in reentry at hypersonic speeds
GAS FLOW↗
A study of thermo-structural design concepts for lifting entry vehicles, phase ii
Space vehicle structural design for ascent, space flight, and reentry
REENTRY↗
Flow field prediction and analysis, project fire final report
Flow field, and convective and radiative heating predictions for NASA Fire project reentry package trajectories
FLOW FIELD↗
The rotornet- a high-performance hypersonic decelerator for planetary entry
Rotating net decelerator for hypersonic reentry
ROTATING DISK↗
A parametric study of the aerodynamic charac- teristics of nose-cylinder-flare bodies at a mach number of 6.0
Longitudinal aerodynamic characteristics of nose cylinder-flare reentry bodies measured in hypersonic wind tunnel
LONGITUDINAL STABILITY↗
Hemispherical spectral emittance of ablation chars, carbon, and zirconia /to 3700 deg k/
Hemispherical spectral emission of ablation chars, carbon, and zirconium oxide formed during reentry
ZIRCONIUM OXIDE↗
Manned space flight network performance analysis for the gt-2 mission
Gemini launch vehicle, spacecraft systems, and performance data on reentry heating under maximum heating conditions
LAUNCH VEHICLE↗