Accession Number : ADA614592


Title :   Development of a Test to Evaluate Aerothermal Response of Materials to Hypersonic Flow Using a Scramjet Wind Tunnel (Postprint)


Descriptive Note : Interim rept. 6 Apr 2010-7 Apr 2010


Corporate Author : UES INC DAYTON OH


Personal Author(s) : Jefferson, George ; Cinibulk, Michael K ; Parthasarathy, Triplicane A ; Petry, M D ; Mathur, Tarun ; Gruber, Mark R


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a614592.pdf


Report Date : May 2010


Pagination or Media Count : 20


Abstract : A methodology to evaluate the aerothermal response of sharp leading edge materials by exposing them directly to hypersonic flow up to Mach 7 was developed and evaluated. The exposure was conducted using a prototype scramjet engine as a wind tunnel. A sample holder was designed using combustion fluid dynamics results as inputs into structural models. The rig conditions were evaluated and found to be close to those during free flight, with respect to aerothermal parameters of importance for material survivability. Samples of ultra high-temperature ceramics and SiC were found to withstand the short-term exposure that simulated Mach 6.5 at 25 km altitude.


Descriptors :   *AEROTHERMODYNAMICS , *HYPERSONIC FLOW , *WIND TUNNELS , CERAMIC MATERIALS , COMBUSTION , EXPOSURE(GENERAL) , FLOW , FLUID DYNAMICS , FREE FLIGHT , HIGH TEMPERATURE , HYPERSONIC CHARACTERISTICS , LEADING EDGES , MATERIALS , METHODOLOGY , MODELS , PARAMETERS , PROTOTYPES , RESPONSE , SAMPLING , SHORT RANGE(TIME) , SIMULATION , STRUCTURAL PROPERTIES , SUPERSONIC COMBUSTION RAMJET ENGINES , SURVIVABILITY , TEST AND EVALUATION


Subject Categories : Test Facilities, Equipment and Methods
      Fluid Mechanics
      Thermodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE