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Hot Structures Thermal Correlation.

AD477775

Publication Date	1965
Personal Author	Clawson, J. F.
Page Count	244
Abstract	Test data generated during the early X-20 (Dyna-Soar) phases are compared with therma2l analysis methods evolved throught the X-20 Program. Data are taken from the Hot Structures concept model test program. This model was similar in shape and concept to the X-20 design. The thermal analysis approach and methods used follow closely those which created the X-20 design temperatures. Generally good correlation is shown for two-dimensional cross-sectional cuts, a simple three-dimensional nose region analysis, simple structural joint analyses, and certain other detail areas. Some additional light is shed on joint interface effects. The only major problem evolved was convection currents in and around the test specimen. This program in combination with an earlier insulated panel correlation program provides general confidence in the X-20 thermal analysis approach and methods. (Author)
Keywords	Thermal analysis Boost glide vehicles Models(Simulations) Research planes Manned spacecraft Computer programming Convection(Heat transfer) Instrumentation Thermocouples Airplane panels Cobalt alloys Nickel alloys Surfaces Heat transfer Simulation Temperature Mathematical prediction Thermal radiation Thermal conductivity Liquid cooled Refractory metals Thermodynamic cycles High temperature Blackbody radiation Structures X-20 spacecraft
Source Agency	Non Paid Delimited ADS
NTIS Subject Category	46 - Physics 84C - Manned Spacecraft
Corporate Authors	Boeing CO Seattle Wash
Document Type	Technical Report
Title Note	Final rept. Oct 64-May 65.
NTIS Issue Number	197715
Contract Number	AF33(657)-7132

Hot Structures Thermal Correlation.

Hot Structures Thermal Correlation.
AD477775

Publication Date	1965
Personal Author	Clawson, J. F.
Page Count	244
Abstract	Test data generated during the early X-20 (Dyna-Soar) phases are compared with therma2l analysis methods evolved throught the X-20 Program. Data are taken from the Hot Structures concept model test program. This model was similar in shape and concept to the X-20 design. The thermal analysis approach and methods used follow closely those which created the X-20 design temperatures. Generally good correlation is shown for two-dimensional cross-sectional cuts, a simple three-dimensional nose region analysis, simple structural joint analyses, and certain other detail areas. Some additional light is shed on joint interface effects. The only major problem evolved was convection currents in and around the test specimen. This program in combination with an earlier insulated panel correlation program provides general confidence in the X-20 thermal analysis approach and methods. (Author)
Keywords	Thermal analysis Boost glide vehicles Models(Simulations) Research planes Manned spacecraft Computer programming Convection(Heat transfer) Instrumentation Thermocouples Airplane panels Cobalt alloys Nickel alloys Surfaces Heat transfer Simulation Temperature Mathematical prediction Thermal radiation Thermal conductivity Liquid cooled Refractory metals Thermodynamic cycles High temperature Blackbody radiation Structures X-20 spacecraft
Source Agency	Non Paid Delimited ADS
NTIS Subject Category	46 - Physics 84C - Manned Spacecraft
Corporate Authors	Boeing CO Seattle Wash
Document Type	Technical Report
Title Note	Final rept. Oct 64-May 65.
NTIS Issue Number	197715
Contract Number	AF33(657)-7132