Accession Number : AD0477773


Title :   THERMAL CORRELATION OF HEAT PROTECTION SYSTEM.


Descriptive Note : Final rept.,


Corporate Author : BOEING CO SEATTLE WASH


Personal Author(s) : Clawson,James F


Report Date : Dec 1965


Pagination or Media Count : 253


Abstract : Prediction of design temperatures and other thermal information for any radiation-cooled hot structure re-entry vehicle is highly complex. Large computer programs, along with other common and uncommon analytic heat transfer methods are usually required, but little or no verification data exist. The basic intent of this program was to analyze, test, and correlate a panel system using X-20 generated technology for panel design, fabrication, and thermal analysis methods. In insulated panel systems similar to that tested, such thermal methods as usage of the Boeing Thermal Analyzer Program, various thermal radiation view factor determination methods, neglect of certain material interface effects, use of large area nodes, neglect of trusswork in a general panel analysis and other lesser items appear valid. Analytic prediction of design thermal information based on these methods would seem quite adequate, although caution is urged in extension of this adequacy to other less similar structural elements where correlation is relatively non-existent at this time. (Author)


Descriptors :   *THERMAL ANALYSIS , *AIRCRAFT PANELS , BOOST GLIDE VEHICLES , MATHEMATICAL MODELS , RESEARCH AIRCRAFT , MANNED SPACECRAFT , HEAT TRANSFER , INSTRUMENTATION , THERMOCOUPLES , MATHEMATICAL PREDICTION , THERMAL INSULATION , VACUUM FURNACES , SIMULATION , THERMAL RADIATION , FUSELAGES , ATMOSPHERE ENTRY , PRESSURE , TEMPERATURE , THERMAL CONDUCTIVITY , REFRACTORY METALS , COMPUTER PROGRAMMING


Subject Categories : Thermodynamics
      Manned Spacecraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE