NDLI: Computational investigation of supersonic boundary layer transition over canonical fuselage nose configurations

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Computational investigation of supersonic boundary layer transition over canonical fuselage nose configurations

Content Provider	NASA Technical Reports Server (NTRS)
Author	Chang, Chau-Lyan Ueda, Yoshine White, Jeffery A. Atobe, Takashi Fujii, Keisuke Ishikawa, Hiroaki Li, Fei Choudhari, Meelan M. Tokugawa, Naoko
Copyright Year	2012
Description	Boundary layer transition over axisymmetric bodies at non-zero angle of attack in supersonic flow is numerically investigated as part of joint research between the National Aeronautics and Space Administration (NASA) and Japan Aerospace Exploration Agency (JAXA). Transition over four axisymmetric bodies (namely, Sears-Haack body, semi-Sears-Haack body, 5-degree straight cone and flared cone) with different axial pressure gradients has been studied at Mach 2 in order to understand the effect of axial pressure gradient on instability amplification along the leeward symmetry plane and in the region of nonzero crossflow away from it. Comparisons are made with measured transition data in Mach 2 facilities as well as with predicted and measured transition characteristics for a 5-degree straight cone in a Mach 3.5 low disturbance tunnel. Limitations of using linear stability correlations for predicting transition over axisymmetric bodies at angle of attack are pointed out.
File Size	1739313
Page Count	20
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20120012434
Archival Resource Key	ark:/13960/t7jq5zr27
Language	English
Publisher Date	2012-07-09
Access Restriction	Open
Subject Keyword	Aerodynamics Amplification Supersonic Flow Pressure Effects Stability Boundary Layer Transition Angle of Attack Supersonic Boundary Layers Axisymmetric Bodies Pressure Gradients Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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