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Kühlsystem
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Ground-stand Cooling Investigation of an R-2600-22 Engine in a PBM-3D Nacelle
Effect of Exhaust Pressure on the Cooling Characteristics of an Air-cooled Engine
High-altitude Flight Cooling Investigation of a Radial Air-cooled Engine
An analysis of supersonic aerodynamic heating with continuous fluid injection
Altitude Performance Characteristics of Tail-pipe Burner with Variable-area Exhaust Nozzle
Experimental investigation of a lightweight rocket chamber
Experimental investigation of two-stage air-cooled turbine suitable for flight at Mach 2.5
STUDY OF CHAMBER COOLING TECHNIQUES FOR SPACECRAFT ENGINES. MONTHLY LETTER
Progress Report on the Development of Protected Construction for Hypersonic Vehicles
SELECTING A THRUST CHAMBER COOLING TECHNIQUE FOR SPACECRAFT ROCKET ENGINES
AN EXPERIMENTAL INVESTIGATION OF GASEOUS-FILM COOLING OF A ROCKET MOTOR
Free-flight investigations of subliming ablators and transpiration cooling at hypersonic velocities
SELECTING A THRUST CHAMBER COOLING TECHNIQUE FOR SPACECRAFT ROCKET ENGINES
FREE-FLIGHT INVESTIGATIONS OF SUBLIMING ABLATORS AND TRANSPIRATION COOLING AT HYPERSONIC VELOCITIES
Design and testing of an aerospace dew point hygrometer Final report
Spacecraft engine thrust chamber cooling final report, 13 may 1963 - 12 apr. 1964
Investigation of cooling problems at high chamber pressures final report, 1 jul. 1963 - 31 mar. 1965
A large ultrahigh-vacuum environmental chamber with liquid-helium-cooled liner.
A radiation-cooled nuclear rocket nozzle for long firing durations.
Spacecraft temperature control by thermostatic fins Progress report, 1 Jun. - 30 Nov. 1965
Program for sea level test firing of rocket engines final report, 1 sep. 1964 - 1 feb. 1965
Apollo portable life-support system - development status.
Devices for controlling thermal gradients in spacecraft structures
Extraterrestrial cryogenic propellants reliquefaction.
Transpiration and Film Cooling of Liquid Rocket Nozzles
[Research on a Self-Temperature Regulating Spacecraft Skin System]
Summary of observed results when chilling the M-1 fuel turbopump to liquid hydrogen temperature
Localized overheating in Aerobee regeneratively cooled thrust chambers
Gaseous-film cooling of a rocket motor with injection near the throat
A probe for total-enthalpy measurements in arcjet exhausts.