Aerospace applications of luminescent paint Part two: Heat transfer measurement

J R Kingsley-Rowe, G D Lock, A G Davies

Research output: Contribution to journalArticle

5 Citations (Scopus)

Abstract

A heat transfer measurement technique has been developed, which utilised a laser to heat a spot of the 'standard' luminescent paint on an insulated metal wind tunnel model. The convective heat transfer coefficient was determined from the experimental quasi steady-state surface temperature. and solutions obtained from radial and axial conduction in a numerical heat transfer model. The convective heat transfer coefficient variation over both a flat plate and a NACA 0012 aerofoil have been measured in transonic flow. Measurements obtained from the flat plate were seen to agree well with correlation data from the literature. Measurements on the NACA 0012 aerofoil indicated the point of transition from laminar to turbulent boundary layer as well as the location of shock boundary layer interaction. The luminescent paint provided simultaneous measurements of pressure and temperature (see Part 1). The distribution of pressure over the NACA 0012 aerofoil was shown to be in excellent agreement with conventional transducer data, although the luminescent paint data provided greater spatial resolution. The position of the shock determined from the heat transfer measurements was shown to be in excellent agreement with the pressure measurements.
Original languageEnglish
Pages (from-to)649-656
Number of pages8
JournalAeronautical Journal
Volume107
Issue number1077
Publication statusPublished - 2003

Fingerprint

Aerospace applications
Paint
Heat transfer
Airfoils
Heat transfer coefficients
Boundary layers
Transonic flow
Surface states
Pressure measurement
Wind tunnels
Transducers
Temperature
Lasers
Metals

Cite this

Aerospace applications of luminescent paint Part two: Heat transfer measurement. / Kingsley-Rowe, J R; Lock, G D; Davies, A G.

In: Aeronautical Journal, Vol. 107, No. 1077, 2003, p. 649-656.

Research output: Contribution to journalArticle

Kingsley-Rowe, JR, Lock, GD & Davies, AG 2003, 'Aerospace applications of luminescent paint Part two: Heat transfer measurement', Aeronautical Journal, vol. 107, no. 1077, pp. 649-656.
Kingsley-Rowe, J R ; Lock, G D ; Davies, A G. / Aerospace applications of luminescent paint Part two: Heat transfer measurement. In: Aeronautical Journal. 2003 ; Vol. 107, No. 1077. pp. 649-656.
@article{a0af3d9aaa40457d966d14d1049e91d0,
title = "Aerospace applications of luminescent paint Part two: Heat transfer measurement",
abstract = "A heat transfer measurement technique has been developed, which utilised a laser to heat a spot of the 'standard' luminescent paint on an insulated metal wind tunnel model. The convective heat transfer coefficient was determined from the experimental quasi steady-state surface temperature. and solutions obtained from radial and axial conduction in a numerical heat transfer model. The convective heat transfer coefficient variation over both a flat plate and a NACA 0012 aerofoil have been measured in transonic flow. Measurements obtained from the flat plate were seen to agree well with correlation data from the literature. Measurements on the NACA 0012 aerofoil indicated the point of transition from laminar to turbulent boundary layer as well as the location of shock boundary layer interaction. The luminescent paint provided simultaneous measurements of pressure and temperature (see Part 1). The distribution of pressure over the NACA 0012 aerofoil was shown to be in excellent agreement with conventional transducer data, although the luminescent paint data provided greater spatial resolution. The position of the shock determined from the heat transfer measurements was shown to be in excellent agreement with the pressure measurements.",
author = "Kingsley-Rowe, {J R} and Lock, {G D} and Davies, {A G}",
note = "ID number: ISI:000186700900002",
year = "2003",
language = "English",
volume = "107",
pages = "649--656",
journal = "Aeronautical Journal",
issn = "0001-9240",
publisher = "Royal Aeronautical Society",
number = "1077",

}

TY - JOUR

T1 - Aerospace applications of luminescent paint Part two: Heat transfer measurement

AU - Kingsley-Rowe, J R

AU - Lock, G D

AU - Davies, A G

N1 - ID number: ISI:000186700900002

PY - 2003

Y1 - 2003

N2 - A heat transfer measurement technique has been developed, which utilised a laser to heat a spot of the 'standard' luminescent paint on an insulated metal wind tunnel model. The convective heat transfer coefficient was determined from the experimental quasi steady-state surface temperature. and solutions obtained from radial and axial conduction in a numerical heat transfer model. The convective heat transfer coefficient variation over both a flat plate and a NACA 0012 aerofoil have been measured in transonic flow. Measurements obtained from the flat plate were seen to agree well with correlation data from the literature. Measurements on the NACA 0012 aerofoil indicated the point of transition from laminar to turbulent boundary layer as well as the location of shock boundary layer interaction. The luminescent paint provided simultaneous measurements of pressure and temperature (see Part 1). The distribution of pressure over the NACA 0012 aerofoil was shown to be in excellent agreement with conventional transducer data, although the luminescent paint data provided greater spatial resolution. The position of the shock determined from the heat transfer measurements was shown to be in excellent agreement with the pressure measurements.

AB - A heat transfer measurement technique has been developed, which utilised a laser to heat a spot of the 'standard' luminescent paint on an insulated metal wind tunnel model. The convective heat transfer coefficient was determined from the experimental quasi steady-state surface temperature. and solutions obtained from radial and axial conduction in a numerical heat transfer model. The convective heat transfer coefficient variation over both a flat plate and a NACA 0012 aerofoil have been measured in transonic flow. Measurements obtained from the flat plate were seen to agree well with correlation data from the literature. Measurements on the NACA 0012 aerofoil indicated the point of transition from laminar to turbulent boundary layer as well as the location of shock boundary layer interaction. The luminescent paint provided simultaneous measurements of pressure and temperature (see Part 1). The distribution of pressure over the NACA 0012 aerofoil was shown to be in excellent agreement with conventional transducer data, although the luminescent paint data provided greater spatial resolution. The position of the shock determined from the heat transfer measurements was shown to be in excellent agreement with the pressure measurements.

M3 - Article

VL - 107

SP - 649

EP - 656

JO - Aeronautical Journal

JF - Aeronautical Journal

SN - 0001-9240

IS - 1077

ER -