Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description
Thermal Fatigue Analysis of a Cryogenically Cooled Rocket Nozzle
Author: THERMAL FATIGUE ANALYSIS OF A CRYOGENICALLY COOLED ROCKET NOZZLE.
Author: Nuclear Science Abstracts
Author: Publisher:
ISBN:
Category : Nuclear energy
Languages : en
Pages : 1108
Book Description
NSA is a comprehensive collection of international nuclear science and technology literature for the period 1948 through 1976, pre-dating the prestigious INIS database, which began in 1970. NSA existed as a printed product (Volumes 1-33) initially, created by DOE's predecessor, the U.S. Atomic Energy Commission (AEC). NSA includes citations to scientific and technical reports from the AEC, the U.S. Energy Research and Development Administration and its contractors, plus other agencies and international organizations, universities, and industrial and research organizations. References to books, conference proceedings, papers, patents, dissertations, engineering drawings, and journal articles from worldwide sources are also included. Abstracts and full text are provided if available.
Analysis, Feasibility, and Wall-temperature Distribution of a Radiation-cooled Nuclear-rocket Nozzle
Author: William H. RobbinsPublisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 36
Book Description
Astm Stp 449 Copy-righted
Author: Fatigue at High Temperature
Author: Publisher: ASTM International
ISBN: 9780803100169
Category : Science
Languages : en
Pages : 166
Book Description
A Design Study of a Regeneratively Cooled Nozzle for a Tungsten Water-moderated Nuclear Rocket System
Author: Richard L. PuthoffPublisher:
ISBN:
Category : Liquid propellants
Languages : en
Pages : 44
Book Description
The Use of Energy Thickness in Prediction of Throat Heat Transfer in Rocket Nozzles
Author: Robert W. GrahamPublisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 36
Book Description
Energy thickness in prediction of throat heat transfer in rocket nozzles using nozzle geometries and temperature ratios.
An Analysis of Nuclear-rocket Nozzle Cooling
Author: William H. RobbinsPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
Book Description
A nuclear-rocket regenerative-cooling analysis was conducted over a range of reactor power of 46 to 1600 megawatts and is summarized herein. Although the propellant (hydrogen) is characterized by a large heat-sink capacity, an analysis of the local heat-flux capability of the coolant at the nozzle throat indicated that, for conventional values of system pressure drop, the cooling capability was inadequate to maintain a selected wall temperature of 1440 R. Several techniques for improving the cooling capability were discussed, for example, high pressure drop, high wall temperature, refractory wall coatings, thin highly conductive walls, and film cooling. In any specific design a combination of methods will probably be utilized to achieve successful cooling.
Digital Codes for Design and Evaluation of Convectively Cooled Rocket Nozzle with Application to Nuclear-type Rocket
Author: John E. RohdePublisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 98
Book Description