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TECHNICAL PAPERS

Compressibility Effects on the Extended Crocco Relation and the Thermal Recovery Factor in Laminar Boundary Layer Flow

[+] Author and Article Information
B. W. van Oudheusden

Department of Aerospace Engineering, Delft University of Technology, PO Box 5058, 2600 GB Delft, The Netherlandse-mail: B.W.vanOudheusden@LR.TUDelft.nl

J. Fluids Eng 126(1), 32-41 (Feb 19, 2004) (10 pages) doi:10.1115/1.1637626 History: Received February 20, 2003; Revised August 27, 2003; Online February 19, 2004
Copyright © 2004 by ASME
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Figures

Grahic Jump Location
Self-similar solutions for the transformed profiles of the velocity f, the enthalpy θ and the total enthalpy θ+f′2. Symbols indicate calculations with Sutherland’s viscosity law, lines for the power-law, see legend in the figure (Pr=0.7,β̃=0,Me=5).
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Effect of Mach number, viscosity law and pressure gradient on f (0) and recovery factor r; top: β̃=0, center: β̃=1, bottom: β̃=−0.15; dashed lines indicate results for Sutherlands’s law with Tt=300 K (Pr=0.7).  
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Normalized recovery factor data and Mach number scaling; left: effect of viscosity-law exponent ω in flat-plate flow (β̃=0); right: effect of pressure-gradient parameter β̃ with linear viscosity law (ω=1), dotted line indicates Me=∞. Symbols apply to numerical data for Pr=0.7. Lines in the bottom diagrams represent the exact (solid) or approximate (dashed) results of the perturbation analysis.
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Nonsimilar boundary layer development (Pr=0.7); top: Me=M0(1+ξ); bottom: Me=M0(1−ξ). Solid lines are for ω=1 (dotted line indicates M0=∞), dashed lines are for ω=0.75.

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