Accession Number : ADA266543


Title :   A Comparison of Computational and Experimental Data for a Subscale High Speed Propulsive Nozzle at Low Mach Numbers


Descriptive Note : Master's thesis


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING


Personal Author(s) : Hyun, Yonghee


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a266543.pdf


Report Date : Jun 1993


Pagination or Media Count : 166


Abstract : This computational study of a hypersonic sub-scale nozzle/cowl configuration compares numerical solutions with experimental data for nozzle performance at off design conditions (subsonic through supersonic Mach numbers. A combination of Van Leer and Roe flux-splitting algorithms was used to solve the flow field. The explicit formulation assumed laminar planar flow and the perfect gas equation of state. A validation for the numerical algorithm was accomplished by comparing with experimental data for a variety of cases. Grid refinement, geometry, and operating conditions all influenced the comparison of the experimental and computational data. Generally, as the Mach number and nozzle pressure ratio increased, the consistency between the experimental results showed better agreement, although the computational investigation was performed on the basis of planar, laminar flow. For the different cowl configurations, the results for baseline and -5 degree cowl show a better agreement than the long and +5 degree cowl.


Descriptors :   *HIGH VELOCITY , *MACH NUMBER , *LOW RATE , *HYPERSONIC NOZZLES , ALGORITHMS , RATIOS , EXPERIMENTAL DATA , FORMULATIONS , THESES , FLOW FIELDS , CONFIGURATIONS , GEOMETRY , LAMINAR FLOW , EQUATIONS , SPLITTING , UNSTEADY FLOW , FLOW , PRESSURE , SCALE , CONSISTENCY , GRIDS , COMPARISON , COMPUTATIONS , VALIDATION


Subject Categories : Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE