Accession Number : AD0662357

Title :   LAMINAR AND TRANSITIONAL HEAT TRANSFER IN THE TWO-DIMENSIONAL SEPARATED FLOW BEHIND A SHARP PROTRUDING LEADING EDGE,

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

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

Report Date : JUL 1967

Pagination or Media Count : 64

Abstract : Heat transfer rates are measured in the separated flow region behind the two-dimensional sharp protruding leading edge step model (boundary layer thickness is zero at the separation point) in the high enthalpy laminar near subsonic and supersonic flow in the shock tube. The measurements are carried out in a shock Mach number range from 2.3 to 10, and a corresponding flow Mach number range from 0.5 to 2.62. The Reynolds number, which is based on the height of the leading edge above the flat plate where the heat transfer rates are measured, varies from 300 to 17,000, and the local Reynolds number on the plate varies from 700 to 290,000. The results are correlated in terms of the non dimensional parameters of Nusselt number as a function of the Mach and Reynolds numbers and stagnation to wall enthalpy ratio. The variations of local, average and maximum heat transfer rates are presented. (Author)

Descriptors :   (*HEAT TRANSFER, GAS FLOW), (*FLOW SEPARATION, LEADING EDGES), LAMINAR FLOW, BOUNDARY LAYER TRANSITION, SUBSONIC FLOW, SUPERSONIC FLOW, ENTHALPY, HYPERSONIC FLOW, REYNOLDS NUMBER, TWO DIMENSIONAL FLOW, MACH NUMBER, SHOCK TUBES, ISRAEL

Subject Categories : Aerodynamics
      Fluid Mechanics
      Thermodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE