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Technical Briefs

Numerical Study of Film Cooling Scheme on a Blunt-Nosed Body in Hypersonic Flow

[+] Author and Article Information
Sung In Kim1

Department of Mechanical and Industrial Engineering,  Concordia University, Montreal, QC, H3G 2W1, Canada

Ibrahim Hassan2

Department of Mechanical and Industrial Engineering,  Concordia University, Montreal, QC, H3G 2W1, CanadaIbrahimH@alcor.concordia.ca

1

Present address: Pratt & Whitney Canada, Longueuil, Québec, Canada.

2

Corresponding author.

J. Thermal Sci. Eng. Appl 3(4), 044501 (Oct 13, 2011) (7 pages) doi:10.1115/1.4005052 History: Received December 27, 2010; Revised August 26, 2011; Published October 13, 2011; Online October 13, 2011

In hypersonic flight, the prediction of aerodynamic heating and the construction of a proper thermal protection system (TPS) are significantly important. In this study, the method of a film cooling technique, which is already the state of the art in cooling of gas turbine engines, is proposed for a fully reusable and active TPS. Effectiveness of the film cooling scheme to reduce convective heating rates for a blunt-nosed spacecraft flying at Mach number 6.56 and 40 deg angle of attack is investigated numerically. The inflow boundary conditions used the standard values at an altitude of 30 km. The computational domain consists of infinite rows of film cooling holes on the bottom of a blunt-nosed slab. Laminar and several turbulent calculations have been performed and compared. The influence of blowing ratios on the film cooling effectiveness is investigated. The results exhibit that the film cooling technique could be an effective method for an active cooling of blunt-nosed bodies in hypersonic flows.

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Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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Figure 1

Schematic view of computational domain and boundary conditions

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Figure 2

3D Grid system for a blunt-nosed body in a hypersonic flow (AoA = 0 deg)

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Figure 3

Temperature (T/T∞ ) contours on a blunt body (M∞  = 8.8, T∞  = 120 K, AoA = 0 deg)

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Figure 4

Comparison pressure and heat transfer on a hemisphere cylinder with experimental data

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Figure 5

Pressure and temperature contours over a blunt-nosed body. (M∞  = 6.56, P∞  = 1185.5 Pa, T∞  = 231.24 K, AoA = 40 deg).

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Figure 6

Comparison of centerline film cooling effectiveness for different turbulence models (BR = 1.0)

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Figure 7

Grid system for a blunt-nosed body in a hypersonic flow, AoA = 40 deg, with film cooling

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Figure 8

Comparison of temperature (T/T∞ ) contours at center plane (z/d = 0) between laminar and turbulent calculations. (M∞  = 6.56, P∞  = 1185.5 Pa, T∞  = 231.24 K, AoA = 40 deg).

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Figure 9

Comparison of film cooling effectiveness (η = (Taw  − Tm )/(Tc  − Tm )) distributions on the target surface between laminar and turbulent calculations. (BR = ρc uc /ρm um  = 2.45, Tm  = 2195 K).

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Figure 10

Schematic view of film cooling flow fields on a blunt body in a hypersonic flow

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Figure 11

Temperature and effectiveness distributions at different blowing ratios

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Figure 12

Comparison of film cooling effectiveness for different blowing ratios

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