Hot Structures Thermal Correlation
Report Number: AFFDL TR 65-142
Author(s): Clawson, James F.
Corporate Author(s): The Boeing Company
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1965-11
Pages: 254
Contract: AF 33(657)-7132
DoD Project: 1467
DoD Task:
Identifier: AD0477775
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.
Provenance: Lockheed Martin Missiles & Fire Control
Author(s): Clawson, James F.
Corporate Author(s): The Boeing Company
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1965-11
Pages: 254
Contract: AF 33(657)-7132
DoD Project: 1467
DoD Task:
Identifier: AD0477775
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.
Provenance: Lockheed Martin Missiles & Fire Control