Author: Richard J. QuentmeyerPublisher:
ISBN:
Category : Combustion
Languages : en
Pages : 22
Book Description
Hot-gas-side Heat Transfer Characteristics of Subscale, Plug-nozzle Rocket Calorimeter Chamber
Author: Richard J. QuentmeyerPublisher:
ISBN:
Category : Combustion
Languages : en
Pages : 22
Book Description
Experimental Investigation of Heat-transfer Characteristics of a Film-cooled Plug Nozzle with Translating Shroud
Author: Francis C. ChenowethPublisher:
ISBN:
Category : Ejector pumps
Languages : en
Pages : 92
Book Description
Heat transfer characteristics of film cooled plug nozzle with translating shroud.
Scientific and Technical Aerospace Reports
Author: Comparison of Predicted and Experimental Heat-transfer and Pressure-drop Results for an Air-cooled Plug Nozzle and Supporting Struts
Author: Edwin J. GraberPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 44
Book Description
Application of Various Techniques for Determining Local Heat-transfer Coefficients in a Rocket Engine from Transient Experimental Data
Author: Curt H. LiebertGovernment Reports Annual Index
Author: Publisher:
ISBN:
Category : Government reports announcements & index
Languages : en
Pages : 1368
Book Description
A Thermal Management Systems Model for the NASA GTX RBCC Concept
Author: Analysis of Heat-transfer Effects in Rocket Nozzles Operating with Very High-temperature Hydrogen
Author: John R. HowellPublisher:
ISBN:
Category : Energy transfer
Languages : en
Pages : 44
Book Description
An analytical technique suitable for & the solution of complex energy transfer problems involving coupled radiant and convective energy transfer is developed. Solutions for the coupled axial wall energy flax distribution in rocket nozzles using hydrogen as a propellant are presented. Flow rates and temperatures studied are near those forecast for gaseous-core nuclear-propulsion systems. Parameters varied are nozzle shape, inlet propellant temperature, mean reactor cavity temperature, and nozzle wall temperature level. The effects of variation of the propellant radiation absorption coefficient with pressure, temperature, and wavelength are presented, and real property variations are used where they appear to be significant. Comparison is made to a simplified, coupled solution using a modified second-order one-dimensional diffusion equation for the radiative transfer. At the temperature levels assumed, radiative transfer may account for a greater portion of the total energy transfer over important portions of the nozzle, and its effects cannot, therefore, be neglected. Extreme energy flaxes (near 3XlO to the 8 Btu/(hr)(sq ft)) are observed for certain cases, and this implies that new nozzle cooling techniques must be developed.
Author: 
Author: Francis C. Chenoweth