Passive Nosetip Technology (PANT) Program. Volume XIII. An Experimental Study to Evaluate Heat Transfer Rates to Scalloped Surfaces - Data Report

Abstract

Hypersonic wind tunnel tests conducted in the Naval Ordnance Laboratory Tunnel Number 8 are described. One calorimeter model which was an exact replica of a scalloped low-temperature-ablator nosetip model was tested at Mach 5, with a total temperature of 830 deg R and freestream unit Reynolds numbers from 2 million to 21 million per ft. Measured heat transfer rates are 1.5 to 2.3 times corresponding smooth wall turbulent predictions. Heating data agree nominally with heat transfer rates inferred from the ablation test results. It is conjectured that scallops increase surface heating through effects on the shock layer flow.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1974
Accession Number
ADA020711

Entities

People

  • M. R. Wool
  • T. C. Derbidge

Tags

Communities of Interest

  • Advanced Electronics
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Convection
  • Data Reduction
  • Flow
  • Flow Fields
  • Free Stream
  • Heat Transfer
  • Heat Transfer Coefficients
  • Mach Number
  • Materials
  • Plastic Explosives
  • Pressure Distribution
  • Reynolds Number
  • Test Facilities
  • Thermal Conductivity
  • Thermal Properties
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Mathematics or Statistics
  • Thermal Physics or Thermal Science.

Technology Areas

  • AI & ML
  • AI & ML - Bayesian Inference
  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow