Accession Number : AD0465896


Title :   THEORETICAL EFFECTS OF REENTRY AERODYNAMIC HEATING ON THE EXTERNAL SKIN STRUCTURE OF AMRAD EXPERIMENT NUMBER ONE


Corporate Author : ARMY MISSILE COMMAND REDSTONE ARSENAL AL SYSTEMS RESEARCH DIRECTORATE


Personal Author(s) : Burleson, W G ; Reynolds, R A


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/465896.pdf


Report Date : 30 Apr 1965


Pagination or Media Count : 45


Abstract : Calculated reentry aerodynamic heating effects on the external skin of an ICBM reentry test vehicle having a relatively low weight-to-drag ratio are presented in this report. The vehicle is a blunt cone with the aft portion designed to fail just after maximum heating and the forward portion designed to survive to impact. The tape-wound, reinforced plastic heat shield is subjected to maximum reentry heating rates between 1,250,000 and 6,500,00 kcal/sq m hr. Resulting external and internal surface temperature histories are given. Effects of extreme trajectory, vehicle characteristics, and atmosphere variations on the aluminum substructure temperature histories are discussed.


Descriptors :   *AERODYNAMIC HEATING , *REENTRY VEHICLES , ABLATION , AIRFRAMES , ALUMINUM , ANTIMISSILE DEFENSE SYSTEMS , ATMOSPHERE ENTRY , BASE FLOW , BLUNT BODIES , CONICAL BODIES , DRAG , EQUATIONS , GLASS , GRAPHICS , GUIDED MISSILE TRAJECTORIES , HEAT SHIELDS , HEAT TRANSFER , MATHEMATICAL ANALYSIS , NOSE CONES , PHENOLIC PLASTICS , RADAR , RECOVERY , SEPARATION , SURFACE TEMPERATURE , TABLES(DATA) , THEORY , THERMAL INSULATION , THICKNESS , VOLUME , WEIGHT


Subject Categories : Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE