Accession Number : AD0649868

Title :   LAMINAR HEAT TRANSFER TO A TWO-DIMENSIONAL BLUNT BASE FROM THE HIGH-ENTHALPY FLOW IN THE SHOCK TUBE,

Corporate Author : TECHNION - ISRAEL INST OF TECH HAIFA DEPT OF AERONAUTICAL ENGINEERING

Personal Author(s) : Rom,Josef ; Seginer,Arnan

Report Date : OCT 1966

Pagination or Media Count : 84

Abstract : Heat transfer rates to a two dimensional blunt base of a wedge-flat plate model are measured in a laminar supersonic flow in the shock tube. The measurements are carried out in a shock Mach number range from 2.6 to 11, and a corresponding flow Mach number range from 1.04 to 2.74. The Reynolds numbers, based on the model chord, are varied between 5000 to 500,000. The ratio of local heat transfer rate on the base to the flat plate heat transfer rate is evaluated from the measurements and the flow conditions of the various experiments. In all cases these measurements indicate a hot peak at the base center, and in some cases there are additional smaller peaks towards the base corners. The maximum and the average heat transfer rates to the base are found to be only slightly sensitive to shock Mach number, being 0.5 and 0.3 of q sub (f.p.) respectively, except in the case of choked flow (i.e. nearly sonic separation) where the average heat transfer rate approaches the value of the flat plate heat transfer rate. (Author)

Descriptors :   (*HEAT TRANSFER, SUPERSONIC FLOW), BLUNT BODIES, FLAT PLATE MODELS, ENTHALPY, SHOCK TUBES, LAMINAR FLOW, MACH NUMBER, REYNOLDS NUMBER, ISRAEL

Subject Categories : Fluid Mechanics
      Thermodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE